Gas turbine controlling apparatus and gas turbine system using same

Gas turbine control device and gas turbine system

technical field

The invention relates to a method for controlling gas turbine device and a system device. The, the invention relates to for to control combustion the vibration control device; and for a control system device.

background technology

Around the traditional gas turbine, a respectively and combustion air chamber and a flow plug in according to power generator and output temperature and humidity of surrounding air, moreover traditional gas turbine according determined flow movement. However, and a spring of the compressor and aging filter stopper, comprising an actual flow with the component number with or wherein test pushing said ring-shape with inconsistent possibility of gas turbine. At the same time, a possibly reducing combustion the stability, and wherein the combustion vibration discharge device. The combustion a vibration hinder seriously the movement of gas turbine. Therefore, communicated from the industrial protection device device and operation rate's viewpoint, the superstrong carrier vehicle or a combustion vibration discharge device. In turn to lining with the needs, a technical skilled engineer multiple regulating gas turbines' the control system of the support, to prevent the combustion vibration discharge device and ensure the retaining combustion the stability. However, which is arranged on the expense of maintaining in order; and switching maintenance coefficient of gas turbine.

The light of the upper description, the Japanese common patented claim JP-A-Heisei (9269107) claimed is a restraining combustion chamber of the vibration device and method. The reference fuse burning, where control device comprises a combustion type body part. Combustion type body part with a frequency analyzer, the central processing unit, a power amplifier and a controller part. The variable analyzer of the combustion chamber the pressure sensor the floating of combustion gas pressure detector end of the frequency tension, the central processing element according to the floating pressure of the frequency of the frequency analyzer computer, obtains the oscillatory stability of the combustion chamber. The power amplifier is a conical to a central output signal, the output signal of the drive part for producing enlarge the valve switch signal, and a control to the combustion valve. The large paying operating to control method of the combustion frequency vibration, when the combustion vibration, the frequency of the combustion vibration of the prediction according to the ratio of the oil and gas. When the combustion frequency vibration, wherein the ratio of fuel gas and is pressed on the surface of the frequency vibration combustion. The infinite low combustion frequency vibration energy with an adverse impact is device, a suppressing the lower combustion frequency, and capable of making the device to avoid the destruction.

The invention outline, a water outlet of the invention is therefore provide the gas turbine control device and a gas turbine system, combustion vibration in the gas turbine can is suppressed; the combustion stability of gas turbine can with the reinforced.

The aim of the invention is provide the gas turbine control device and a gas turbine system, a drainage air degree of the gas turbine comprising a reducing.

The aim of the invention is provide the gas turbine control device and a gas turbine system, a detachable of the gas turbine the frequency of the combustion vibration, moreover energy vibrate according to the spring the combustion type of the tension.

The invention relates is provide the gas turbine control device and a gas turbine system, for keeping the combustion stability of gas turbine, which is composed of gas turbine performance along with force of time variable-frequency.

The aim of the invention is provide the gas turbine control device and a gas turbine system, improving the reliability of gas turbine, the service life of gas turbine, the last reducing the maintenance cost.

The aim of the invention is provide the gas turbine control device and a gas turbine system, capable of using the remote monitoring to the movement of gas turbine, in turn to be a countermeasure extending to the abnormal and.

The aim of the invention is provide a gas turbine remote monitoring system, a controls the centralized screen is multiple gas turbines with a remote seat, for controlling operation efficiency.

The invention, wherein a handle, a gas turbine control device comprises a frequency tension member and control unit. The frequency a tension component and each combustion chamber gas turbine combustion chamber at least a vibration a vibration of hydraulic end of the frequency tension, and output frequency first tension spring, and multiple preset variable frequency bands tension results. The control unit cover according to the frequency bands the frequency first tension results, at least one air and first air flow the two discharging to the fuel first fuel flow rate end of the control. The oil and gas product refers to the gas turbine.

Here; the control unit is comprises a control part and a back part. The control output section expressed gas turbine operation state in data and method for controlling gas turbine control signal. The intensity of the frequency tension spring display vibration relative of the frequency bands a frequency is a threshold value hole, the frequency belt is a unusual frequency interlayer, the back part to unusual frequency and a control section in data determining unusual frequency fastening calibrating data, and according to the determined calibrating data and control signal, at least and first air flow the two discharging to the first fuel flow rate end of the control.

The shell; the control unit is comprises a database, wherein the database storing with belong to the other gas turbine multiple groups of fuels second fuel flow rate and second air flow; And is in the second gas turbine combustion chamber at least pressure vibration and second gas turbine each combustion chamber a vibration a variable frequency second tension spring. The back part corresponding to the first frequency tension spring frequency second tension spring at least a second fuel flow rate and second air flow, wherein at least determining calibrating data the first fuel flow rate and a first air flow. Automobile, the back part of the base determined calibrating data and control signal, wherein at least a first fuel flow rate and a first air flow.

Similarly; the control unit is further - comprising try the operating part, for determining the gas turbine part and running status different testing work state, the testing operation state of determined comprising a first fuel gas and air flow test flow. The back cover component according to each determined testing operation state); the gas turbine to try to move. The variable tension member and each combustion chamber at least one of a vibration to the gas turbine combustion chamber internal pressure vibration end of the frequency tension, and multiple output frequency bands frequency first tension results according to tries movable. Tries the operating part determined to try to move according to work state in the data and frequency first tension spring, the determined gas turbine the priority shipment parallel, and capable of reducing the vibration intensity.

The first fuel flow rate capable of the main fuel flow and at least one of pilot-ignition oil flow. Similarly, the first air flow capable of the gas turbine air flow and an air flow at least one of the inlet guide blade is adjusted.

The other aspect of the invention, the gas turbine system of comprises the gas turbine control device, and a combustion chamber gas turbine.

Similarly, the invention, the other side; the gas turbine system and combustion chamber gas turbine comprises an upper gas turbine control device. The calibration comprises a first part and second etched part. The first etched part corresponding to the first frequency tension spring frequency second tension spring at least a second fuel flow rate and second air flow, wherein at least determining calibrating data the first fuel flow rate and a first air flow. The second etched part to determined calibrating data and control signal, wherein at least a first fuel flow rate and a first air flow. The control unit is a further - comprising a first and second corresponding part; And a database, the first etched part and second corresponding can provide part is far away from the control part and control unit of frequency tension member, the second etched part and first part corresponding. The control part is transmitted in the data through the first and second part of the control unit back part. Similarly, frequency tension member through the first and second part of the first tension frequency readouts of multiple frequency bands to control unit back part. The first calibrates determining the calibration data, and determined calibrating a data transmits the second etched unit through the first and second part corresponding. The second etched part to came the first to calibrate the determined calibrating data and control signal a control part control at least a first fuel flow rate and a first air flow.

Similarly, the invention, the other side; the gas turbine control method with the inner layer is: The pressure vibration and a at least metrical data the turbine of the combustion chamber a vibration connected with the turbine combustion chamber; End of the frequency tension is provided with a frequency tension spring to the metrical data; Frequency of the tension spring is multiple frequency stainless steel; According to the frequency tension results and multiple frequency bands' threshold values, determined according to the gas fuel turbine flow rate and air flow at least a back; the dataAnd according to the instruction gas turbine operation state in data and back data management gas turbine.

Can provide a program of the gas turbine control method thereof.

Attached or summary pattern 1) is formed according to the invention first embodiments gas turbine control system device and diagram for gas turbine; systemOr 2 determines for calibrating the data of the first implementation example's gas turbine control device of a formed; Or 3 determines for calibrating the data of the first implementation example's gas turbine control device is formed; Radiator (4) is formed according to the invention second embodiments gas turbine control system device and diagram for gas turbine; systemRadiator (5) is formed according to the invention third embodiments gas turbine control system device and diagram for gas turbine; systemRadiator (6) is formed according to the invention fourth embodiments gas turbine control system device and diagram for gas turbine; systemRadiator (7) is formed according to the invention fifth embodiments gas turbine control system device and diagram for gas turbine; systemHeatsink 8) is within the embodiments the testing and image of gas turbine control device; Radiator (9) is a display determines the invention gas turbine control device is priority shipment rod of the image of process; Radiator (10) is invention gas turbine remote monitoring system the diagram system of; aHeatsink 11 of the invention gas turbine control device of gas turbine system structure; diagramHeatsink 12) is invention gas turbine control device the flow pattern of; andRadiator (13) is a display calculates calibrating data the diagram of curves of functional relation of the invention gas turbine control device; Radiator (14) is a flat representation of the invention gas turbine control device end of the combustion oscilation frequency tension the spring diagram of curves; Radiator (15) is a flat representation of the gas turbine the frequency of gas turbine control device, wherein the calibration data and vibration intensity the image of relation; And heatsink 16) is invention gas turbine control device the flow pattern of operation.

The preferred embodiment is as follows, a as to the attached radiator, and invention to the invention the gas turbine the gas turbine of control device is arranged on the detailed description systematically.

A although of a gas turbine and example the control device for the invention to describe, while the invention can the other combustion vibrations of the fuel-burning device.

The first joint, specifically to a attached or 11, concerning to the invention gas turbine control device and gas turbine system the gas turbine 2 describes.

Or 11 schematic display gas turbine 2 structure. The gas turbine (2) comprises a turbine main body (100) and combustion part 110.

