Untitled record

full description

invention background

The invention relates in general to electrical power systems, which include capacity generation for a gas turbine, and more specifically for energy storage, as it is useful to provide additional electrical energy during periods of peak electrical power demand and to provide systems where the gas turbine and steam turbine maintain

<p>5 hot and in the operating position, which leads to a reduction in the start-up time.</p>

The current marginal energy is mainly produced by a gas turbine, either in simple cycle or combined cycle configurations. As a result of the load demand profile curve, gas turbine base systems turn on during high demand periods or shut off during low demand periods

<p>10 demand. This cycle is typically derived by the Grid operator under a program called active grid control (AGC). Unfortunately, because industrial gas turbines, which account for most of the installed base, are primarily designed for base load operation, when rotated, severe penalty comes with the maintenance cost for those</p>

<p>15th special unit. For example, a gas turbine powering the base load could move through normal maintenance once every three years, or 24,000 hours at a cost in the $2–3 million range. And that same cost incurred in one year for a plant that is paid to start up and shut down every day.</p>

These gas turbine units can currently shut down to approximately 50% of their rated capacity. It does this by closing the inlet guide vanes of the compressor, which

<p>20 Reduces the air flow to the gas turbine, also pushes the fuel flow down where the fuel ratio is constant</p>

٦١٩٦

-٣-

A constant fuel air ratio is required in the combustion process. Maintaining safe compressor operation and emissions typically limits the level of shutdown that can be achievable. The minimum safe operation of the compressor in current gas turbines is improved by introducing warm air.

<p>5 air to the gas turbine inlet, typically from mid stage bleed extraction from the compressor. Sometimes, warm air is also introduced into the inlet to reduce icing. In both cases, when this is done, work done to air by the compressor is eliminated in the process for the benefit of its ability to operate the compressor safely to lower flow, resulting in increased turn down capability. This has a negative effect</p>

<p>10 Adding to the efficiency of the system as the work done is lost to the air that is leaked out. In addition, the combustion system also shows a limit to the system.</p>

15

20

The combustion system often limits the amount that the system can shut down because less fuel is added, the temperature of the flame decreases, which increases the amount of carbon monoxide emissions that are produced. The relationship between flame temperature and carbon monoxide emissions is logarithmic exponential with decreasing temperature, therefore, whenever a gas turbine system gets close to the limit, carbon dioxide emissions rise dramatically, so the limit is maintained healthy margin from this point. This characteristic of all gas turbine systems limits it to approximately 50% turn-down capability, or, for a 100 MW gas turbine, the minimum achievable power is approximately 50%, or 50 MW. As the mass flow of the gas turbine is shut off, the efficiency of the compressor and the turbine also decreases, causing an increase in the heat rate of the machine. Some operators are faced with this situation every day and as a result, the loading demand drops, the gas turbine units hit their minimum operating limits and the machines have to be shut down which incurs a huge maintenance cost error.

Another characteristic of a typical gas turbine is that the higher the ambient temperature

<p>25 temperature, the power output decreases proportionally due to the linear effect of density</p>

٦١٩٦

5

-٤-

Reduced as the air temperature increases. The power output can be reduced by more than 10% of the feature plate during hot days, typically when the peak gas turbine need is called in.

Most of the time to deliver power.

Another distinguishing feature of a typical gas turbine is that air is delivered by piping that is compressed and heated in the compressor section of the gas turbine to the various parts of the turbine section of the gas turbine where it is used to cool the various components. This air is typically called turbine cooling and air leakage (TCLA) a term where it is well known in

field view of gas turbines. Despite heating from the compression 10 process, TCLA air is still significantly cooler than turbine temperatures, and is thus effective in cooling these components in a post-compressor turbine. Typically it exceeds 10% to 15% of the air that comes from the inlet of the inlet compressor inlet and is used for this process. Thus, turbine air cooling and leakage are an obvious fault in the performance of the gas turbine system.

15th Another distinguishing characteristic of gas turbines is that they typically take 20-30 minutes to start up due to heat loading considerations and a heat recovery steam generator

generator (HRSG) when a combined cycle plant can take an hour or more. This is clear because the combined cycle plants are used periodically to balance renewable energy, which fluctuates clearly in minutes.

20 General description of the invention

The present invention provides multiple options, based on specific plant needs, to optimize the maximum power output of a gas turbine, increasing the capacity and regulation capability of a new or existing gas turbine system.

