Unitary conduit for transporting fluids and method of manufacturing

The present invention generally relates to conduits for transporting fluids, and more particularly to single conduits for transporting fuel to fuel nozzles used in gas turbine engines.

Turbine engines typically include multiple fuel nozzles to supply fuel to the engine's combustor. Fuel is introduced from the fuel nozzle at the front end of the burner in the form of a very fine spray. Compressed air flows around the fuel nozzles and mixes with the fuel to create an air-fuel mixture, which is ignited by the burner. Due to the limited fuel pressure available and the wide range of required fuel flow rates, many fuel injectors include a pilot nozzle and a main nozzle, only the pilot nozzle is used during start-up and the output is high. Both nozzles are used during operation. The flow to the main nozzle is reduced or stopped during start-up and low power operation. Such an injector can more accurately control the fuel flow and guide the fuel injection more accurately according to a specific combustion requirement, so that it can burn more efficiently and cleanly than a single nozzle fuel injector. .. The pilot nozzle and main nozzle can be housed in the same nozzle assembly or can be supported in another nozzle assembly. Also, these dual nozzle fuel injectors can be configured to allow further control of the fuel for the dual combustor, resulting in even higher fuel efficiency and reduction of harmful emissions. The temperature of the ignited air-fuel mixture can reach above 3500 ° F (1920 ° C). Therefore, it is important that the fuel supply conduits, channels and distribution systems are virtually leak-free and protected from flames and heat.

Continuous exposure to high temperatures during the operation of the turbine engine for a long period of time can induce thermal stress on the conduits and fuel nozzles, which can damage the conduits and fuel nozzles and the conduits and fuel. It may adversely affect the operation of the nozzle. For example, thermal stress can cause a decrease in fuel flow in the conduit, which can lead to uneven distribution of excess fuel in the turbine engine. In addition, long-term continuous operation with damaged fuel nozzles can reduce turbine efficiency, damage turbine components, and / or reduce engine exhaust temperature margins.

By improving the life cycle of the fuel nozzle installed in the turbine engine, the life of the turbine engine can be extended. Known fuel nozzles include delivery and support systems. A delivery system that includes conduits for transporting fluid delivers fuel to the turbine engine and is supported and shielded within the turbine engine by a support system. More specifically, known support systems surround the delivery system and are therefore exposed to higher temperatures and have higher operating temperatures than delivery systems that are cooled by the fluid flowing through the fuel nozzles. By setting the outer and inner contours and thicknesses, the thermal stress of the conduits and fuel nozzles can be reduced.

Traditional gas turbine engine components, such as fuel nozzles and their associated conduits, are generally expensive to manufacture and / or repair. This is because traditional fuel nozzle designs with complex conduits for transporting fuel involve complex assemblies and the joining of more than 30 components. More specifically, the use of brazed joints may increase the time required to manufacture the component, and the need for the proper area to allow the placement of the brazed alloy, unnecessary. The need to minimize the flow of brazing alloys, the need for acceptable inspection techniques to verify brazing quality, and some brazing that can be used to prevent remelting of the previous brazing joint. The fabrication process can be complicated for any of several reasons, including the need to have brazing alloys. In addition, a large number of brazing joints can result in some brazing runs that can make the base metal of the component fragile. The presence of a large number of brazing joints can increase the weight and manufacturing cost of the components, which is not desirable.

<p num="0006"> Therefore, it is desirable to have a conduit for transporting fluid, such as a fuel supply conduit for fuel nozzles, which has a single structure to reduce the possibility of leakage and the other unwanted effects mentioned above. There will be. It is desirable to have a fluid supply conduit with a complex shape with a single structure for cost reduction and ease of assembly. It is desirable to have a method of manufacturing a single conduit having a complex three-dimensional shape for transporting a fluid, such as a fuel supply conduit for a fuel nozzle.</p>