On the out of the combustion part is more than 110 a combustion chamber or bases (m is more than 1) is a combustion chamber. The afterward description, which are expressed the combustion chamber 111-1 structures are 111-m, the mark 111,And when each combustion chamber describes hole, the mark is 111-1 structures are 111-m. A split air pipe ingress 117, sliding valve of the combustion chamber (111) is 118, the energy air mixing tube 119, wherein the burning gas interface pipe ingress 120, a fuel supply valve (115) and pilot-ignition fuel supplying valve (116), a describe of the mediate way.

The heatsink 11 display first combustion chamber 111-1, therefore, the fixing description is defined in the first combustion chamber and accessory.

The turbine main body (110) comprises a compressor 101, wherein the compressor is equipped with an inlet guide blade (102), a rotating shaft (103) and a turbine 104. The combustion part (110) comprises an air lead-in part (112) and split air ingress pipe and 117-1 sliding valve 118-1 and split air mixing tube 119-1 and burning gas ingress pipe and 120-1 combustion chamber 111-1 and a main oil flow control valve and 113 pilot-ignition oil flow control valve (114) and a main oil supplying valve 115-1 and a pilot-ignition fuel supplying valve 116-1. Gas turbine (2) and a power generator 121 ring.

The air from outside the feed pipe (101); and a compression the compressor through hole, relative to the combustion chamber 111. On the other side, the fuels through the pilot-ignition oil flow control valve (114), the supply combustion chamber 111 pilot-ignition fuel 116 valve hole, wherein the combustion chamber 111. The surplus fuels through the main exhaust gas flow control valve (113), the supply combustion chamber 111 main oil supply 115 valve hole, wherein the combustion chamber 111. The air and gas according inducts 111) in internal combustion chamber. The combustion, the burning gas generating device is inducted the turbine 104, wherein said to drive the turbine 104 rotations. Generator 121 turbine 104 conversions rotating of energy and electric energy.

Now 11, wherein each part or a describe.

The first, a describe the turbine main body (100).

The turbine 104 and burning gas interface pipe ingress 120 ring; the efficient is propped to the burning gas exhaust. The turbine 104 (101) is connected with the compressor; and a rotating shaft (103 and 121 generator ring. The burning gas interface pipe ingress 120, the combustion chamber is 111 to 104 provide the burning gas to the turbine. The turbine 104 the wind energy of combustion gas the rotary energy, and a first rotating. And a spring of the turbine rotations 104, 121 generator and compressor (101) receives to drive a. The burning gas interface pipe is made to generate electricity hole, and is arranged to unit.

The compressor (101) and outsideair's introduction pipeline and a compressed air for part and 112,)through a rotating shaft (103 and 104 turbine generator and 121 ring. The rotary of turbine transmits compressor 101, wherein the compressor is) is a. Air surrounded by the rotation movement of air compressor. Hole; the air of the compressor (101 compressions, and compressed air chamber is embedded in the combustion chamber 111.

The flow guide blade 102) is rotary blades, in which the compressor 101 air inlet ends. Capable of adjusting rotating blade angle, and has 101 compressor the air flow adjusting, which if the compressor (101) formed to the mediate variable rotation. The rotating blade of the gas turbine section and control 3, wherein a describe is as follows.

The rotating shaft (103 and 101 compressor, are 104 and 121 generator connected, and transmits the turbine (104 moments the compressor (101 and 121 generator.

The generator 121 to 103 and 104 turbine connected via a rotating shaft, and turbine rotating 104 conversions of energy and electric energy.

Now, 110) for describe the combustion part.

The compressed air inducts the part (112) is provided with a space; the ingress pipe and combustion part 110 shell of the air feed pipe and compressor (101) connected, and a compressed air feed pipe combustion chamber of the compressor and 101 111-1.

The divided-flow ingress air pipe for 117-1 the part with an air 112), with an opening, wherein the other end is sliding valve 118-1 connected. The divided-flow ingress air pipe for 117-1 supply of the combustion chamber 111-1 air to the energy 104 turbine.

A sliding valve 118-1 end of the flow ingress air pipe 117-1 connected, and other end of the flow air mixing tube connected 119-1. The sliding valve 118-1 the gas turbine control part 3) of as follows description, control through a split air ingress pipe 117-1 air current.

A split air mixing tube 119-1 and sliding valve 118-1 connected, the other end of combustion gas ingress pipe connected 120-1. The divided-flow air mixing tube 119-1 is made 120-1 is coupled to the burning gas ingress pipe through the sliding valve 118-1 air, combustion gas mixing in order to 111-1 generating with a combustion chamber and.

A main oil flow control valve (113) and end is connected with the external feed's fuel pipeline, the other end of 115-1 fixing the m connected with the pipeline is connected with the main oil supply valve. The main oil flow control valve (113) of the gas turbine control part 3) is as follows described, is controlled by the outer to the combustion chamber (111) and fuel flow rates. The combustion chamber main 111 burner a main oil flow control valve (113) fuels.

A main oil supplying valve 115-1 end of said main control valve is 113, the other end and is connected with the pipeline of the combustion chamber (111) connected burner. The main oil supplying valve 115-1 the gas turbine control part 3) is as follows described, control supply combustion chamber 111-1 main fuel burners' flow rates.

A fuel pilot-ignition flow control valve (114) and end is connected with the external feed's fuel pipeline; the other end 116-1 piece at m is connected with multiple pilot-ignition oil supply valve. Pilot-ignition oil flow control valve (114) of the gas turbine control part 3) is as follows described, control from the outside of the combustion chamber fuel 111 rates flow. The combustion chamber 111 ignition burner of the fuel pilot-ignition flow control valve (114) fuels.

A pilot-ignition fuel supplying valve 116-1 end and is connected with the pipeline of pilot-ignition oil flow control valve is 114, the other end and is connected with the pipeline of the combustion chamber 111-1 ignition connected burner. The pilot-ignition fuel supplying valve 116-1 the gas turbine control part 3) is as follows described, wherein the control supply combustion chamber 111-1 burner ignited fuel flow rate.

The combustion room 111-1 for the part with the supplying air conditioner compressed air 112), a pipeline and a fuel supply main oil supplying valve 115-1, wherein a pipeline connected, the fuel feed's pilot-ignition fuel supplying valve 116-1 and discharging combustion gas combustion gas ingress pipe is 120-1. The combustion room 111-1 receiving supplies' fuels and air, wherein a combustion the high-temperature pressure burning gas. Gas combustion according and producing to the turbine 104.

A combustion gas ingress pipe 120-1 end of the combustion chamber 111-1 connected, the other end and a turbine 104). Combustion gas ingress pipe 120-1 midway connected with the air flow mixing tube is 119-1. The combustion gas ingress pipe 120-1 is used to the turbine 104 of combustion gas and air flow.

(The first embodiments now), the finger attached radiator, a explain of the invention first embodiments the gas turbine control device and gas turbine 2 gas turbine system.

Radiator (1) is the invention gas turbine control device circuit structure diagram. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) in a depth measuring part (4) and a main oil flow control part (5) and pilot-ignition oil flow control part (6) and a split air flow console section (7) and a guide blade console section (8) and a pressure measuring variable-frequency part (9) and a central parts 10.

On the other side; the gas turbine control part (3) comprises a control part (11) and a tension variable parts (12) and back function pilot-ignition oil flow back part 21. The fuel pilot-ignition flow back part (21) comprises a data calibrating determining part (22) and body part 23.

According to the invention, the gas turbine 2, wherein the control and first quantity's main oil flow rate and pilot-ignition oil flow, and between the first air refrigerant split air flow and manufacture procedure inlet of vane's air flow (main oil flow control part 5, pilot-ignition oil flow control part 6, energy air flow console section (7) and a guide blade console section (8); the combustion chamber 111 combustion fuel. A on the electric generator is the burning gas. The gas turbine 2 statuses running through the depth measuring part 4) controls the monitoring according to the process value. Moreover, the infinite intelligent pressure and a vibration of the variable-frequency pressure measuring part (9), a central parts 10) is simultaneously is the monitoring.

On the other side, according to the invention, a gas turbine control part 3) and fuels air for gas turbines 2 movement. Gas turbine control part (3) is in monitoring value monitoring gas turbine of 2 statuses. Moreover, a gas turbine section and 3 monitoring gas turbines 2, comprising as the pressure and speed according and thereby, and a frequency tension member 12 pairs analyzing optimal. The first embodiments, a pilot-ignition oil flow back part 21 pilot-ignition determining fuel rates of flow' calibrating values, and output pilot-ignition oil flow control part, 6 is pressed the pressure and a vibrate.

, Wherein the gas turbine control section (3 observations vibrate of the combustion of the gas turbine is 2, the frequency of the combustion and vibration according to cooling); the gas turbine movements 2 appropriately, specifically, a according to the vibration exchange pilot-ignition oil flow, wherein the combustion type vibrate.

Now 1, the part or a describe.

The gas turbine (2) and reference pattern 11 gas turbine is the same. The display 1 gas turbine 1 structure diagram.

Reference pattern 1, the process depth measuring part (4) is composed of a different in depth measuring device, which are made of observation to the display gas turbine 2 operation state and a corresponding value. The wet-processing depth measuring device is arranged on the gas turbine (2) disposed position; the central spring output the gas turbine section and 3 control section is as follows is fixed to 11 describe. (Power and current voltage of here, process is a to produce the power generation according typically); the temperature and humidity and different part is surrounded air flow and air pressure and combustion chamber the burning gas temperature and burning gas flow and burning gas pressure compressor, and number of the secondary turbine unit interval/unit time.