٦١٩٦

-٥-

A feature of the present invention relates to methods and systems that allow gas turbine systems to more efficiently provide maximum additional power during peak demand periods because a separately fueled engine is used to drive the system, which eliminates significant parasitic loads parasitic loads

5 Typically associated with compressed air injection systems.

Another feature of the present invention relates to the exhaust recirculation system, which disposes of the point source of emissions from the separated fuel engine.

Another feature of the present invention relates to efficiency improvements using waste heat associated with an exhaust gas recirculation system.

.recirculation system 10

Another feature of the present invention relates to a fueled inlet chiller system where the waste heat from the separated fuel engine increases the power output of a steam turbine and thus maintains or improves the efficiency of the combined cycle plant.

Another feature of the present invention relates to the alternate use of a power system

15th boost system While the power plant is not operating, compressed air is pushed through the gas turbine and exhaust from the separated-fuel engine is pushed through the "heat recovery steam generator" (HRSG) to keep the gas turbine and the entire steam turbine hot as Reduces startup time.

Another feature of the present invention relates to the alternative use of a power-boosting system while the power unit 20 does not operate in which compressed air is pushed through a gas turbine and a heat recovery steam generator to maintain a turbine.

The gas and steam turbine is fully heated which reduces start-up time.

Another feature of the present invention relates to an air injection system to enhance the capacity that displaces cooling air naturally obtained from a gas turbine discharge plenum or compressor mid-stage while at the same time

٦١٩٦

-٦-

Using the exhaust from the separated-fuel engine in a steam generator to recover heat to produce additional power. The cooling air supplied by a substitute can be similar in temperature and pressure to the air it displaces, or cooler (reducing cooling air requirements and GT efficiency).

.) turbine 5

Another feature of the present invention relates to the use of relatively cool first-stage nozzle cooling air, which leads to a reduction in cooling air needs that translates into enhanced efficiency.

Another feature of the present invention relates to a power boost system where it receives coolant relatively hot air and during periods when the combined cycle unit is not operating, it receives hot 10 compressed air to keep the turbine section hot while at the same time the exhaust is used for an engine supply with fuel separately in a packaged boiler to deliver steam through the heat recovery steam generator and steam turbine to bring the start-up time of the “CC” combined cycle unit to the limit the lowest.

15 Another feature of the present invention relates to the use of a separately fueled motor to push hot compressed air into a combustion discharge device.

plenum while at the same time the excess lower quality (i.e. lower temperature) available heat from the exhaust of the fueled engine is used separately for the preheating of the gas turbine fuel, resulting in improved efficiency for the gas turbine.

An embodiment of the invention relates to a system whereby a complementary compressor, at least one compressor, at least one electrical generator, at least one turbine (at least one turbine connected to at least one generator and at least one compressor), and a combustion chamber combustion case (which is the discharge manifold of the compressor).

٦١٩٦

-٧-

Another advantage of another preferred embodiment is the ability to rapidly increase the power output of the gas turbine system with supplemental compressed hot air delivered by the separated fuel engine.

5 Another advantage of the preferred embodiment is the recirculation of some or all of the exhaust gas from the separate fuel engine resulting in a reduction or elimination of emissions from a second source of emissions at the power unit.

Another advantage of the preferred embodiment is to recycle some or all of the exhaust gas from the fuel-separated engine thereby reducing or eliminating the cost associated with scrubbing emissions using the existing gas turbine emission control system.

<p>10 Another advantage of other preferred embodiments is the ability to increase the power output while at the same time improving the efficiency of the entire system.</p>

Another advantage of embodiments of the present invention is the ability to improve the power output and efficiency of a conventional chiller system.

Another advantage of embodiments of the present invention is the ability to maintain the 15 components of the gas turbine and steam turbine while the unit is shut down resulting in reduced start-up time required.

Another advantage of some embodiments of the present invention is the ability to improve the efficiency of the integrated power boost system by reducing heat that would otherwise be lost in association with the GT's cooled cooling air circuits.

<p>20 Another advantage of some embodiments of the present invention is the ability to deliver cooler cooling air to externally supplied turbine components resulting in a reduction in turbine air cooling and leakage required for a gas turbine and improved efficiency of the integrated powertrain.</p>

٦١٩٦

-٨-

Another advantage of some embodiments of the present invention is the ability to deliver cooler cooling air to internally supplied turbine components by preferred drain or direct manifold of cooling air resulting in reduced turbine air cooling and leakage required for the gas turbine and improved efficiency of the gas turbine system Integrated capacity enhancement.