<p num="0007"> The above need (s) is a method of making a single conduit, the step of determining the 3D information of a single conduit with at least one flow path, and each slice defining the cross-sectional layer of the single conduit. Provides a method of making a single conduit, including the step of converting 3D information into multiple slices to be made and the step of forming each layer of the single conduit one after another by melting the metal powder using laser energy. It can be satisfied by an exemplary embodiment. In another aspect of the invention, there is disclosed a single conduit that includes a main body and a flow path, the flow path and the main body having a single structure, and being manufactured using a rapid manufacturing process. In another embodiment, the single conduit 105 has a flow path whose cross-sectional shape changes from a first cross-sectional shape to a second cross-sectional shape. In another embodiment, the outer contour 140 of the body 106 generally fits the inner contour 141 of the flow path 108. In another embodiment, the flow path 108 branches into a plurality of sub-passages 109.</p><p num="0008"> The subject matter considered to be the present invention is specifically pointed out and explicitly claimed at the conclusion of the specification. However, the present invention can be best understood with reference to the following description along with the accompanying drawings.</p>

<figref num="1">It is the schematic of the gas turbine engine of the high bypass turbofan.</figref><figref num="2">FIG. 3 is an isometric view of a fuel distributor having a single duct according to an exemplary embodiment of the present invention.</figref><figref num="3">It is a cross-sectional view of the horizontal axis of the single conduit shown in FIG.</figref><figref num="4">FIG. 3 is an isometric view of a fuel distributor having a single duct according to an alternative exemplary embodiment of the present invention.</figref><figref num="5">It is a cross-sectional view of the horizontal axis of the single conduit shown in FIG.</figref><figref num="6">FIG. 3 is an isometric view of a fuel distributor with a single conduit according to another alternative exemplary embodiment of the present invention.</figref><figref num="7">It is a cross-sectional view of the horizontal axis near the inlet end of the single conduit shown in FIG.</figref><figref num="8">It is a cross-sectional view of the horizontal axis at the intermediate position of the single conduit shown in FIG.</figref><figref num="9">It is a cross-sectional view of the horizontal axis near the outlet end of the single conduit shown in FIG.</figref><figref num="10">FIG. 5 is an isometric vertical cross-sectional view of a single vessel according to another exemplary embodiment of the present invention.</figref><figref num="11">FIG. 3 is an isometric view of an exemplary fuel nozzle having a single conduit according to an exemplary embodiment of the present invention.</figref><figref num="12">It is a partial isometric sectional view of the exemplary fuel nozzle shown in FIG.</figref><figref num="13">It is a partial isometric sectional view of the exemplary fuel nozzle shown in FIG.</figref><figref num="14">It is a flow chart which shows the exemplary embodiment of the method of manufacturing a single duct.</figref>

Next, referring in detail to a drawing showing the same elements with the same numbers throughout the figure, FIG. 1 is an exemplary gas turbine engine 10 incorporating an exemplary embodiment of a single conduit for transporting liquid fuel to a fuel injector. (High bypass type) is shown in schematic format. An exemplary gas turbine engine 10 has an axial centerline axis 12 passing through it for reference purposes. The engine 10 preferably includes a core gas turbine engine identified by number 14 as a whole and a fan section 16 located upstream from it. The core engine 14 typically includes an overall tubular outer casing 18 that defines the annular inlet 20. The outer casing 18 further surrounds and supports the booster 22 in order to increase the pressure of the air entering the core engine 14 to the first pressure level. The high-pressure multi-stage axial compressor 24 receives compressed air from the booster 22 to further increase the pressure of the air. Compressed air flows into the combustor 26, where fuel is injected into the compressed air stream, igniting and raising the temperature and energy levels of the compressed air. High energy combustion products flow from the combustor 26 to the first (high pressure) turbine 28 to drive the high pressure compressor 24 via the first (high pressure) drive shaft 30, and then the first drive shaft 30. It flows to the second (low pressure) turbine 32 to drive the booster 22 and the fan section 16 via a second (low pressure) drive shaft 34 that is coaxial with. After driving each of the turbines 28 and 32, the combustion products leave the core engine 14 via the exhaust nozzle 36 to provide at least a portion of the jet propulsion thrust of the engine 10.