Main oil flow control part (5) according to the control command main oil flow of the control part 11 banks which. Main oil flow control part (5) comprises a main oil flow control valve (113) and a main oil supplying valve 115-1 piece at 115-m. Main fan oil flow of a main oil flow control valve (113) controls and limiting. The combustion chamber 111-1 is propped at the 111-m main oil flow 115-1 is propped at the 115-m control and adjusting from the exhaust main oil supply valve are.

Pilot-ignition oil flow control part (6) comprises a command control pilot-ignition oil flow of the control part 11 banks which. The fuel pilot-ignition flow control part (6) comprises a pilot-ignition oil flow control valve and 114 pilot-ignition fuel supplying valve 116-1 piece at 116-m. Pilot-ignition three oil flow of pilot-ignition oil flow control valve (114) controls and limiting. The combustion chamber 111-1 is propped at the 111-m pilot-ignition oil flow 116-1 is propped at the 116-m control and adjusting from the exhaust pilot-ignition fuel supplying valve are.

Split air flow console section (7 111-1 base propped on the 111-m air flow from command control of each combustion chamber of the control part 11 banks which. The divided-flow air flow console section (7) comprises a split air ingress pipe 117-1 is propped at 117-m and sliding valve 118-1 is propped at 118-m, and a split air mixing tube 119-1 piece at 119-m. 111-1 Structures are 111-m surrounds each burning room, the enlarging or reducing corresponding to the sliding valve 118-1 is propped against 118-m the opening, a grease adder or reduce the air flow, thus increasing or the decompression device interval/unit the primary air volume of supply combustion chamber.

Inlet guide blade section console 8) comprises a control command introduction compressor 101 air current according the control part 11 banks which. The, introduces compressor (101) in the air flow to be adjusted through the control inlet guide blade rotating 102 degrees angle adjustment.

Variable-frequency pressure measuring part comprises 9) is fixed; the exhaust combustion chamber 111-1 propped on the pressure measuring device is 111-m. Variable-frequency pressure measuring part 9 111-1 fixing the pressure of 111-m according to the indication measuring combustion chamber of the control part 11 emitting device, and 111-1 is propped against the 111-m determining value of the pressure variable-frequency outputs each combustion chamber the gas turbine section and 3 frequency tension 12 parts.

The speed increasing central part comprises 10) is fixed; the exhaust combustion chamber 111-1 propped on the speed detector unit is 111-m. The speed detector (10 111-1 fixing the 111-m speed according to the instruction measuring each combustion chamber according control part 11 surfaces of two (differentials of the displacement), and 111-1 fixing the speed 111-m determining value outputs each combustion chamber the gas turbine section and 3 frequency tension 12 parts.

On the other side; the gas turbine control part comprises 3 to 2 of the combustion vibration discharge device in the process value, and pressure control speed of gas turbine the gas turbine 2 determines.

Control part (11) comprises a process value of gas turbine determines 2, wherein the control signal output with the main oil flow control part (5), a split air flow console section (7) and a guide blade section console 8, in turn to be a control to claims. Moreover, control part 11) for controlling the pilot-ignition oil flow control part 6 general control signals to the divided-flow pilot-ignition oil flow back part (21 description is as follows), and auxiliary the divided-flow fuel flow rate back part 21 pilot-ignition control oil flow control element 6. The main oil flow control part (5), a split air flow console section (7) and a guide blade console section (8 typically controls the control based on the oil inlet method, the feedback method or the PID method.

The variable tension member (12) comprises a variable-frequency pressure measuring part 9 determinations the pressure variable-frequency the combustion chamber, 111-1 propped at a speed of hydraulic or the circumference of 111-m to each combustion chamber compressor. At the same time, the frequency tension member 12 frequency of multiple frequency bands, and an output each frequency converter is frequency tension spring. Similarly, frequency tension member comprises 12 111-1 to each combustion chamber is propped at the 111-m a frequency to analyze from the information speed of a central part 10 determinations. At the same time, the frequency tension member 12 frequency of multiple frequency bands, and an output each frequency converter is frequency tension spring. Each combustion chamber 111-1 propped at the 111-m results tension to transmit to the pilot-ignition oil flow back part 21.

The fuel pilot-ignition flow back part (21) according to the process is frequency tension spring for each frequency of the pressure and acceleration and rubber, calculates the calibration data. The fuel pilot-ignition flow back part (21) with a turning building accurate by data coming from the values of control part 11 control signal cabin instructions, which is used for controlling the pilot-ignition oil flow control part (6), and outputs a back control signal to the pilot-ignition oil flow back part 6. The fuel pilot-ignition flow back part (21) may comprise a control part 11.

Calibrating data determining part 22 pressure-based and each hoop variable frequency tension spring, a reference calibrating data plug the table (Figure sees 2 and 3, wherein a circulating with a description) and process value of the control part obtain 11, determines the calibration data for calibrating control pilot-ignition oil flow control part 6 control signals. Determined calibrating data output body part 23.

The accumulator (23) of calibrating data is plug the component 22 determined calibrating data to add a values of control part 11 control signal cabin instructions, which is used for controlling the pilot-ignition oil flow control part (6), and to pilot-ignition oil flow control part 6 output calibrating control signals, and controlling latter's control signal.

Now, a as to the attached and movement of gas turbine system to the first embodiments gas turbine control device describes.

The first described, a base back data determined method for controlling the gas turbine and.

Radiator (14) in variable-frequency pressure measuring part 9 determinations the base of undulating pressure quantity's, a frequency tension the diagram of curves of the spring frequency tension member (12) is completed. The diagram of curves horizontal shaft and vertical shaft expressed the frequency vibration and intensity (grade). A see radiator is 14 of the combustion oscilation frequency, namely the has wide range and pressure vibration and a vibration of the combustion chamber (111) with. Therefore, the combustion vibration needs through suppressing the vibration of different frequency a.

As the circumference of each frequency is achieved by the nappe factor; a moving through a single control method and/or the single control parameter. Moreover, force to oscilation variable frequency of vibration. Therefore, although to the frequency belt, and display intensity possibly to permit, and other two frequency interlayer, wherein a vibration is reversely fatal. And a spring of the ends; the gas turbine 2 statuses distributed on rely is based on multiple oscilation frequency parameter controls the control.

Therefore, to realize the outlet of the invention, the first to the following way of calibrates the data (sees or attached 2) and.

Two indicator formed on the comprising a frequency, threshold value and back data and other clauses, each clause a describe is as follows.

(1) Are belt: The variable a to the base of the frequency tension and a measuring the smallest unit.

The first, product defined of the pressure and a frequency vibration range. A example pipe, and is of 0 to 5000 hertz the frequency belt is shown and or 14, wherein the flange is from 0 to 5000 hertz frequency range. Automobile, variable diameter of the connected pipe of the frequency hoop. The other words, variable diameter of an n (n is more than 0) integers. If the frequency range are divided into 50 hertz frequency interlayer, then n is equal to 100. Operating a frequency necessity is provided with the same size.

(2) Threshold value: Surrounds each frequency interlayer, a vibration sensor intensity according for.

Vibration each with frequency (1) is leaned with n) each pressure vibration and a vibration defines a threshold value (1) is leaned with n). Threshold value indeed Sadamoto whether with and/or the structure and oscilation with frequency resonating, whether with the component and/or the structure is easy to destroy the lower oscilation frequency, the 1-5, wherein the end of and/or the structure of bear.

The operating threshold value is as the same around the frequency hoop.

(3) Calibrating data: A represents the calibration data the control signal, and is attached with control part 11 general control signals, in order to each switching fastening variable frequency oscilation to the permitting layer.

Bundles from 1 to n each frequency interlayer, calibrates the data arranged in the depth (. e.g, a power and temperature and humidity and different part fuel flow rate and a pressure difference and air flow and air pressure and combustion chamber for surrounding air with burning gas temperature and burning gas flow and burning gas pressure and interval/unit unit comprises a rotating number of the compressor turbine and) of the pedestal for the process is function to determine. The other words, 1 leaned with n to provide the calibration data is the variable a function f1 to fn (the process is: Electric generator and a temperature and humidity of the surrounding air with of), and function computed spring section and back data. And a spring of the effect on the gas turbine is different because of the frequency interlayer, therefore do not need is the same as that the frequency bands function f1 to fn. Therefore, the process is type do not need is the same as the function.

Relies with function f1 to exchange the fn of the material of the gas turbine 2 structure and gas turbine is 2; and gas turbine of 2 statuses. Therefore, each gas turbine function f1 to fn according to the design feature (structure and material), a data and front of the data determining of similar gas turbine tried to move to obtain.

On the device for fixing the n each frequency a concave 1, does not need is a single threshold value. The other words, possibly the multiple threshold values any two frequency interlayer, and surrounds each threshold value, defines a impeller value. The control section (11 movements rely on the impeller is exchange, capable of adjusting the operation state according to a threshold value layer, a reducing gas turbine 2 working/. A example, a flat the two threshold values, wherein the impeller is determining describes of the following. The shell, a relatively small calibrating data and first threshold value (impeller is 1), and a relative big calibrating data and second threshold value (impeller is 2), which reaches the second threshold value, sounds the alarm.

The display (3 a lining and end of the example form. Reference pattern 3, namely from 1 to n each frequency interlayer, the two threshold values. A example 1, the threshold value is α the frequency belt is 11 α 12, further claims a back data f11 is a threshold value (in value) and f12 (in) is a. Thus, which one vibrated intensity to increase, the circumference of the is suppressed, which do not need annular to exchange the operation state. Therefore, a avoid the gas turbine 2 withstanding the large load, and pressing with the vibration.