<p>5 Characteristics, features and other characteristics of the invention, as well as the modes of operation and functions of the relevant elements of the structure and combination of parts, will become clearer when the following detailed description and the elements of protection appended with reference to the attached drawings, each of which form part of this description, are considered.</p>

Brief explanation of the drawings

<p>10 Figure 1 shows a schematic drawing of an embodiment of the present invention having a supplemental power system with a recuperated fueled engine, with exhaust gas recirculation, in which the supplemental compressor is driven to where some or all of the engine's exhaust is connected heat recuperated engine's exhaust to the gas turbine for additional combustion.</p>

15

20

Figure 2 shows a schematic diagram of an embodiment of the present invention having a supplementary power system with a heat recovery fuel engine, with exhaust gas recirculation, and fuel heating, with the supplemental compressor being driven where some or all of the recuperated engine's exhaust is connected. To the gas turbine for additional combustion, the additional low quality waste heat is used to heat the gas turbine fuel.

Figure 3 shows a schematic diagram of the embodiment of the current invention, which integrates an inlet cooling system

chiller using a complementary power augmentation chiller to amplify the chilling system

Driven by a separate fuel engine, the exhaust from the separately fueled engine is integrated into the gas turbine exhaust.

٦١٩٦

5

-٩-

Figure 4 shows a schematic diagram of an embodiment of the present invention with a fueled engine exhaust heating system whereby both the compressed air and the fueled engine are used to keep the simple or combined cycle unit warm while it is not running Unit.

Figure 5 shows a schematic diagram of an embodiment of the current invention that incorporates a fast start system using compressed air, in which a mixture of compressed air and compressed exhaust from the fueled engine is used to keep the combined or simple cycle unit warm while the unit is not running.

10

Figure 6 shows a schematic diagram of an embodiment of the current invention supplemented by turbine cool air, whereby cool turbine air is supplied to a high pressure cooling circuit of a gas turbine by a supplementary compressor, and the fueled engine and the fueled engine exhaust are added to the turbine exhaust Gas turbine's exhaust

Figure 7 shows a schematic diagram of an embodiment of the present invention by supplementing cooled cool air to the downstream turbine nozzle.

<p>15th Cool cooling air, by means of the supplementary compressor and the engine supplied with fuel, is transferred to the intermediate pressure cooling circuit, and the exhaust of the engine supplied with fuel is added to the exhaust of the gas turbine.</p>

Figure 8 shows a schematic diagram of the embodiment of the present invention by supplementing the cooled cooling air to the first turbine nozzle, where the cold cooling air is supplied by the supplementary compressor

<p>20 The engine fueled by the cooling circuit of the first stage nozzle of the gas turbine, and the exhaust of the fueled engine is added to the exhaust of the gas turbine.</p>

Figure 9 shows a schematic diagram of an embodiment of the present invention having a fast start with air and steam injection, whereby cold refrigerant air is supplied by the supplemental compressor and the fueled motor to a first-stage nozzle refrigeration circuit, high pressure refrigerant circuit, or pressure refrigerant circuit

٦١٩٦

5

-١٠-

The gas turbine's medium exhaust is used to fuel the steam to produce steam to amplify power when the gas turbine is running and compressed air and steam is used to keep the unit warm when the gas turbine is not running.

Figure 10 is a schematic diagram of an embodiment of the current invention by heating fuel, which has a complementary power system

recuperated with a supplemental energy system

fueled engine In which the supplementary compressor is driven, some or all of the fueled engine's exhaust is used to heat the gas turbine fuel.

Figure 11 shows a gas turbine cycle of the type applicable to the present invention on the temperature entropy of the entropy graph enthalpy 10 - entropy for SW501FD2 injected equal to 25 kg/sec (55 lb/sec) +5.5% (.

Figure 12 shows a comparison of the workpiece per pound of mass required to pump air from weather conditions

For compressor compare elevated pressure to atmospheric conditions

Intercooler compressor process.

Detailed description:

<p>15th An aspect of the invention relates to methods and systems that allow gas turbine systems to operate more efficiently under various conditions or modes of operation. In systems such as that described in Nakhamkin Patent No. 6.305.158 (“Patent 158”), where there are three basic modes of operation defined, the normal mode, the charging mode, and the air injection mode, But it only needs a generator</p>

<p>20 An electrical generator has the capacity to deliver "full rated power" that the gas turbine system would receive. The fact is that this patent has not been issued for more than 10 years and so far there are no known applications for it in that it</p>

time Rapidly rising energy costs prove do not determine market requirements.

٦١٩٦

-١١-

First of all, it is very costly to replace and upgrade the alternator so it can receive power “beyond the full rated power” that the gas turbine system currently receives.