The fan section 16 includes a rotatable axial fan rotor 38 surrounded by an annular fan casing 40. It will be appreciated that the fan casing 40 is supported from the core engine 14 by a plurality of substantially radially spaced outlet guide vanes 42. In this way, the fan casing 40 surrounds the fan rotor 38 and the fan rotor blades 44. The downstream section 46 of the fan casing 40 extends over the outer portion of the core engine 14 and defines a secondary or bypass airflow conduit 48 that provides additional jet propulsion thrust.

From a flow perspective, it will be understood that the initial airflow indicated by arrow 50 enters the gas turbine engine 10 through the inlet 52 to the fan casing 40. There are two airflows 50, a first compressed airflow (indicated by arrow 54) that passes through the fan blade 44 and travels through conduit 48, and a second compressed airflow (indicated by arrow 56) that enters booster 22. Divided into.

The pressure in the second compressed air stream 56 increases and enters the high pressure compressor 24 as indicated by the arrow 58. After mixing with the fuel and burning in the combustor 26, the combustion product 60 exits the combustor 26 and flows through the first turbine 28. The combustion product 60 then flows through the second turbine 32 and exits the exhaust nozzle 36 to provide at least a portion of the thrust of the gas turbine engine 10.

Combustor 26 includes a vertical axis 12 as well as an annular combustion chamber 62 coaxial with inlet 64 and outlet 66. As described above, the combustor 26 receives an annular flow of compressed air from the high pressure compressor outlet 69. A part of this compressor exhaust air flows into the mixer (not shown). Fuel is injected from the fuel nozzle tip assembly and mixed with air to form an air-fuel mixture, which is sent to the combustion chamber 62 for combustion. Ignition of the air-fuel mixture is achieved by a proper igniter and the resulting combustion gas 60 flows axially towards and into the annular, first stage turbine nozzle 72. Nozzle 72 includes a plurality of radial, circumferentially spaced nozzle vanes 74 that rotate the gas so that the gas flows at an angle and acts on the first stage turbine blades of the first turbine 28. It is defined by an annular flow path. As shown in FIG. 1, the first turbine 28 preferably rotates the high pressure compressor 24 via the first drive shaft 30. The low pressure turbine 32 preferably drives the booster 24 and the fan rotor 38 via the second drive shaft 34.

The combustion chamber 62 is housed in the engine outer casing 18. Fuel is supplied to the combustion chamber by, for example, a fuel nozzle as shown in FIGS. 11, 12 and 13. The liquid fuel is transported via a single conduit 105 (ie, a conduit having a simple structure) as shown, for example, in FIGS. 2, 4, 6 and 10. The single vessel 105 may be located within the stem 102 and coupled to the fuel distributor tip 190. The pilot fuel and main fuel are sprayed onto the combustor 26 by the fuel nozzle tip assembly using conventional means. During the operation of the turbine engine, initially pilot fuel is supplied through the pilot fuel passage 153 (see, eg, FIG. 10) during predetermined engine operating conditions such as starting and idling operations. The pilot fuel is discharged from the fuel distributor tip 190 via the pilot fuel outlet 162. When additional power is required, the main fuel is supplied through the main fuel passages 151, 152 (see, eg, FIG. 10) and the main fuel is injected using the main fuel outlet 161.

FIGS. 2-10 show exemplary embodiments of the invention of a single vessel 105 for transporting fluids. The term "single" is used in this application to mean that the relevant components, such as the conduit 105 described herein, are manufactured as an integral part during manufacture. Therefore, a single component has an integral structure in the entire component, and is different from a component manufactured by a plurality of component components that are combined to form a single component.

FIG. 2 shows an isometric view of a fuel distributor 100 with a single vessel 105 according to an exemplary embodiment of the present invention. The exemplary fuel distributor 100 shown in FIG. 2 includes a single vessel 105 and a distributor tip 190. The single conduit 105 and the distributor tip 190 may have a single structure as shown in FIG. 2, which is manufactured using the methods described herein below. Alternatively, the fuel distributor 100 manufactures the distributor tip 190 and the stand-alone conduit 105 separately and connects them using appropriate conventional connecting means so that the distributor tip 190 is in flow communication with the stand-alone conduit 105. It may be manufactured by.