The product is capable of each of the control part (main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8) and such as the external part of the valve to claim 2 or 3 and displays data. The first embodiments, 6 device form for fuel pilot-ignition flow control component.

Hole of the pressure vibration or a vibration data possibly is used for forming or a data of pressure vibration and a vibration device according to or 2 or shown in the 3.

Now, a as to or 1, 2 and 12, explained for controlling the pilot-ignition oil flow through the back of the data determining gas turbine (2) and process.

(1) Radiator (12) is a step) of the front and gas turbine system, a data or 2 or 3 or device according to the upper end. The data wire (storage the pattern is not expressed) of the pilot-ignition oil flow back part 21 storing unit.

(2), Then the) of the gas turbine 2 actual performance, the variable-frequency pressure measuring part (9) and a central part 10 measuring each combustion chamber 111-1 is propped against 111-m are the pressure variable-frequency and each combustion chamber of combustion gas 111-1 fixing the speed increasing the 111-m. The metrical data output the frequency tension part of each predetermined time 12. Metrical data of gas turbine section and 3 frequency tension member (12) extending part (Figure the step 12) S1.

(3) The gas turbine section and 3 frequency tension 12 parts end of the frequency tension operation to the metrical data by Fourier a tension, obtains and frequency vibration part is shown and radiator (14) grade relation. Based on, assigns frequency of the preset frequency hoop and the data wire (Figure the step 12) Supply. Automobile, such of a obtain the output pilot-ignition oil flow back part 21 calibrating data determined 22 parts.

(4) The gas turbine section and 3 calibrating data plug the component 22 pairs 1 propped on the n spring and discharging of each frequency interlayer of the frequency tension member (12) is among the storing is formed, wherein to 2 and shown in the radiator (3) is pattern of display) is storing part corresponding frequency fastening threshold value α compares. Speed and hydraulic motor is longer threshold value α hole, a shift calibrating data 0. The contrary one; and part is longer than the corresponding frequency interlayer (is as follows with a called unusual frequency) and a threshold value α hole, made from the process of values control part 11 output end of the housekeeping functional f, a sensor calibrating data (Figure the step 12) S3. Determined calibrating data output body part 23.

(5) The gas turbine section control chamber 3 and 23 arranged from the control pilot-ignition oil flow control part 6 control signals of control part (11) outputs on the corresponding to the back data determining part (22) outputs a signal of calibrating data, a sensor a new control signal, for controlling fuel pilot-ignition flow control part (6) of the step 12) S4.

(6) The gas turbine control part (3) and new determined control pilot-ignition oil flow control part 6 control signals, which is used for controlling the rear (Figure the step 12) S5.

(7) Pilot-ignition the oil flow control part (6) comprises a control signals of the regenerative chamber (23) outputs, the control pilot-ignition fuel supplying valve 116-1 is propped at 116-m or the pilot-ignition oil flow control valve (114).

Product point device of gas turbine 2 movements; for each predetermined time, the step (1) is (7) continuous actuator.

The multiple 13 diagram of curves for displaying accumulator (23) by the example of the gas turbine. Diagram of curves display calibrating data (fp in value) and relationship between pilot-ignition oil supply openings valve. The or 13, wherein the vertical shaft expressed according pilot-ignition fuel supplying valve opening 116, wherein the horizontal shaft expressed calibrating data (fp the process is: MW, surrounding air temperature, so). Or 13 Q0 display structure and back data is 0:00; the pilot-ignition fuel supplying valve opening 116. Groove, is made of calibrating data fp, the pilot-ignition oil supply 116 valve opening rubber the calibration. Claim see calibrating data fp along with the process is exchange.

Although through the calibration 13 fp data (in value), a valve opening rubber to increase, further necessity of the bus. The contrary opening, and reduces along with the structure and/or the frequency of a device.

Similarly, a main oil flow of a split air flow and is connected to the control feed-forward, the control valve or the PID control by inlet guide blade the feed pipe of air is connected to the controller, in order to set and a respective predetermined value.

Thus, the invention, the pilot-ignition oil flow and capable of controlling the pressure function of vibration and a vibration of the gas turbine rubber 2, thus the internal pressure vibration and speed and conditioning. The, the invention, a through the frequency a end is a vibration having variable with the analysis, a determine the back pressure value of each frequency hoop. Therefore, the stability of the operation and power of combustion gas turbine can greatly for.

(Embodiments 2) now, the finger attached on the explained that the invention second embodiments and uses the control device and gas turbine 2 gas turbine system for gas turbine 2 gas turbine control device.

Radiator (4) is a schematic diagram, a display gas turbine control device and invention second embodiments gas turbine system structure. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) comprises in the depth measuring part (4), main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8), a variable-frequency measuring part (9) and a central part 10.

On the other side; the gas turbine control section (3) comprises a control part 11, frequency tension part (12) and back function split air flow back part 24. The divided-flow air flow back part (24) comprises a data calibrating determining part (25) and body part 26.

The invention second embodiments is different from the first embodiments is calibrates the data and is coupled to the pilot-ignition oil flow, further diverging to the air flow, as to reduce the gas turbine 2 vibrations pressure and accelerations vibrate. And is more special, and a measuring sum of the tension frequency of the pressure and a vibration of the combustion with a frequency tension member 12 pairs. Therefore, is used for adjusting flow of refrigerant calibrating data made of a split air flow back part 24 determinations, and outputs a split air flow console section 7, wherein the nozzle is pressed the pressure vibration discharge device.

And is more special, the combustion vibration of the gas turbine section and 3 pairs of gas turbines 2) is provided with a measuring, and according to measured of the combustion vibration the frequency, specifically according to the circumference of the second embodiments, a split type air flow, appropriately controlling the gas turbine movements 2, wherein in the combustion type vibrate.

Now 4, the part or a describe.

The gas turbine (2) is the same as the gas turbine of the first embodiments described, therefore here pad is a heatsink further description to a.

On the other side; the gas turbine section and 3 to this values' data, and a control gas turbine (2) in the gas turbine two measuring's pressure, to prevent the combustion vibration discharge device.

Control part (11) symmetrically arranged in the data value of gas turbine 2, obtains to the main oil flow control part 5, pilot-ignition oil flow control unit and 6 inlet guide blade section console 8 control output signals, and a control to claims. Similarly, control part 11 (24 description is as follows) is a which is used for controlling the split air flow console section (7) double-layer signals to the divided-flow air flow back part, and auxiliary split air flow back part 24 control split air flow console 7 sections. The main oil flow control part 5, pilot-ignition oil flow control component (6) and inlet guide blade section console 8 typical situations controls the control through the oil inlet method, the feedback method or the PID method.

The same frequency tension member 12 operation and a first embodiments, and each combustion chamber results to tension split air flow back part (24) outputs.

Split air flow back part (24) comprises based on the process is a variable frequency tension spring of the pressure and acceleration and obtain, calculates calibrating a data. Automobile, expressed of the back data's signal and is attached with the control part 11 control signals, which is used for controlling the split air flow console section (7), and outputs a back control signal to the divided-flow air flow back part 7. The divided-flow air flow back part (24) may comprise a control part 11.

Calibrating data determining part 25 pressure-based and each hoop variable frequency tension spring, a reference calibrating data plug the table (Figure sees 2 and 3, wherein a circulating with a description) and process value of the control part obtain 11, determines the calibration data for calibrating control split air flow console section 7 control signals. Determined calibrating data output body part 26.

The accumulator (26) of calibrating data is plug the component 25 determined calibrating data to add a control part 11 control signals, which is used for controlling the split air flow console section (7), and is split air flow console section (7 and back control signals, and controlling latter's control signal.

Now, a as to the attached and movement of gas turbine according to the invention gas turbine control device describes.

Here, plug such as the display and back 3 data's thereof is the same as the first embodiments the or 2, therefore no need of the further description here.

Claim pay operating a radiator and 2 or three display the data for controlling each part (main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8) and part (valve) preparation. The second embodiments, a energy the air flow console section (7) is prepared form a.

Hole of the pressure vibration or a vibration data possibly is used for container data of pressure vibration and a vibration device of each of which the section of to or 2 or shown in the 3.

Now, a as to or 4, 2 and 12, explained for controlling the divided-flow air flow through the back of the data determining gas turbine (2) and process.

(1) Radiator (12) is a step) of the front and gas turbine system, a data or 2 or 3 or device according to the upper end. The data wire (storage the pattern is not expressed) is a split air flow back part 24 storing unit.

(2), Then the) of the gas turbine 2 actual performance, the variable-frequency pressure measuring part (9) and a central part 10 measuring each combustion chamber 111-1 is propped against 111-m are the pressure variable-frequency and each combustion chamber of combustion gas 111-1 fixing the speed increasing the 111-m. The metrical data output the frequency tension part of each predetermined time 12. Metrical data of gas turbine section and 3 frequency tension member (12) extending part (Figure the step 12) S1.

(3) The gas turbine section and 3 frequency tension 12 parts end of the frequency tension operation to the metrical data by Fourier a tension, obtains and frequency vibration part is shown and radiator (14) grade relation. Based on, assigns frequency of the preset frequency hoop and the data wire (Figure the step 12) Supply. Automobile, such of a obtain outputs a split air flow back part 24 calibrating data determined 25 parts.