Another drawback is that the system cannot be implemented on a combined cycle unit without a significant negative impact on fuel consumption. are used most

5 Specific implementations of heat recovery for heating air in a simple cycle operation, which lower the point of excess fuel consumption, however, add obvious cost and complexity. The submitted invention identified below identifies both the cost and performance shortfalls of the systems disclosed in Patent 158'.

An embodiment of the invention relates to a method for operating a gas turbine energy system 10 which includes:

(a) operation of a gas turbine system comprising a compressor, burner case, incinerator, and turbine, connected to each other by fluids;

(b) ambient air using a supplementary compressor driven by a fueled motor, the operation of which is independent of the electric grid; and

15th (c) Injecting pressurized air into the said incinerator housing.

According to a preferred embodiment of the invention, the warm exhaust from the separately fueled engine is used to preheat the fuel fed into the burner.

Preferably, the fuel-fed engine incorporates a jacket cooling system,20 and the cooling heat from the jacket cooling system is used for preheating the fuel as it is fed into the incinerator.

In accordance with another preferred embodiment of the invention, all or part of the exhaust of a fueled engine is diverted to provide

Heat input to a steam generator to recover heat when the gas turbine is not operating.

٦١٩٦

-١٢-

According to another preferred embodiment of the invention, the compressed air produced is converted by a fuel-engine driven compression process to provide heat entry into a heat recovery steam generator and/or turbine when the gas turbine is not operating.

Another embodiment of the invention relates to a method for operating a gas turbine power system which includes:

5 (a) The operation of the gas turbine system, which includes a compressor, a burner case, an incinerator, and a turbine, has been

connect them to each other with fluids;

(b) the pressure of the ambient air and a portion of the exhaust gases from the fueled engine, using a supplementary compressor propelled by the fueled engine; and

(c) Injection of the exhaust and compressed air mixture into the incinerator housing, where the operation of the fuel engine is independent of the electrical grid.

According to a preferred embodiment of the invention, the warm exhaust from the separated fuel engine is used for preheating the fuel fed into the incinerator.

Preferably, the fueled engine includes a jacket cooling system, and the evaporative heat from the jacket cooling system is used for preheating the fuel as it is fed into the burner.

15th In accordance with another preferred embodiment of the invention, all or part of the exhaust of a fueled engine is diverted to provide

Thermal entry into a steam generator to recover heat when the gas turbine is not operating.

According to another preferred embodiment of the invention, the compressed air produced by the fueled engine driven compression process is diverted to provide heat entry to a heat recovery steam generator and/or turbine when the gas turbine is not operating.

20 Another embodiment of the invention also relates to the method of operating a gas turbine power system which includes:

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

٦١٩٦

-١٣-

(b) the pressure of the ambient air and all exhaust gases from the fueled engine, using a supplemental compressor propelled by the fueled engine; and

(c) Inject the said exhaust and compressed air mixture into the incinerator case, where the operation of the fueled engine is independent of the electrical grid.

5 According to a preferred embodiment of the invention, the warm exhaust from the separated fuel engine is used for preheating the fuel fed into the incinerator.

Preferably, the fueled engine includes a jacket cooling system, and the evaporative heat from the jacket cooling system is used for preheating the fuel as it is fed into the burner.

According to another preferred embodiment of the invention, all or part of the exhaust of a fueled engine is diverted to provide heat entry to a heat recovery steam generator when the gas turbine is not operating.

According to another preferred embodiment of the invention, the compressed air produced by the fueled engine driven compression process is diverted to provide heat entry to a heat recovery steam generator and/or turbine when the gas turbine is not operating.

An embodiment of the invention also relates to a method of operating a gas turbine power system as it includes:

15th (a) The operation of the gas turbine system, which includes a compressor, a burner case, an incinerator, and a turbine, has been

connect them to each other with fluids;

(b) Compressing the exhaust gases only from a fueled engine, using a supplemental compressor propelled by the fueled engine; and

(c) Injection of a mixture of compressed and exhaust air into the incinerator housing, where the operation of the supplied engine is

20 The fuel is independent of the electrical grid.

According to a preferred embodiment of the invention, the warm exhaust from the separated fuel engine is used for preheating the fuel fed into the incinerator.

٦١٩٦

-١٤-

Preferably, the fueled engine includes a jacket cooling system, and the evaporative heat from the jacket cooling system is used for preheating the fuel as it is fed into the burner.

According to another preferred embodiment of the invention, all or part of the exhaust of a fueled engine is diverted to provide heat entry to a heat recovery steam generator when the gas turbine is not operating.

5 According to another preferred embodiment of the invention, the compressed air produced is converted by a compression process

Driven by the fueled engine to provide heat entry to a heat recovery steam generator and/or turbine when the gas turbine is not operating.

