Axial-stage fuel distribution device of gas turbine

Abstract

The invention discloses a gas turbine axial stage fuel distribution device which comprises a lining, at least two fuel pipelines and a flange, the number of the fuel pipelines is at least two, the at least two fuel pipelines are arranged in the circumferential direction of the lining at intervals, the fuel pipelines extend in the extending direction of the lining, the fuel pipelines are provided with pipe cavities, and the flanges are arranged in the pipe cavities. The flange is arranged at one end of the lining, the flange is provided with a feeding port and a fuel ring cavity, the feeding port is communicated with the fuel ring cavity, the fuel ring cavity is arranged in the circumferential direction of the lining and communicated with the pipe cavity, and the flange, the fuel pipeline and the lining are integrally formed. The axial-stage fuel distribution device of the gas turbine is good in sealing performance, the structure is simplified, and the integrity is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to an axial stage fuel distribution device for a gas turbine. Background Art

[0002] In the thermodynamic cycle of a gas turbine, excess air easily forms nitrogen oxides (NOx) at high temperatures. In order to reduce the emission of nitrogen oxides, staged combustion is usually used in the combustion chamber of the gas turbine.

[0003] In the related art, the combustion chamber comprises at least two axial-stage burners evenly spaced along the circumference of a liner and at least two fuel pipes. One end of the fuel pipe passes through the liner flange to the outside of the casing and connects to the fuel inlet flange. The other end of the fuel pipe is axially connected to the axial-stage burner to supply axial-stage fuel. However, because the fuel pipe sections include sealed joints, elbow welds, bellows welds, and other methods, and the pipe section joints must be welded or sealed, the pipe section structure is complex and non-integrated. This can lead to thermal displacement and vibration during engine operation, resulting in fuel leakage. Summary of the Invention

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent. To this end, an embodiment of the present invention provides an axial stage fuel distribution device for a gas turbine.

[0005] The gas turbine axial stage fuel distribution device according to an embodiment of the present invention comprises:

[0006] bushing;

[0007] a fuel pipeline, wherein the number of the fuel pipelines is at least two, and the at least two fuel pipelines are arranged at intervals along the circumference of the liner, the fuel pipelines extending along the extension direction of the liner, the fuel pipelines having a lumen, and the fuel pipelines communicating with the axial stage burner to supply fuel to the axial stage burner;

[0008] A flange is provided at one end of the bushing, the flange having a feed port and a fuel ring cavity, the feed port is connected to the fuel ring cavity, the fuel ring cavity is arranged along the circumference of the bushing and is connected to the tube cavity, the flange, the fuel pipeline and the bushing are formed as one piece.

[0009] The gas turbine axial stage fuel distribution device of the embodiment of the present invention has a flange, fuel pipeline and bushing integrally formed, which improves the sealing and integrity of the device, avoids the risk of fuel leakage caused by thermal displacement, vibration, etc. during the operation of the gas turbine, simplifies the structure that requires additional coordination, reduces weight, and saves costs.

[0010] In some embodiments, the flange, the fuel line, and the bushing are integrally formed using additive manufacturing technology.

[0011] In some embodiments, the fuel ring cavity has a first circumferential wall, a second circumferential wall and a bottom wall that are interconnected, the first circumferential wall is adjacent to the sleeve, the second circumferential wall is located on the outside of the first circumferential wall, the bottom wall is lower than the top surface of the flange, and there is an inclination angle a between the second circumferential wall and the bottom surface of the flange, a>45°.

[0012] In some embodiments, the flange further has a first fuel channel and a second fuel channel, the first fuel channel extends along the circumference of the flange and is connected to the feed port, there are at least two second fuel channels, at least two of the second fuel channels are arranged at intervals along the extension direction of the first fuel channel, and the second fuel channel connects the first fuel channel and the fuel ring cavity.

[0013] In some embodiments, the first fuel channel has a first side surface, a second side surface and a bottom surface connected to each other, the second side surface is located outside the first side surface and adjacent to the feed port, and an inclination angle b is formed between the first side surface and the bottom surface of the flange, b>45°.

[0014] In some embodiments, a cross-section of the first fuel channel has a polygonal profile.

[0015] In some embodiments, the cross-sectional area of ​​the first fuel passage, the cross-sectional area of ​​the second fuel passage, the cross-sectional area of ​​the fuel annulus, and the cross-sectional area of ​​the fuel pipeline are all greater than the sum of the cross-sectional areas of the fuel injection holes in the axial stage combustor.

[0016] In some embodiments, the fuel pipeline includes a first pipe segment, a second pipe segment, and a third pipe segment arranged in sequence, one end of the first pipe segment is connected to the fuel ring cavity, the other end of the first pipe segment extends toward the other end of the bushing and is connected to one end of the second pipe segment, the other end of the second pipe segment extends toward the other end of the bushing and is inclined away from the bushing, one end of the third pipe segment is connected to the other end of the second pipe segment, and the other end of the third pipe segment extends toward the other end of the bushing.

[0017] In some embodiments, an inclination angle c is formed between the second pipe section and the bottom surface of the flange, where c>45°.

[0018] In some embodiments, the flange includes a main body, an extension portion and a protrusion, the main body has a through hole, the extension portion is arranged on the top surface of the main body and is arranged around the through hole, the fuel ring cavity is arranged in the extension portion, the protrusion is arranged on the peripheral wall of the main body, the first fuel channel is arranged in the protrusion, and the second fuel channel is arranged in the main body. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Schematic diagram of a gas turbine axial stage fuel distribution device according to an embodiment of the present invention.