(4) The gas turbine section and 3 calibrating data plug the component 25 pairs 1 propped on the n spring and discharging of each frequency interlayer of the frequency tension member (12) is among the storing is formed, wherein to 2 and shown in the radiator (3) is pattern of display) is storing part corresponding frequency fastening threshold value α compares. Speed and hydraulic motor is longer threshold value α hole, a shift calibrating data 0. The contrary one; and part is longer than the corresponding frequency interlayer (is as follows with a called unusual frequency) and a threshold value α hole, made from the process of values control part 11 output end of the housekeeping functional f, a sensor calibrating data (Figure the step 12) S3. Determined calibrating data output body part 26.

(5) The gas turbine section control chamber 3 and 26 arranged from the control split air flow console section 7 control signals of control part (11) outputs on the corresponding to the back data determining part (25) outputs a signal of calibrating data, a sensor a new control signal, for controlling a split air flow console section (7) of the step 12) S4.

(6) The gas turbine control part (3) and new determined control split air flow console section 7 control signals, which is used for controlling the rear heatsink (12 step 85).

(7) And a split air flow console section (7) comprises a control signals of the regenerative chamber (26) outputs, and one or multiple the sliding valve 118-1 structures are 118-m.

On the out of the movement of gas turbine; for each predetermined time; the step (1) is (7) and a repeatedly.

Similarly, a main oil flow rate and pilot-ignition oil flow and is connected to the control feed-forward, the control valve or the PID control by inlet guide blade introduction the air volume is connected to the control, in order to set and a respective predetermined value.

, Thus according to the invention, flow the air flow and capable of controlling the pressure function of vibration and a vibration of the gas turbine rubber 2, thus the internal pressure vibration and speed and conditioning. The, the invention, a through the frequency a end is a vibration having variable with the analysis, and a heatsink the calibration for measuring each frequency hoop. Therefore, the stability of the operation and power of combustion gas turbine can greatly for.

(Embodiments 3) now, the finger attached on the explained that the invention third embodiments for gas turbines 2 gas turbine control device and comprises a control device of gas turbine system.

Radiator (5) is a schematic diagram, the invention display third embodiments gas turbine control device and gas turbine system structure. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) comprises in the depth measuring part (4), main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8), a variable-frequency measuring part (9) and a central part 10.

On the other side; the gas turbine control section (3) comprises a control part (11), a tension variable parts 12) and an inlet guide vane back part 27. The flow guide vane back part (27) comprises a data calibrating determining part (28) and body part 29.

The invention third embodiments is different from the first and second embodiments is calibrates the data and is coupled to the pilot-ignition oil flow, diverging to the air flow invention, the relative to the inlet guide blade 102). i.e, wherein the control introduction compressor air 101, reducing gas turbine 2 vibrations pressure and accelerations vibrate. And is more special, and a measuring sum of the tension frequency of the pressure and a vibration of the combustion with a frequency tension member 12 pairs. Groove, which is used for controlling inlet guide blade (102) and introduction compressor 101 air flow calibrating data through the flow guide blade back part 27 determinations, and output inlet guide blade section console 8, wherein the nozzle is pressed the pressure vibration discharge device.

And is more special, the combustion vibration of the gas turbine section and 3 pairs of gas turbines 2) is provided with a measuring, and according to measured of the combustion vibration the frequency, specifically according to the circumference of the third embodiments, a split type air flow, appropriately controlling the gas turbine movements 2, wherein in the combustion type vibrate.

Now 5, the part or a describe.

The gas turbine (2) is the same as the gas turbine of the first embodiments described, therefore here pad is a heatsink further description to a.

On the other side; the gas turbine section and 3 to this values' data, and a control gas turbine (2) in the gas turbine two measuring's pressure, to prevent the combustion vibration discharge device.

Control part (11) symmetrically arranged in the data value of gas turbine 2, obtains to the main oil flow control part 5, pilot-ignition oil flow control component (6) and a split air flow console section 7 output signals control. Similarly, control part 11 (27 description is as follows) is a which is used for controlling the inlet guide blade 8 normal signals to the inlet guide vane back part, and auxiliary air inlet vane back part 27 control inlet guide blade console 8 sections. The main oil flow control part 5, pilot-ignition oil flow control component (6) and a split air flow console 7 sections of typical situations controls the control through the oil inlet method, the feedback method or the PID method.

The same frequency tension member 12 operation and a first embodiments, and each combustion chamber results to tension inlet guide vane back part (27) outputs.

Inlet guide vane back part (27) comprises based on the process is a variable frequency tension spring of the pressure and acceleration and obtain, calculates calibrating a data. Automobile, an inlet guide blade back part 27 expressed of the back data's signal and is attached with the control part 11 control signals, which is used for controlling the inlet guide blade section console 8, and outputs a back control signal to the inlet guide blade section console 8. The flow guide vane back part (27) may comprise a control part 11.

Calibrating data determining part 28 pressure-based and each frequency converter is frequency analysis's the spring, a reference calibrating data plug the table (Figure sees 2 and 3, wherein a circulating with a description) and process value of the control part obtain 11, determines the calibration data for calibrating control inlet guide blade section console 8 control signals. Determined calibrating data output body part 29.

The accumulator (29) of calibrating data is plug the component 28 determined calibrating data to add a control part 11 control signals, which is used for controlling the inlet guide blade section console 8, and inlet guide vane adjusting part (8) and a back control signals, and controlling latter's control signal.

Now, a as to the attached and movement of gas turbine according to the invention third embodiments gas turbine control device describes.

Here, plug such as the display and back 3 data's thereof is the same as the first embodiments the or 2, therefore no need of the further description here.

Claim pay operating a radiator and 2 or three display the data for controlling each part (main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8) and part (valve) preparation. The third embodiments, 8 prepared with a formed with the inlet guide blade section console.

Hole of the pressure vibration or a vibration data possibly is used for container data of pressure vibration and a vibration device of each of which the section of to or 2 or shown in the 3.

Now, a as to or 5, 2 and 12, explained for controlling the divided-flow air flow through the back of the data determining gas turbine (2) and process.

(1) Radiator (12) is a step) of the front and gas turbine system, a data or 2 or 3 or device according to the upper end. The data wire (storage the pattern is not expressed) of the flow guide blade back part 27 storing unit.

(2), Then the) of the gas turbine 2 actual performance, the variable-frequency pressure measuring part (9) and a central part 10 measuring each combustion chamber 111-1 is propped against 111-m are the pressure variable-frequency and each combustion chamber of combustion gas 111-1 fixing the speed increasing the 111-m. The metrical data output the frequency tension part of each predetermined time 12. Metrical data of gas turbine section and 3 frequency tension member (12) extending part (Figure the step 12) S1.

(3) The gas turbine section and 3 frequency tension 12 parts end of the frequency tension operation to the metrical data by Fourier a tension, obtains and frequency vibration part is shown and radiator (14) grade relation. Based on, assigns frequency of the preset frequency hoop and the data wire (Figure the step 12) Supply. Automobile, such of a obtain output the flow guide blade back part 27 calibrating data determined 28 parts.

(4) The gas turbine section and 3 calibrating data plug the component 28 pairs 1 propped on the n spring and discharging of each frequency interlayer of the frequency tension member (12) is among the storing is formed, wherein to 2 and shown in the radiator (3) is pattern of display) is storing part corresponding frequency fastening threshold value α compares. Speed and hydraulic motor is longer threshold value α hole, a shift calibrating data 0. The contrary one; and part is longer than the corresponding frequency interlayer (is as follows with a called unusual frequency) and a threshold value α hole, made from the process of values control part 11 output end of the housekeeping functional f, determining calibrating data (Figure the step 12) S3. Determined calibrating data output body part 29.

(5) The gas turbine section control chamber 3 and 29 arranged from the inlet control guide blade section console 8 control signals of control part (11) outputs on the corresponding to the back data determining part (28) outputs a signal of calibrating data, a sensor a new control signal, for controlling inlet guide blade console section (8) of the step 12) S4.

(6) The gas turbine control part (3) and new determined control inlet guide blade section console 8 control signals, which is used for controlling the rear (12) or the S5).

(7) When inlet guide blade section console 8 to gas turbine 2 movements from the control signals of the accumulator output 29); the inlet guide blade.

On the out of the movement of gas turbine; for each predetermined time; the step (1) is (7) and a repeatedly.

The main oil flow rate and pilot-ignition oil flow and is connected to the control feed-forward, the control valve or the PID control by inlet guide blade introduction the air volume is connected to the control, for setting device capable of the preset value.

, Thus according to the invention, flow the air flow and capable of controlling the pressure function of vibration and a vibration of the gas turbine rubber 2, thus the internal pressure vibration and speed and conditioning. The, the invention, a through the frequency a end is a vibration having variable with the analysis, and a heatsink the calibration for measuring each frequency hoop. Therefore, the stability of the operation and power of combustion gas turbine can greatly for.

(Embodiments 4) now, the finger attached on the explained that the invention fourth embodiments of the gas turbine 2 gas turbine control device and comprises a control device of gas turbine system.

Radiator (6) is a schematic diagram, the invention display fourth embodiments gas turbine control device and gas turbine system structure. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) comprises in the depth measuring part (4), main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8), a variable-frequency measuring part (9) and a central part 10.

On the other side; the gas turbine control part (3) comprises a control part 11, frequency tension member 12 and 15 databases and calibrates part is 30, the three back part (30) comprises a data calibrating determining part (31) and accumulator (23, 26, 29 and 32, and a back function.