As shown in FIGS. 2-10, the single vessel 105 includes one or more channels 108 located within the body 106. The single conduit 105 has an inlet end 111 and an outlet end 112. The fluid enters the conduit 105 at the inlet end 111, flows longitudinally 101 towards the outlet end 112, and exits the conduit 105 at the outlet end 112. FIG. 3 shows a cross-sectional view on the horizontal axis of the exemplary single vessel shown in FIG. As shown in FIG. 2, the single conduit 105 includes an outer contour 140 and a main body 106 having a large number of channels 108 located within the main body 106. The flow path has a cross-sectional shape 120 and an inner contour 141. In the exemplary embodiment shown in FIG. 3, there are four passages, each having a circular cross-sectional shape. As shown in FIG. 2, the flow paths may have different dimensions. For example, in the exemplary embodiment shown in FIG. 2, two outer passages 155 and 157 are pilot fuel passages and two inner passages 151 and 152 are main fuel streams used for the fuel distributor 100. The road. Each flow path 108 has a wall, for example, as shown as item 114, which separates the inner contour 141 of the flow path 108 from the outer contour 140 of the body 106. Channels 108 located adjacent to each other within the body 106 are separated from each other by a separation wall, for example, as shown as item 116. In the exemplary embodiments shown in FIGS. 2 and 3, the main channels 151, 152 have diameters between about 0.060 inches and 0.150 inches, respectively, and the pilot channels 155, 157. Have diameters between about 0.040 inches and 0.150 inches, respectively. The wall 114 has a thickness between about 0.020 inches (about 0.051 cm) and 0.060 inches (about 0.152 cm). The separation wall 116 has a thickness between about 0.020 inches (about 0.051 cm) and 0.060 inches (about 0.152 cm).

Circular cross sections have usually been selected in the flow path based on manufacturing requirements. However, in certain cases, such as in fuel circuits exposed to thermal stress, it is advantageous to have a flow path 118 having a non-circular cross section. By properly shaping the inner portion of the flow path 108 and the outer contour 140 of the main body 106, the stress concentration of the flow path 108 can be reduced. The flow path 108 may be circular (see FIG. 3) or elliptical (see FIG. 5). A circular passage would be shorter in length but wider in width. An elliptical passage would be narrower but longer in length. The narrower width provides more flexibility in the supply portion of the single conduit 105, facilitating the reduction of thermal stresses in the body 106. FIG. 4 is an isometric view of a fuel distributor with a single conduit 105 according to an alternative exemplary embodiment of the invention, where the flow path 118 has a non-circular cross-sectional shape 121. FIG. 5 shows a cross-sectional view on the horizontal axis of the single vessel 105 shown in FIG. The inner contour 141 of each flow path 118 can be selected to be circular, non-circular, or the proper combination of circular and non-circular. FIG. 5 shows an exemplary embodiment of a single vessel 105 having one channel with a circular contour and three channels 118 with a non-circular contour 141. Each flow path 118 has a wall 114 that separates its inner contour 141 from the outer contour 140 of the body 106. The flow paths 118 adjacent to each other in the main body 106 are separated from each other by the separation wall 116. In the exemplary embodiment shown in FIG. 5, the non-circular flow path 118 is approximately 0.004 square inches (approximately 0.026 cm).²) And 0.018 square inches (about 0.116 cm)²), The circular pilot channel has a cross-sectional area of about 0.005 square inches (about 0.0323 cm).²) Has a cross-sectional area. The wall 114 has a thickness between about 0.020 inches (about 0.051 cm) and 0.060 inches (about 0.152 cm). The separation wall 116 has a thickness between about 0.020 inches (about 0.051 cm) and 0.060 inches (about 0.152 cm).

In the exemplary embodiment of the single conduit 105 shown in FIGS. 2-5, the cross-sectional shapes 120, 121 of the flow path 108 remain substantially constant from the inlet end 111 to the outlet end 112 of the single conduit 105. Similarly, the cross-sectional area of each flow path 108 may be substantially constant from the inlet end 111 to the outlet end 112 of the single vessel 105. Alternatively, the cross-sectional area of the flow path 108 is preferably substantially one from the inlet end 111 to the outlet end 112 of the single conduit 105 so that proper flow characteristics are achieved within the distributor tip 190 of the fuel nozzle. It may change as follows. For example, it is possible to accelerate the fluid in several channels 108 within a single conduit 105 by reducing the flow range, preferably substantially uniformly, between the inlet end 111 and the outlet end 112. Is.