Another embodiment also relates to the mode of operation of a gas turbine power system which includes:

(a) operation of a gas turbine system comprising a compressor, burner housing, incinerator, and turbine, connected to each other by fluids;

(b) cooling the gas turbine inlet air using a supplemental refrigeration process driven by a fueled engine; and

(c) Injection of the exhaust from the separated fuel engine into the exhaust of the gas turbine, where the operation of the fueled engine is independent of the electrical grid.

15th Another embodiment also relates to the mode of operation of a gas turbine power system which includes:

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

(b) cooling the gas turbine inlet air using a complementary cooling process propelled by a fueled engine; and

20 (c) Injecting the exhaust from the separated fuel engine into the exhaust of the gas turbine, where it is a

The engine with fuel is independent of the electric grid.

Another embodiment also relates to the mode of operation of a gas turbine power system which includes:

٦١٩٦

-١٥-

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

(b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine; and

(c) Injecting compressed air into the rotor cooling air circuit before the coolant

5 rotor air, since the operation of the engine with fuel is independent of the electric grid.

Preferably, the exhaust from the alternative fuel engine is drained into the turbine exhaust.

Another embodiment also relates to the mode of operation of a gas turbine power system which includes:

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

10 (b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine; and

(c) Injecting compressed air into the rotor cooling air circuit after the rotor air cooler, since the operation of the fueled engine is independent of the electrical grid.

Preferably, the exhaust from the alternative fuel engine is drained into the turbine exhaust.

Another embodiment concerns the mode of operation of a gas turbine power system which includes:

15th (a) The operation of the gas turbine system, which includes a compressor, a burner case, an incinerator, and a turbine, has been

connect them to each other with fluids;

(b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine; and

(c) Injecting compressed air into the intermediate pressure cooling circuit, where the operation of the engine fueled by fuel is independent of the electrical network.

20 Preferably, the exhaust from the alternative fuel engine is drained into the turbine exhaust.

Another embodiment concerns the mode of operation of a gas turbine power system which includes:

٦١٩٦

-١٦-

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

(b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine; and,

(c) Injecting compressed air into a cooling circuit with a nozzle first stage

5 nozzle, where the fueled engine is grid-independent.

Preferably, the exhaust from the alternative fuel engine is drained into the turbine exhaust.

Another embodiment concerns the mode of operation of a gas turbine power system which includes:

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

10 (b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine;

(c) injection of compressed air into the gas turbine cooling circuit; and

(d) Injecting the steam produced using heat from the alternative fuel engine into the turbine, where the operation of the fueled engine is independent of the electrical grid.

Another embodiment concerns the mode of operation of a gas turbine power system which includes:

15th (a) The operation of the gas turbine system, which includes a compressor, a burner case, an incinerator, and a turbine, has been

connect them to each other with fluids;

(b) the pressure of the ambient air using a supplementary compressor driven by a fueled engine;

(c) Injecting compressed air into the turbine when the gas turbine system is not operating, as the operation of the fueled engine is independent of the electrical grid.

20 Another embodiment concerns the mode of operation of a gas turbine power system which includes:

٦١٩٦

-١٧-

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

(b) Steam, which is produced using heat from the alternative fuel engine, is injected into the steam generator to recover heat while the fueled engine system is not operating.

5 Another embodiment concerns the mode of operation of a gas turbine power system which includes:

(a) the operation of a gas turbine system comprising a compressor, a burner housing, an incinerator, and a turbine, connected to each other by fluids;

(b) Exhaust injection of the alternative fuel engine into the steam generator to recover heat while the fuel engine system is not operating.

10

Another embodiment of the invention relates to a device formed to conduct methods according to the invention comprising a gas turbine system comprising a compressor, a burner case, a burner, a turbine, connected to each other by fluids, and one or more additional components (for example, an engine supplied with fuel) formed to make a method according to the invention.

The components of an embodiment of the present invention are illustrated in Figure 1 as they are used in a turbine system

15th Existing gas (1). The gas turbine system (1) includes a compressor (10), an incinerator (12), a combustion case (14), a turbine (16) and a generator (18). The fueled engine (151) is used. , which is either a reciprocating internal combustion engine, a gas turbine, or a similar machine in which fuel is converted into energy through an exothermic reaction such as combustion, to drive a complementary multi-intercooled compressor

20 Relays (116) where the ambient air (115) and/or the cooled exhaust (154) is compressed and drained

Compressed air/exhaust 117 (compressed air/exhaust). Because those skilled in the art will already appreciate that, as the exhaust air in the supplementary compressor passes from one compressor stage to the next, the air is intercooled with a heat exchanger , such as a cooling tower, to reduce the work required for compressive air at a phase

٦١٩٦

-١٨-

auxiliary compressor. This increases the efficiency of the supplementary compressor (116), as it makes it more efficient than the compressor (10) of the gas turbine system (1).