The invention fourth embodiments with a first different to the third embodiments is calibrates the data, a energy the air flow and a guide blade to the main oil flow rate and pilot-ignition oil flow 102, as to reduce the gas turbine 2 vibrations pressure and accelerations vibrate.

The fourth embodiments; and second gas turbine split air flow and relation with a guide blade (102) of the air flows from the second air flow compose device the data according to the second fuel flow rate of the vibration intensity and other gas turbine 2 main oil flow rate and pilot-ignition oil flow by. Automobile, the gas turbine (2) of status's vibration data of the data with presently and compares, a flow sensor and gas turbine of 2 statuses. , Thus flow base and a second flow the back are determined according hole, calibrates the data is calibrated. The embodiments and front end of different first on the aspects to the third embodiments.

The, the combustion vibration of the gas turbine section and 3 pairs of gas turbines 2) is provided with a measuring. Automobile, the frequency characteristics of gas turbine section and 3 to combustion vibrations, specifically formed according to the oscillatory speed, a gearbox main oil flow rate and pilot-ignition oil flow of a split air flow inlet and air vane's opening); the gas turbine 2 movements. The other, the gas turbine control part (3) through the calibration gas turbine along with the timing exchange; the combustion type and.

Now 6, the part or a describe.

The gas turbine (2) is the same as the gas turbine of the first embodiments described, therefore here pad is a heatsink further description to a.

On the other side; the gas turbine section and 3 to this values' data, and speed of the gas turbine two measuring's pressure control; the gas turbine, 2 to prevent the combustion vibration discharge device.

Control part (11) symmetrically arranged in the data value of gas turbine 2, obtains to the calibrates part (30) outputs for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section is 7) and a guide blade section console 8 control signals. Automobile, control section (11 calibrate auxiliary the component 30 main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section is 7) and a guide blade section console 8.

Same as the frequency tension member 12 operation and a first embodiments, calibrate to the part (30) outputs and each combustion chamber results tension full.

The fourth implementation example's of 15 to a intervening the movement relative data, energy, the air current and other gas turbine 2 inlet guide blade (102) and air current with a vibration intensity and a main oil flow rate and pilot-ignition oil flow from. The data for screwing to 15 to describe.

Reference pattern 15, wherein the frequency a fixing 1) in n and reference pattern or 2 or 3) of description. The control signal x expressed and second fuel flow rate pilot-ignition oil flow flow and a main oil flow plate and second air inlet flow guide blade (102) and air flow and a split air flow. Therefore, the listed four fuels and air data (main fuel, pilot-ignition oil flow, and air inlet guide blade of 102) and display the radiator is 15 to form. The or 15, wherein flow with a1 and a2, so, AL each row of display or fuel gas flow range. A example, 0<a1<5nm3/min, 5<a2<10nm3/min, so, 45<al<50nm3/min. And the hydraulic vibration using the new frequency fastening results tension rubber is when the gas turbine according to heating and required is sunk the steady flow measurer band type hoop frequency vibration intensity. A example, when the gas turbine with the a2 and a flow, the frequency a vibration 2 intensities is A22. The hydraulic vibration with the specific value.

Radiator (15) are symmetrically distributed on the gas turbine (2) is features, and data and data preparations. The fixed are three part of values, a blade and four different fuels of air and a of a flow rate, a obtain the mediate data. The flat preferably, the other types of multiple groups of fixtures are multiple, therefore the work statuses possibly and an of the combining.

The complete back part (30) comprises based on the process is a variable frequency tension spring for pressure and acceleration and obtain, calculates calibrating a data. Automobile, the three back part 30 expressed of the back data's signal and is attached with the control part 11 control signals, which is used for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8, and outputs a back control signal connected to the component. The complete back part (30) may comprise a control part 11.

The calibration data plug the part (31) based on each of pressure and a frequency of the frequency tension spring the frequency tension member obtain 12, and comprises a database 15 or four of oil gas and vibration data intensity, applying the current gas turbine 2 statuses of the novel gas turbine 2. The other words, calibrates the data to determine of the component 31 searches section of the work operation or data. Automobile, calibrates the data determining part 31 and 2 or 3) in the display and such as to the probe spring determined novel gas turbine 2 calibrating data determined are determined, main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8 calibrating data. The determined calibrating data output the body part respectively 23, 26, 29 and 32.

The accumulator (23, 26, 29 and 32 of the calibration data determining part 31 determined type each calibrating data's signals, a to add a control part 11 control signals, which is used for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7) and a guide blade section console 8, and outputs each calibrating control signal and control signal connected to the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8.

Now, a as to brief description of the invention drawings gas turbine control device and operation of gas turbine system.

Here, plug such as a display or 2 and 3 calibrating data method, and is used in the gas turbine 2, wherein the same as the first embodiments, therefore no need of the further description here. Claim understand of the method is used to implement the example 1 novel gas turbine.

Claim pay operating a radiator and 2 or three display the data for controlling each part (main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8) and part (valve) preparation. The embodiments, for the part of the preparation.

Hole of the pressure vibration or a vibration data, possibly is used for container data of pressure vibration and a vibration device of each of which the section of to or 2 or shown in the 3.

Now, a as to or 6, 2, 12 and 15, explained of the connected part of calibrating data determining of gas turbine movement 2); the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade console section (8).

(1) Radiator (12) is a step) of the front and gas turbine system, a data of the or 2 or 3 and 15 or device according to the upper end. Of calibrating the component 30 storing element (a pattern is of express) is a new gas turbine 2 preparation's data storages full.

(2), Then the) of the gas turbine 2 actual performance, the variable-frequency pressure measuring part (9) and a central part 10 measuring each combustion chamber 111-1 is propped against 111-m are the pressure variable-frequency and each combustion chamber of combustion gas 111-1 fixing the speed increasing the 111-m. The metrical data output the frequency tension part of each predetermined time 12. Metrical data of gas turbine section and 3 frequency tension member (12) extending part (Figure the step 12) S1.

(3) The gas turbine section and 3 frequency tension 12 parts end of the frequency tension operation to the metrical data by Fourier a tension, obtains and frequency vibration part is shown and radiator (14) grade relation. Based on, assigns frequency of the preset frequency hoop and the data wire (Figure the step 12) Supply. Automobile, such of a obtain output the calibration data determined part 31.

(4) The gas turbine section and 3 calibrating data plug the component 31 pairs 1 propped on the n spring and display part of each frequency interlayer of the frequency tension member (12) is obtained data (, energy of data with a frequency and a main oil flow rate and pilot-ignition oil flow of the air 15) and a guide blade 102 gas flow amount relate belt, and storing of the vibration 15, intensities with or movement relative data) and compares. Automobile, calibrates the data to determine of the component 31 discover the operation state (or four of oil and gas rates flow), the frequency vibration a intensity and operation bijection data of each other satisfied the intercoordination. A typical flat, the satisfying intercoordination the flat is a hydraulic vibration differential value of ±10%.

Afterward, the operation state (or four of oil and gas rates flow) and () and a running status of gas turbine 2 four different of fuel and air flow compare) and calculate the differential value. Speed difference (e.g. ±2%) is preset with permission hole, does not controls the calibration.

The shell, calibrates the data to determine of the component 31) for vibrate intensity and storing the storing part (of pattern is not expressed frequency) is leaned 1 n at each threshold value is compare. Speed and hydraulic motor is longer threshold value α hole, a shift calibrating data 0,On the other side, if the vibrated part is longer threshold value α hole, made from the process of values control part 11 output (. e.g generator, the output power and temperature and humidity and each component is surrounded fuel gas flow rate and pressure and each component air flow and pressure, and temperature of each chamber of combustion gas's flow and pressure and interval/unit unit comprises a rotating number of the secondary of compressor and turbine, waited) and a housekeeping the functional f, a sensor calibrating data (Figure the step 12) S3. Determined calibrating data output accumulator (23, 26, 29 and 32.

On the other side, if any differential value of four different of fuel and air relative is set to permit the range (e.g. ±2%); and air flow to the fuel is arranged on the back of the flow differential value's base. The calibration data and back data plug the component 31 storing element (a pattern is not expressed), capable of the control afterward operation. Similarly, wherein the calibration data output the control part (11), and aim of using.

Afterward in, when flow is not surpassed for the range similarly, therefore no need of the further description here.

The calibration data or 2 or 3 or rubber symmetrically arranged in the value of each frequency a fixing 1) in n are determined. Therefore, the fuel and air flow rate value differential on the back data the differential value. And a spring of the flange, impossible to vibrating end is a precisely. However, the upper back operation, a determine the calibration data precisely, which if the production of differential value of the different flange, comprising a resetting along with the timing exchange.

(5) The gas turbine section and 3 parts claim 23, 26, 29 and 32 arranged from the main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section of the control part (11) outputs 7, and inlet guide blade section console 8 control signals, which to corresponding to each of calibrating data signals of calibrating data determining part (31) outputs, a sensor the new control signal, to the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console sections 7, 8 end of the control with the inlet guide blade console section (Figure the step 12) S4.

(6) The gas turbine control part (3) and new determined main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8 control signals, is adapted to the control.

(7) And a main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8, according to of the accumulator (23, 26, 29 and control signals of output 32, wherein the control the main oil supplying valve 115-1 structures are 115-m or the main oil flow control valve are 113, wherein the one or more pilot-ignition fuel supplying valve 116-1 structures are 116-m or the pilot-ignition oil flow control valve (114), the sliding valve 118-1 at input and 118-m inlet guide blade 102.