In some applications, it is advantageous to vary the medial contour 141 and cross-sectional area of the flow path 108 of the single conduit 105 between the inlet end 111 and the outlet end 112. 6-9 show an exemplary embodiment of a single vessel 105 with four channels 108 having a first cross-sectional shape 131 near the inlet end 111 and a second cross-sectional shape 132 near the exit end 112. The cross-sectional shape 141 varies substantially uniformly between the first cross-sectional shape 131 near the inlet end 111 and the second cross-sectional shape 132 near the exit end 112. 7-9 show cross-sections of the single vessel 105 near the inlet end 111, at the outlet end 112, and at an intermediate position between the inlet end 111 and the outlet end 112. As shown in FIGS. 7 to 9, in the first cross-sectional shape 131, each of the four passages 108 is circular. In the second cross-sectional shape 132 near the exit end 112, three of the passages are non-circular and the fourth passage (pilot passage 153) remains circular. FIG. 8 shows the cross section at the intermediate position and shows the change from the circular cross section to the non-circular cross section for the three flow paths 118.

In addition to varying the cross-sectional shapes 131, 132, it may be advantageous to vary the thickness of the walls 114 and separation walls 116 of the single vessel 105 to reduce thermal stress and weight. For example, the single conduit 105 is located near the outlet end 112 located near the distributor tip 190, from the thicker portion from the valve brazing area near the inlet end 111 to reduce the thermal stress of the single conduit 105. It may change to a thinner part. The wall thickness 114 of the fuel passage 108 may be kept substantially constant in a particular cross section in order to reduce weight as shown in FIG. Alternatively, in a particular cross section, the outer contour 140 of the body 106 and the wall thickness 114 of the flow path 108 should obtain a flat outer surface between the right and left ends of the flow path, as shown in FIG. You may shape the contour. Based on the thermal stress profile at the cross-sectional position, it may be advantageous to have a combination of the above means at different cross-sectional positions of the single vessel 105. The cross section and outer contour 140 of the single conduit 105 may be molded to generally conform to the shape of the passage in the body 106 (see Figures 7-9), or they have a smooth outer surface (see Figures 3 and 5). It may be molded to have. In the fuel nozzle application of the single conduit 105, the fuel flowing through the pilot supply conduit cools the body 106 and the fluid passages located within the conduit body and promotes the reduction of thermal stress, as described below. It is possible to locate one or more pilot supply conduits.

FIG. 10 is a partial cross-sectional isometric view of an exemplary single vessel 105 used to transport liquid fuel in a fuel nozzle. In an exemplary embodiment, the single conduit 105 includes a flow path 108 located within the body 106 that acts as a main fuel passage into the fuel nozzle and a pilot fuel passage 153 that extends within the body 106. Fuel from the pilot fuel passage 153 is guided into the fuel nozzle by the pilot supply tube 154 and exits through the pilot fuel outlet 162. For some single vessels 105, it is advantageous to have a flow path 108 that branches into two or more sub-passages 109, 110, for example, as shown in FIG. As shown in FIG. 10 for applying the single conduit 105 to the fuel nozzle, the flow path 108 branches into a first main passage 151 and a second main passage 152. The liquid fuel is supplied into the nozzle through the main passage inlet 126 and enters the flow path 108. The fuel stream then branches into two streams, one through the first main passage 151 and the other through the second main passage 152 and then into the distributor tip 190. As shown in FIG. 10, the main fuel passage 108, the sub passages 151, 152, and the pilot fuel passage 153 are located between the inlet end 111 and the outlet end 112, generally axially 101 in the body 106. Extend along.