This embodiment also includes a heat recoverer (144), which is a heat exchanger whereby exhaust gas (152) is received from the fueled engine (151) and compressed air/exhaust

5 117 (compressed air/exhaust) from the supplemental compressor (116).

(144), 152 hot exhaust gas heats up the compressed air/exhaust (117) and then exits the heat recoverer (144) as considerably cooler exhaust gas (153). 144), the compressed air/exhaust (117) absorbs the heat from the exhaust gas (152) and then exits from the heat recoverer (144) in the form of the most compressed air/exhaust

118 (from him when) substantially hotter compressed air/exhaust 10 considerably hotter

It enters the heat recoverer (144). The considerably hotter compressed exhaust air/exhaust (118) is then discharged to the combustion case (14) of the gas turbine system (1) where it becomes an addition to the mass flow through the burner (12) ) and the turbine (16).

The warm exhaust gas 153 that has been drained from the heat recoverer 15 (144) enters the valve 161 where some or all of the warm exhaust gas (153) is directed to

Cooling tower (130 cooling tower) for additional cooling. The cool exhaust

154 gas) to the inlet of the supplementary compressor (116). Ambient air can also be added

Additional ambient air (115) to the inlet of the supplementary compressor (116). Any warm exhaust gas (153) that is not diverted to the cooling tower (130) may be discharged by

20 Valve (161) to atmospheric air, fuel heating system, or gas turbine exhaust (22).

Partial exhaust recirculation system reduces emissions from the fueled engine

separately fueled engine while exhaust . exhaust

100% recirculation system of the engine with separated fuel as a source of emissions. and this is

It can be very helpful

where

Allow

For reasons and also to reduce costs, as can be done

25 The use of an existing gas turbine exhaust technology system thus eliminates the possible cost of the project.

٦١٩٦

-١٩-

It diverts gasoline, diesel, natural gas, or biofuels and similar reciprocating engines are relatively insensitive to back pressure, so the recuperator 144 is placed on the 151 fueled engine. It does not cause a significantly 5 measurable effect on the performance of the fueled engine (151). Figure 1-1 shows the gas turbine cycle on a TS or HS diagram (temperature-entropy of enthalpy-entropy). The temperature and enthalpy of enthalpy are proportional to each. Cp), where the vertical distance between 101.42 kPa (14.7 pounds per inch) to ambient pressure (P10).

Work ("CDP") compressor discharge pressure 10 and compressor drain pressure operation

The compressor required to pump air to the compressor discharge pressure.

The dotted line 1 PI shows the drain pressure of the injected compressor, which is 15.04 bar (218.1 psi), while the dashed line 2 PI shows the drain pressure of the injected compressor, which is 15.89 bar (230.5 psi). inches (where . increases

<p>15th Compressor discharge temperature from 410°C (770°F) (3 PI) without compressed air injection, to 398°C (749°F) (4 PI) with compressed air injection due to an increase in the compression ratio. This additional -4.4 °C (24 °F) produces 1% less fuel than is required to heat the air to 1,346 °C (2,454 °F) ignition temperature,</p>

<p>20 It also produces a 1.3% increase in compressor operation (compared to a 5 PI compressor without compressed air injection), or 3.5 MW. The temperature rises (the rise in heat content in the mass) from approximately 399°C (750°F) to turbine inlet temperature 1346 °C (2454 °F), approximate “ignition temperature” (6 PI), which is the fuel input in British thermal units</p>

<p>25 BTU") British Thermal Units". where is the vertical distance from the compressor drain pressure</p>

٦١٩٦

-٢٠-

(2 PI,1 PI) to 101 kPa (14.7 psi) (P10) on the right side turbine work (7 PI), which is approximately twice the work of the compressor (5 PI). Exhaust temperature decreases with injection. This is due to the high term compression ratio, from 530°C (987°F) (P18) to 519°C (967°F) (P19), a drop of 6.6°C (20°F), or +.81% and more capacity. per pound of air, +4.7

megawatts at base flow.