On the out of the movement of gas turbine; for each predetermined time; the step (1) is (7) and a repeatedly.

According to the invention, the main oil supplying valve 115-1 structures are 115-m and a main oil flow control valve, 113 pilot-ignition oil supplying valve 116-1 is propped at 116-m and pilot-ignition oil flow control valve, 114 sliding valve 118-1 is propped at 118-m and a guide blade 102 air flow control, a end of the control according to the gas turbine (2 vibrations and a vibrations, the face of the pressure vibration and a superiorly and. The, a through the frequency and end is a vibration having variable with the analysis, and a heatsink the calibration for measuring each frequency hoop. Therefore, the stability of the operation and power of combustion gas turbine can greatly for.

Moreover, pipe are several on the fuel and an actual flow along with primary variable-frequency with a ring-shape with inconsistent, the differential value of the section (11 confirmed is capable of the database a data to calibrate automatic. Therefore, a combustion by fixing said for a long time.

(Embodiments 5) now, the finger attached radiator, a explain the invention embodiments for gas turbines 2 gas turbine control device and comprises a control device of gas turbine system.

Radiator (7) is a schematic diagram, the invention display fifth embodiments gas turbine control device and gas turbine system structure. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) comprises in the depth measuring part (4), main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8), a variable-frequency measuring part (9) and a central part 10.

On the other side; the gas turbine control part (3) comprises a control part 11, frequency tension member (12) and a to try to a movable determining part (16) and a back data to determine of the component (31) and calibrates part is 33, the three back part (33) comprises the accumulator (23, 26, 29 and 32, and a back function.

The embodiments of the invention with a first different to the third embodiments is calibrates the data, a energy the air flow and a guide blade to the main oil flow rate and pilot-ignition oil flow 102, as to reduce the gas turbine 2 vibrations pressure and accelerations vibrate.

, And the embodiments of the invention with a first different to the third embodiments is running status the part of the gas turbine (2) in operation is gradually variable, thus determined with the vibration intensity and adjusting the relationship of the work state, then, and multiple operation state of the changed results; and determined priority shipment parallel, and lower of the vibration part is quadrilateral.

The other words, the gas turbine control part 3) in which the combustion of the gas turbine (2) and a. Automobile, the embodiments, according to the frequency of the combustion vibration, the gas turbine 2 movements is controlled appropriately. A example, a main oil flow rate and pilot-ignition oil flow of a split air flow inlet and air vane's, condition of product according to the vibration heat exchange. For automatically scan the combustion vibration minimum operation state. Therefore, capable is pressed to the combustion vibration.

Now 7, the part or a describe.

The gas turbine (2) is the same as the gas turbine of the first embodiments described, therefore here pad is a heatsink further description to a.

On the other side; the gas turbine section and 3 to this values' data, and a control gas turbine (2) in the gas turbine two measuring's pressure, to prevent the combustion vibration discharge device.

Control part (11) symmetrically arranged in the data value of gas turbine 2, obtains to the calibrates part (33) is as follows description output) for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section is 7) and a guide blade section console 8 control signals, calibrates the component 33 main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section auxiliary full 7) and a guide blade section console 8.

Same as the frequency tension member 12 operation and a first embodiments, calibrate to the part (30) outputs and each combustion chamber results tension full.

The embodiments testing plug for determining part 16); and lower onward and parallel with the gas turbine (2) of statuses, a example, a main oil supplying valve 115-1 structures are 115-m and a main oil flow control valve, 113 pilot-ignition oil supplying valve 116-1 is propped at 116-m and pilot-ignition oil flow control valve, 114 sliding valve 118-1 is propped at the 118-m opening angle and a guide blade 102 degrees, to find to minimize the hydraulic vibration the work state, the performing the gas turbine 2 movements testing, and determines the operation state. Is as follows a describe the variable determining, and actuator operation state.

The or 8, wherein the horizontal shaft expressed of the sliding valve 118-1 propped at the 118-m opening; and vertical shaft expressed of the pilot-ignition fuel supplying valve 116-1 propped at the opening 116-m. The operation state when the gas turbine 2 to eight mm x when the movable expressed that and then of the operation state of △ expressed (four points) is connected to try to move. The onward movement of said and try the operation state the differential value is limited is less than of each parameter preset depth (. e.g, flow) ±2%. Tries to the movable determining part 16 to determine of each parameter the difference (e.g., namely flow, ±0.01Nm3/min), and output determined differential value to the back data determined part 31.

The complete back part (33) comprises based on the process is a variable frequency tension spring for pressure and acceleration and obtain, calculates calibrating a data. Automobile, the back data's signal and is attached with the control part 11 control signals, which is used for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8, and outputs a back control signal to the component. The complete back part (33) may comprise a control part 11.

The calibration data plug the component 31 determinations capable of testing to the movable determining the differential 16 values the calibration data, and outputs the accumulator (23, 26, 29 and 32. On the out of the embodiments, based on coming from frequency tension member 12 frequency tension results the gearbox of operation state is a temporary plate. The variable tension member (12) with a description of the preceding text, a as to the first to the third embodiments.

The accumulator (23, 26, 29 and 32 of the calibration data is plug the component 31 determined type each calibrating data the signals to add a control part (11) is used for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7) and inlet guide blade section console 8 control signals, and outputs each calibrating control signal and control signal to the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8.

Now, a as to brief description of the invention drawings the gas turbine control device and operation of gas turbine system.

(1) The gas turbine of the embodiments 2 to 8 of the lower x from the centre of expressed with a first to the third embodiments same and heatsink (16 is characterized).

(2), Then tries is flexibly the determined part 16 charts determining 8) and x of the position and displacement of expressed by running status of △ expressed (calls tries to move) and. Automobile, tries to a movable determined part 16 testing to push and each and between the onward movement of the differential value, namely, sliding valve (118) and pilot-ignition oil supply 116 valve guide opening and they the testing to move openings the differential value, the output calibrating data determining part (31 or 16 S11 the).

(3) And the back data plug the part (31) for internal try from small to the determined part 16 statuses of the differential values to be the calibration data, and finally fixed to the radiator (16 S12 the). Last determined calibrating data output the body part respectively 23, 26, 29 and 32.

(4) The gas turbine section and 3 parts claim 23, 26, 29 and 32 arranged from the main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section of the control part (11) outputs 7, and inlet guide blade section console 8 control signals, which to corresponding to each of calibrating data signals of calibrating data determining part (31) outputs, a sensor the new control signal, to the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console sections 7, 8 end of the control with the inlet guide blade console section (Figure the step 16) S13.

(5) The gas turbine control part (3) and new determined main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8 control signals, which is used for controlling the radiator (16 S14 the).

(6) And a main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8 to control signals, an operation the main oil supplying valve 115-1 structures are 115-m or the main oil flow control valve are 113, wherein the one or more pilot-ignition fuel supplying valve 116-1 structures are 116-m or the pilot-ignition oil flow control valve (114), the sliding valve 118-1 at input and 118-m inlet guide blade 102.

And operation spring; the gas turbine (2) of statuses of the lower adjusting, replaceable vibration intensity. The pressure variable-frequency part (9) and a central part 10 measuring each combustion chamber 111-1 structures are 111-m the pressure variable-frequency of the combustion gas respectively, 111-1 fixing the speed increasing the 111-m to change on each combustion chamber. Output such a gas turbine section and 3 frequency tension member (12) extending part (Figure the step 16) S15.

(7) The gas turbine section and 3 frequency tension 12 parts of the Fourier a tension end of the frequency tension operation to the metrical data typically, obtains to 14 or a display and frequency vibration part (grade) relation. Based on, assigns frequency of the preset frequency hoop and the data wire (Figure the step 16) S16. Automobile, such of a obtain outputs to try to a movable determined part 16.

(8) Around the testing movement of designation; the step (1) is (7) relapse performing (Figure the step 16) S17.

(9) Of each tries and length and frequency to tension part, tries is flexibly the determined part 16 determining the priority shipment harness.

The following for screwing to 9 pair of the priority shipment rod of the determined corresponding to describe.

The or 9, wherein the horizontal shaft expressed of the sliding valve 118-1 propped at the 118-m opening; and vertical shaft for expressed and vibration part of the frequency tension spring rubber. The or 9, x expressed front end of any tries to a vibration part of the gas turbine 2 initial work state, △ indicated according to tries movable the operation state each vibration intensity. Connecting △ the curve respectively represents based on at △ and x metrical data forecast surface. A optimum position according o expressed according 118-1 piece at 118-m the opening position of range of variable-frequency to determine from the branching valve; and a limit surface to try is flexibly the spring determining of said work statuses and heatsink (9 or 16) S18.

Last, running status rubber the back, a section to the priority shipment line of determining.

Thus, the testing is movably, the gas turbine control device found to minimize the vibration the operation state. Therefore, the driving the gas turbine mobile is pressed the vibration and stable conbustion, between the service life of gas turbine, reduces the maintenance cost.

Speed and a spring of along with the variable-frequency timing fuel, and an actual flow confirmed with control part (11) is ring-shape with inconsistent hole, the testing element capable of the priority shipment line to improve the work state, thus of the affected primary reducing to is quadrilateral.

(Embodiments 6) now, the finger attached radiator, a explain the invention sixth embodiments with gas turbine gas turbine remote monitoring system.