An exemplary fuel distributor 100, which has a single vessel 105 as described herein and is used in a gas turbine engine fuel nozzle, is shown in FIGS. 11-13. In an exemplary embodiment, the single vessel 105 is located within the stem 102, which has a flange 160 for mounting on the gas turbine engine 10. The single conduit 105 is located within the stem 102 so that there is a gap 107 between the inside of the stem and the body 106 of the single conduit 105. The gap 107 insulates the single conduit 105 from heat and other adverse environmental conditions surrounding the fuel nozzles of the gas turbine engine. Additional cooling of the single vessel 105 is achieved by circulating air in the gap 107. The single conduit 105 is connected to the stem 102 using conventional connecting means such as brazing. Alternatively, the single conduit 105 and stem 102 may be manufactured by a rapid manufacturing method, such as, for example, direct laser metal sintering as described herein. In an exemplary embodiment, the fuel distributor tip 190 has a main fuel passage (first main passage 151 and second main passage 152) and a pilot fuel passage 153, for example, as shown in FIG. 13, the fuel distributor tip 190. Extends from the single conduit 105 and stem 102 to flow and connect with. Specifically, the main fuel passages 151 and 152 are flow-tethered and coupled to a main fuel circuit defined within the fuel distributor tip 190. Similarly, the primary pilot passage 155 and the secondary pilot passage 157 flow-communicate and are coupled with a corresponding pilot injector (not shown) located inwardly radially within the fuel nozzle.

Illustrative embodiments of the single conduit 105 shown in FIGS. 2-3 and alternative embodiments of the single conduit 105 shown in FIGS. 4-13 are Direct Metal Laser Sintering (DMLS), Laser Net Shape Manufacturing (LNSM), It can be manufactured using rapid manufacturing processes, such as electron beam sintering and other known manufacturing processes. DMLS is the preferred method for manufacturing elemental fuel nozzle components such as the fuel distributors 60, 160 and swirler 50 described herein.

FIG. 14 is a flow chart illustrating an exemplary embodiment of the method 200 for manufacturing the single vessel 105 described herein. Method 200 includes the step of making a single vessel 105 (shown in FIGS. 2-13) using direct metal laser sintering (DMLS). DMLS is a known manufacturing process that uses 3D information about a component, eg, a 3D computer model, to make a metal component. The 3D information is transformed into multiple slices, each slice defining a cross section of a component of a slice of a given height. The components are then "built up" slice by slice or layer by layer until they are complete. Each layer of the component is formed by melting the metal powder using a laser.

Therefore, method 200 includes step 205 to determine the 3D information of the single conduit 105 and step 210 to transform the 3D information into multiple slices where each slice defines the cross-sectional layer of the single conduit 105. The single vessel 105 is then made using DMLS, or more specifically, each layer is formed one after the other at 215 by melting the metal powder using laser energy. Each layer has dimensions between about 0.0005 inches and about 0.001 inches. The single conduit 105 may be made using any suitable laser sintering machine. Examples of suitable laser sintering machines are, but are not limited to, EOSINT.RTM.M270DMLS machines, PHENIX PM250 machines, and / or EOSINT.RTM.M available from EOS of North America, Inc. in Novi, Michigan. 250 Xtended Includes DMLS machine. The metal powder used to make the elemental fuel nozzle components 50, 60, 160 is preferably a powder containing cobalt chromium, but is not limited to any other suitable, such as HS188 and INCO625. It may be a metal powder. The metal powder can have a particle size between about 10 microns and 74 microns, but preferably between about 15 microns and about 30 microns.

Although it is stated herein that the method of manufacturing the elemental conduit 105 uses DMLS as the preferred method, any other suitable rapid manufacturing method using layer-by-layer construction or additional fabrication may also be used. , Will be understood by those skilled in the art. These alternative rapid manufacturing methods are, but are not limited to, selective laser sintering (SLS), 3D printing with inkjet and racer jets, stereolithography (SLS), direct selective laser sintering (DSLS), electronic. Includes beam sintering (EBS), electron beam melting (EBM), laser technology net-shaping method (LENS), laser net-shaping manufacturing (LNSM) and direct metal deposition (DMD).

The single conduit 105 for the fuel distributor 100 of a turbine engine (see Figures 11-13) contains fewer components and fittings than known fuel nozzles. Specifically, the single conduit 105 includes, for example, an integral body 106 having one or more channels shown as items 108, 118, 155, 157, 151 and 152 in FIGS. 2-13 herein. Because it is used, it requires fewer components. As a result, the described fuel distributor 100 provides a lighter, less costly alternative to known fuel distributors. In addition, the described single conduit 105 has less chance of leakage or failure compared to known conduits and is easier to repair.