Figure 12 shows a comparison of work per pound of mass required to pump air from atmospheric conditions (14.7) to a pressure slightly higher than the compressor drain pressure of 15.8 bar (230 psi) so it can be dispensed into a compressor drain pressure blower aerator. The dashed curve represents an approximate three-stage intercooler compressor 2.45 pressure ratio per stage (2.5 bar (about 36 psi) after the first stage and 6.3 bar (92 psi) after the second stage, and 15.86 bar (230 psi after the third stage). The work to compress 6.7 kPa (1 pound mass) of air (using a P20 intercooled process) is significantly lower than that of a 15 intercooled compressor considering similar stage compression efficiency. Realistically, due to losses

The intercooler pressure at each stage and the fact air was actually pumped to a pressure higher than the CDP to effectively inject the air into the gas turbine, and more work is required from Figure 12. However, per base pound for these considerations, a compressor is used The intercooler is less able to operate (P21) than is required by the gas turbine to compress the air for the turbine cycle 20.

Figure 2 shows the embodiment from Figure 1 where the fuel heating is done by using a warm exhaust (153) to heat the fuel in a fuel 201 heater. This also improves the efficiency of the power plant and reduces the fuel inlet British Thermal Units BTU required to raise

٦١٩٦

-٢١-

The compressor (10) to drain the air to the turbine inlet temperature, which is produced in a low amount of fuel (24), which is required by the gas turbine.

Figure 3 uses an alternative technology, the 401 inlet chilling system, to increase capacity. Inlet chilling works by providing a cold 5 refrigerant that is used to cool the fluid that has been circulated in the 405 radiator.

The cooled fluid (403) enters the radiator (405) and cools the gas turbine inlet air (20 gas turbine inlet air) as it passes through the radiator (405) and such cool air (402) is drained into the GT inlet causing the GT cycle more Efficiency and produces higher power. The cooled fluid (404) is then drained from the hotter (405) radiator when it is introduced and the chiller system (401) cools down 10 where the fluid returns to the bottom. Traditionally, these systems are driven by electric motors, which place a large parasitic load on the station at the same time the station attempts to create additional power, which translates into a significant heat rate penalty. When the split-fuel engine is used to drive the chiller, the parasitic load is removed.

15th With the advent, current deployment and evolution of efficient natural gas reciprocating engines, the exhaust from the reciprocating engine can be added to the gas turbine exhausts to make additional steam in the steam generator to recover the heat of the steam turbine. Some can be extracted

Or all this extra steam as well and use steam injection to supply power if needed. All of these features are effective and obvious improvements to the combined cycle unit. On simple cycle units, an additional 20 auxiliary boiler (not shown) 352 hot exhaust can be used to produce steam which can then be used to inject steam into the GT where it is produced in the power supply.

Figure 4 shows an alternate embodiment from Figure 1 where the 501 valve is positioned at the exhaust (152) from the split-fuel engine (151) which pushes the exhaust (152) from the engine (151) to the 503 H SG) from the combined cycle unit They are used before preheating or to keep the system hot which enables faster start times.When this system is running, a clutch is used

٦١٩٦

-٢٢-

clutch hydraulic or mechanical 504 to separate the shaft from the fueled engine (151) from the compressor (116) such that it does not start.

Figure 5 is very similar to Figure 4, however, the 116 supplemental compressor clutch is removed and the compressor supplies 5 602 compressed air/exhaust mixture to the heat recovery steam generator. 503) and/or

The exhaust/compressed air mixture (118) is transferred to the gas turbine via heat recovery (114). This is an advantage over the low pressure exhaust as shown in Figure 4 and because the compressed air mixture can be more easily routed In addition, the separated fuel engine will produce 10 (151) hotter exhaust temperatures that may be required for heating purposes. The modulation can be done in such a low pressure method, but a very high temperature exhaust (not shown) can be used for the preheat areas of the heat recovery steam generator (503) and GT which can use 15 degree air . Hot heat, low temperature compressed air/exhaust can be used in

The areas of a heat recovery steam generator (503) and a turbine that can use cooler temperature air.

Figure 6 is a simple approach for injecting compressed air into a gas turbine (1) system. Because compressed air (117) is not required to be heated because 20 air is used to replace the 602 cooled cooling air, which is supplied with

Natural by a gas turbine (601) and cooled by air or steam in a rotary air cooling system 155 (rotor air cooling system) under normal operation Siemens Westinghouse 501F, 501D5, and 501B6 engines, for example, are approximately 6.5% of compressed air By the compressor (10) drained (601) from the ventilation drain device

25 Blower for compressor (14) compressor discharge plenum through single large pipe

٦١٩٦

-٢٣-

single large pipe, approximately 20 in diameter. The bleed air (601) is bleed air at approximately 1.38-1.72 MPa, 343-399 °C (200-250 psi and 650-750 F). The hot air enters the rotary air cooling system (155) where the air is used or steam to cool the drain air (601).