Radiator (10) is a diagram, a display invention the embodiments gas turbine remote monitoring system structure. Gas turbine remote monitoring system comprises a gas turbine system (1) and a remote monitoring part 20. The gas turbine 1 system comprises a gas turbine 2) and invention gas turbine control device of gas turbine section and 3.

The gas turbine (2) comprises in the depth measuring part (4), main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8), a variable-frequency measuring part (9) and a central part 10.

On the other side; the gas turbine control section (3) comprises a control part 11, frequency tension part (12) and a corresponding part 17.

The remote monitoring part (20) comprises a database 35) and a to calibrate the lower part (34) and a corresponding part 18. The, the three back part 30 determining calibrating data's first etched function, applying of calibrating the lower part is 34. According to the determined calibrating data and control signal control gas turbine 2 second etched functions, wherein the control part is 11. However, wherein the functional is 21 of generally to the first embodiments back part.

The embodiments of the invention with the first to the fourth embodiments difference, the remote monitoring part (20) for gas turbine 2 vibrations pressure and accelerations vibrate. And is more special, the remote monitoring part 20 to 3 obtain the gas turbine 2 vibration data from the gas turbine control part of the communication cable. Vibration data and storing of the three back part references 34 received in a of the data 35, determined main oil flow rate and pilot-ignition oil flow of a split air flow and a guide blade 102 control signals calibrating data. Automobile, a corresponding alignment gas turbine control part (3 orders, a vibrating and is pressed.

And is more special, the remote monitoring part (20) connected with the gas turbine control part corresponding 3, recognize of the combustion of the gas turbine (2) is vibration discharge device. Automobile, the remote monitoring part 20 to vibrations' combustion frequency tension results; the signals of the transmission control gas turbine 2, and are formed to the vibration control main oil flow rate and pilot-ignition oil flow of a split air flow inlet and air vane's opening.

10 Now the part or a describe.

The gas turbine (2) is the same as the gas turbine of the first embodiments described, therefore here pad is a heatsink further description to a.

On the other side; the gas turbine section and 3 to this values' data, and a control gas turbine (2) in the gas turbine two measuring's pressure, to prevent the combustion vibration discharge device.

Control part is 11 to 17) to the remote monitoring part (20) in transmission values (aspect type data), and a corresponding part 17) on the remote monitoring part 20 control signals. The control part (11) with accumulator the fourth embodiments 23, 26, 29 and 32, a coming from the general control signals of remote monitoring part (20) and control signal and corresponding end of the curved to increase or lower. Automobile, the control part (11) and main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8) as control signals, which is used for using the control suitable to claims.

Frequency tension member 12 to the first embodiments the end of the operation 12, 17 the results a tension and remote monitoring part of the corresponding part and frequency tension member 20. Therefore, here do not describe.

Corresponding part (17) and gas turbine section and 3 control part 11 sum of the frequency tension member 12 ring. The corresponding part 17) via the communication cable and remote monitoring part 20 ring, a communication wire is a circular ring and/or the lead wire.

The remote monitoring part (20) connected with the gas turbine control part 3, which is on the monitoring to the combustion vibration of the gas turbine (2) with. Automobile, a signal and of the combustion type remote monitoring part 20 vibration-based transmission the frequency the rubber and control gas turbine according and a. The remote monitoring part (20) is not need is made of a gas turbine specially 2. The remote monitoring part (20) capable of multiple gas turbines, for monitoring operation efficiency.

The part of the embodiments 35) is a remote of actually; a fourth embodiments of 15), therefore no need of the further description.

The complete back part (34) is formed with a fourth embodiments same mode, the process is comprises a pressure or each hoop variable frequency tension spring, obtains and comprises a database 35 four part of the vibration intensities of fuel and air, a calculating calibrating data. Automobile, the three back part (34) through a corresponding part 18 calibrating the data output the gas turbine control part (3); the data is used for controlling the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7) and a guide blade section console 8. The complete back part (34) comprises a fourth embodiments to calibrate the data determining part 31 functions.

Now, the finger attached radiator and gas turbine to the invention the gas turbine control device systematically describes.

Here determines, such as and 2 or three display data method of the radiator and fourth embodiments the same, therefore no need of the further description.

Claim pay operating a radiator and 2 or three display the data for controlling each part (main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade section console 8) and part (valve) preparation. The embodiments, for the part of the preparation.

Hole of the pressure vibration or a vibration data possibly is used for container data device according to the or 2 or shown in or 3, or a data of pressure vibration and a vibration can be used for container data device for or 2 or shown in the 3.

Now, a as to or 10, 2 and 15, explained of the connected part of calibrating data determining of gas turbine movement 2); the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), an inlet guide blade console section (8).

(1) The front and gas turbine system, a data of the or 2 or 3 and 15 or device according to the upper end. Of calibrating the component 34 storing element (a pattern is of express) is a new gas turbine 2 preparation's data storages full.

(2), Then the) of the gas turbine 2 actual performance, the variable-frequency pressure measuring part (9) and a central part 10 measuring each combustion chamber 111-1 is propped against 111-m are the pressure variable-frequency and each combustion chamber of combustion gas 111-1 fixing the speed increasing the 111-m. The metrical data output the frequency tension part of each predetermined time 12. Data output of a gas turbine section and 3 frequency tension member 12) on.

(3) The gas turbine section and 3 frequency tension 12 parts end of the frequency tension operation to the metrical data by Fourier a tension, obtains and frequency vibration part is shown and radiator (14) grade relation. Based on the assigns, a data the preset frequency hoop. The spring is rubber 17) and is wire output the remote monitoring part is corresponding part 20.

(4) And a remote monitoring part 20 three back part 34 to 1) for propped on the n spring and display part of each frequency interlayer of the frequency tension member (12) is obtained, a data, flow the air flow and a guide blade 102 rates flow and storings with a frequency from a data and a main oil flow rate and pilot-ignition oil flow of the radiator (15) in of the vibration 35 intensities, or compared with the movement relative data. Automobile, the three back part 34 discover the operation state of four different of fuel and air rates flow, the frequency vibration a intensity and movement relative data of each other satisfied the intercoordination. A typical flat, the satisfying intercoordination the flat is a hydraulic vibration differential value of ±10%.

Afterward, the operation state (or four of oil and gas rates flow) compare with four different fuels of the air flow of gas turbine 2 actual driving element, and calculates the differential value. Speed difference (e.g. ±2%) and a predetermined permission range, then no need of the concrete measuring. The shell, the three back part 34) for vibrate intensity and or 2 or 3 or a data the frequency hoop (1) is propped at the n threshold value is compare; and if the intensity of more than threshold value, calibrates the data access 0.

On the other side, if the vibrated part is longer than a threshold value hole, made from the process of values control part 11 output (. e.g generator, the output power and temperature and humidity and each component is surrounded fuel gas flow rate and pressure and each component air flow and pressure, and temperature of each chamber of combustion gas's flow and pressure and interval/unit unit comprises a rotating number of the secondary of compressor and turbine, waited) and a housekeeping the functional f, a sensor calibrating data. Determined calibrating data and 18 communication wire output the gas turbine section and a corresponding part 3.

On the other side, if four different of fuel and air values longer is set to permit the range (e.g. ±2%); and air flow to the fuel is arranged on the back of the flow differential value's base. The calibration data storage of calibrating the component 34 storing element (a pattern is of express), a capable of the control afterward operation. Similarly, wherein the calibration data output the control part (11), and aim of using.

Afterward in, when flow is not surpassed for the range similarly, therefore no need of the further description here.

The calibration data or 2 or 3 or rubber symmetrically arranged in the value of each frequency a fixing 1) in n are determined. Therefore, the fuel and air flow rate value differential on the back data the differential value. And a spring of the flange, impossible to vibrating end is a precisely. However, the upper back operation, a determine the calibration data precisely, which if the production of differential value of the different flange, comprising a resetting along with the timing exchange.

(5) The gas turbine section and 3 and 11 sections arranged from the main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section of the control part (11) outputs 7, and inlet guide blade section console 8 control signals, which the corresponds to the calibrates the part (34) outputs each calibrating data signal, a sensor the new control signal, to the main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console sections 7, 8 end of the control with the inlet switch console blade section and.

(6) The gas turbine control part (3) and new determined main control oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8 control signals, is adapted to the control.

(7) And a main oil flow control part 5, pilot-ignition oil flow control part (6), a split air flow console section (7), a inlet guide blade section console 8, according to a control signals of control part output 11, wherein the control the main oil supplying valve 115-1 structures are 115-m or the main oil flow control valve are 113, wherein the one or more pilot-ignition fuel supplying valve 116-1 structures are 116-m or the pilot-ignition oil flow control valve (114), the sliding valve 118-1 at input and 118-m inlet guide blade 102.

On the out of the movement of gas turbine; for each predetermined time; the step (1) is (7) and a repeatedly.

Thus, the contingency of the remote monitoring part of the invention 20 of the remote monitoring gas turbine 2 movements, and control processing gas turbine 2, comprising to the combustion and. The remote monitoring can not need is made of a gas turbine part in. The usual multiple gas turbines share a remote monitoring part, centralized screen each gas turbine, which is equipped on the control to any one. Therefore, multiple factories' control system capable of controlling has multiple easily, back to the operation efficiency monitoring and reducing the overhead charging.

According to the invention, a according to the gas turbine, when the onward movement of said variable wherein running status. The, face of the combustion of the gas turbine with vibration discharge device, the combustion stability. Automobile, reliability of gas turbine for improving, the premier cost of reducing drastically.