As used herein, steps listed in the singular or without numerals should be understood not to exclude the plural elements or steps unless it is explicitly stated to exclude the plural. Is. When introducing the elements / components / steps of the Elemental Venturi 500, 600 described and / or exemplified herein, the absence of numerals and articles such as "above" may be one or more elements / components. Intended to mean that there is / etc. The terms "comprising", "including" and "having" are comprehensive and mean that there may be additional elements / components / etc. in addition to the listed elements / components / etc. Intended to. Furthermore, reference to "one embodiment" of the present invention is not intended to be construed as excluding the existence of additional embodiments that also incorporate the listed features.

Although the methods and single conduit 105 described herein are described in the context of supplying liquid fuel to a turbine engine, the single conduit 105 described herein and the method of its manufacture are described as fuel distributors. Or it should be understood that it is not limited to turbine engines. The components of the single vessel 105 or fuel distributor 100 depicted are not limited to the particular embodiments described herein, but rather they are independent of the other components described herein. Can be used individually.

This document includes the best forms and uses examples to disclose the invention and to allow those skilled in the art to manufacture and use the invention. The patentable scope of the invention is defined by the claims and may include other examples noticed by those skilled in the art. Such other examples are such that the example has structural elements that do not differ from the wording of the claims, or that the example differs only slightly from the wording of the claims. If it contains an accompanying equivalent structural element, it is intended to be within the scope of the claims.

10 turbine engine 11 Distributor axis 12 Axial centerline axis 16 fan section 18 outer casing 20 Ring entrance 22 Booster 24 Multi-stage axial flow compressor 26 Combustor 28 turbine 30 drive shaft 32 turbine 34 drive shaft 36 Exhaust nozzle 38 Axial fan rotor 40 annular fan casing 42 Guide vane 44 fan blade 46 downstream section 48 Vessel 50 air flow / swirl 52 entrance 54 Air flow 56 Air flow 58 Air flow 60 Combustion products / combustion gas / fuel distributor 62 Combustion chamber 64 entrance 66 Exit 68 Nozzle tip assembly 69 exit 72 turbine nozzle 74 Nozzle vane 100 distributors 101 vertical 102 stem 105 Elemental conduit 106 body 107 Gap 108 Channel 109 Sub-passage 110 sub-passage 111 Entrance end 112 Exit end 114 wall 116 Separation barrier 118 Channel 120 cross-sectional shape 121 Cross-sectional shape 126 Main passage entrance 131 Cross-sectional shape 132 Cross-sectional shape 140 outer contour 141 Inner contour 151 Main fuel passage / flow path 152 Main fuel passage / flow path 153 Pilot fuel passage 154 Pilot supply tube 155 Aisle / Aisle 157 Aisle / Aisle 160 Flange / Fuel Distributor 161 Main fuel outlet 162 Pilot fuel outlet 163 Pilot fuel injector 190 Fuel Distributor Tip 300 distributor 301 Distributor ring body 302 Main flow path 303 Main flow path 304 Main flow path 305 Main flow path 306 wall 307 entrance 308 Mainstream exit passage 309 Fuel injection 310 Fuel post 312 heat shield 314 heat shield 316 Insulation gap 317 Fluid flow direction 318 Fluid flow direction 401 Pilot entrance 402 Pilot flow path 403 Inflow route 404 pilot flow path 405 Outflow channel 406 Pilot fuel flow direction 502 Pilot flow path 503 Inflow route 504 Pilot flow path 505 pilot outflow channel 506 Pilot fuel flow direction 507 Pilot entrance 516 Insulation gap 563 Pilot fuel injector 601 Distributor ring body 602 Pilot flow path 603 Main flow path 604 Main flow path 610 fuel post 611 heat shield 612 Front heat shield 614 Rear heat shield 616 Insulation gap 654 Pilot supply tube 661 Main fuel outlet 663 Pilot injector 670 Ring ring 672 Ring ring wall 674 slot 680 Cooling holes