5 The heat is discharged to the atmosphere (603) and consumed when air is used to cool the drain air (601). However, if steam is used as a coolant to cool the drain air (601), the heat is transferred from the drain air (601). 601) to the steam, thus increasing the enthalpy in the mass of the steam, and then the steam can be used in the steam cycle. In all cases, there is an effective improvement to the gas (1(GT) cycle if no heat is discharged at all. By injecting cold compressed air 117(cool pressurized air) up (601) or down (602) of the 155(rotor air cooler) heat 603 (rejected) is reduced or removed, thus improving the efficiency 1 GT cycle while at the same time effectively increasing the mass flow of air through the combustor section (12) and the turbine section (16). Most gas turbines are dedicated to compressor bleeders 15 medium pressure (701) which are used to cool the last stages of the turbine where pressure reduction is required as shown in Figure 7. Also, all gas turbines feed a first blade cooling circuit with the highest pressure. Available, which is at the compressor drain fold port (14) (or burner housing) as shown in Figure 8.

Depending on the injection site, rotary cooling air is required as shown in Figure 6 and 20, intermediate pressure cooling as shown in Figure 7, or first vane cooling as shown in Figure 8, and the various pressures. These pressures can be supplied through the exit of the intercooled supplementary compressor

116 (or early stages of the intercooled supplemental compressor

Complementary intercooler (116) for lower pressure applications. In all cases, where this type of injection uses little (not shown) or no recovery to heat the air upwards, exhaust can be added (152)

٦١٩٦

-٢٤-

For a fuel-separated engine to a gas turbine exhaust(22) as shown to increase the exhaust power of a combined cycle unit. If the power boost system of the present invention is placed at a simple cycle unit, the hot exhaust (152) may be used in the boiler The packaged (901) to make steam for injection into the gas turbine (903) as shown in Figure 9.

5 Whereas a TurboPHASE package (as this invention is called) is supposed to be modular, it can have the advantage of incorporating it into a packaged boiler (901) when at least one of the units such that during the peak times of a typical TurboPHASE package can be referenced to maintain Hot gas turbine with pressurized hot air cycle 117 and keep gas turbine / 503 HPvSG hot with steam cycle to reduce start-up time requirement.

10 There are further improvements in efficiency that can be achieved by incorporating low quality heat. For example, in Example 10, the gas turbine fuel inlet can be pre-heated (24) with heat from a fueled engine's jacket cooling system (1011 and 1012). By doing this, the cooling requirements of the plant will be reduced. cooling requirements and turbine fuel pre-heating will take place

15th Gas (1023) before entering the 201 fuel heater, and therefore requires the lowest heat intake

To reach the desired fuel temperature, or be able to reach a higher fuel temperature. Also, Figure 10 shows an alternative embodiment where exhaust (153) from heat recovery (144) is used to add to the final heat in the gas turbine fuel (1024) prior to injection into the GT. In this case, it is

20 Exhaust gas (153) of an alternate-fuel engine (151), after flowing through the fuel heater (201) and draining relatively cool.

While the specific systems, components, methods, and means described herein or described in detail are fully capable of achieving the objectives and characteristics described above of the invention, those preferred embodiments provided by the invention must be understood and thus represent the subject matter 25 that has been Reflect on it broadly through the current invention, and it includes the perspective of the current invention

٦١٩٦

-٢٥-

Exactly the other embodiments that may become apparent to those skilled in the field, and the present invention perspective is accordingly not limited to anything other than the protections attached. Which has a reference to an element in the singular tools "one or more" and not one and only one", unless otherwise stated in the protection element.

5 It will be estimated that the modifications and variations according to the invention are explained by the previous data and within the framework of the attached protection elements without deviating from the content and the intended perspective of the invention.

relay list:

144 heat retriever

130 Cooling Tower/Intercooler

10 152 Exhaust exit

124 Engine fuel entry

116 intercooler compressor

151 fueled engine

20, 115, 150 air intake

15th 22 GT . exhaust

24 GT . fuel entry

201 fuel heater

401 Cooling system

352 Exhaust exit

20 503 Heat Recovery Steam Generator

٦١٩٦

-٢٦-

155 rotor air cooling

603 heat exit

901 full boiler

1011, 1012 cooling

5 1024 Hot GT Fuel Entry

"A" Engine Jacket Heater

B Temperature (Fahrenheit)

C entropy (btu/lbs per mass/R)

D 230 psi

<p>10 H 92 psi</p>

<p>and 36 pounds per square inch</p>

<p>"g" 14.7 psi</p>

٦١٩٦

-٢٧-