[0020] Figure 2 It is a schematic diagram of the manufacturing direction of the axial stage fuel distribution device of the gas turbine according to an embodiment of the present invention.

[0021] Figure 3 It is a top view of the axial stage fuel distribution device of the gas turbine according to an embodiment of the present invention.

[0022] Figure 4 Schematic diagram of a lumen of an axial stage fuel distribution device for a gas turbine according to an embodiment of the present invention.

[0023] Figure 5 yes Figure 4 Cross-sectional view along the A direction.

[0024] Figure 6 It is a partial structural schematic diagram of the gas turbine axial stage fuel distribution device according to an embodiment of the present invention.

[0025] Figure 7 yes Figure 6 Cross-sectional view in the B direction.

[0026] Figure 8 Schematic diagram of a second fuel passage of an axial stage fuel distribution device for a gas turbine according to an embodiment of the present invention.

[0027] Figure markings: 1. Bushing; 2. Fuel pipeline; 21. First pipe section; 22. Second pipe section; 23. Third pipe section; 24. Tube cavity; 3. Flange; 31. Body; 311. Perforation; 312. Second fuel channel; 32. Extension; 321. Fuel ring cavity; 3211. First circumferential wall; 3212. Second circumferential wall; 3213. Bottom wall; 33. Protrusion; 331. Feed port; 332. First fuel channel; 3321. First side surface; 3322. Second side surface; 3323. Bottom surface. DETAILED DESCRIPTION

[0028] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0029] like Figures 1-8As shown, the axial-stage fuel distribution device for a gas turbine according to an embodiment of the present invention includes a liner 1, a fuel line 2, and a flange 3. There are at least two fuel lines 2, spaced apart along the circumference of the liner 1. The fuel lines 2 extend along the extension direction of the liner 1 and have a lumen 24. The fuel lines 2 communicate with the axial-stage burner to supply fuel to the axial-stage burner. The flange 3 is provided at one end of the liner 1 and has a feed port 331 and a fuel annular lumen 321. The feed port 331 communicates with the fuel annular lumen 321. The fuel annular lumen 321 is provided along the circumference of the liner 1 and communicates with the lumen 24. The flange 3, fuel line 2, and liner 1 are integrally formed.

[0030] In the gas turbine axial stage fuel distribution device of the embodiment of the present invention, the flange 3, the fuel pipeline 2 and the bushing 1 are integrally formed, which improves the sealing and integrity of the device, avoids the risk of fuel leakage caused by thermal displacement, vibration, etc. during the operation of the gas turbine, simplifies the structure that requires additional coordination, reduces weight, and saves costs.

[0031] Specifically, there are four fuel lines 2, which are evenly spaced along the circumference of the liner 1. One end of the fuel line 2 is connected to the fuel annular cavity 321, and the other end of the fuel line 2 is connected to the axial stage burner (not shown). Fuel enters the fuel annular cavity 321 through the feed port 331, then enters the tubular cavity 24 from the fuel annular cavity 321, and finally enters the axial stage burner from the tubular cavity 24, thereby supplying fuel to the axial stage burner.

[0032] In some embodiments, the flange 3 , the fuel line 2 , and the bushing 1 are integrally formed by additive manufacturing technology and are integrally manufactured along a direction from the flange 3 to the bushing 1 .

[0033] Specifically, additive manufacturing, also known as 3D printing (3DP), is a technology that manufactures physical parts based on three-dimensional CAD data by adding materials layer by layer. The flange 3, fuel line 2, and bushing 1 are integrally formed. Compared to the prior art, the sealing interface, skin, bellows, elbow, and welded interface of the fuel line 2 are eliminated, reducing the number of parts from the original multiple to a single device, streamlining the structure. Furthermore, the original installation and disassembly procedures, such as connecting the fuel line 2, connecting the pipe section sealing interface, leading out the pipe section inlet, and the pipe section installation sequence, are streamlined to consider the installation of a whole, simplifying the installation and disassembly procedures. Furthermore, the gas turbine axial stage fuel distribution device according to the embodiment of the present invention does not require the use of traditional welding processes or sealing technologies, and does not introduce welds or sealing joints. This can prevent fuel leakage at the connection due to thermal deformation and vibration during engine operation, and provides better sealing performance.

[0034] In some embodiments, the fuel ring cavity 321 has a first circumferential wall 3211, a second circumferential wall 3212 and a bottom wall 3213 that are interconnected. The first circumferential wall 3211 is adjacent to the bushing 1, the second circumferential wall 3212 is located on the outside of the first circumferential wall 3211, and the bottom wall 3213 is lower than the top surface of the flange 3. There is an inclination angle a between the second circumferential wall 3212 and the bottom surface 3323 of the flange 3, and a>45°.

[0035] Specifically, first circumferential wall 3211 is adjacent to the outer circumferential surface of one end of bushing 1, and second circumferential wall 3212 is spaced apart from first circumferential wall 3211 at one end adjacent to bottom wall 3213. When flange 3, fuel line 2, and bushing 1 are manufactured using additive manufacturing technology, second circumferential wall 3212 is less likely to be distorted by sagging of molten material, thus avoiding the need for auxiliary supports and ensuring the effective area of ​​fuel annular cavity 321. Preferably, inclination angle a is 60°.

[0036] It is understandable that when the inclination angle a≤45°, the second peripheral wall 3212 is prone to sag due to the molten material. When additive manufacturing is performed, auxiliary supports need to be provided in the fuel ring cavity 321 to enhance the stability of the structure. However, the use of auxiliary supports will reduce the effective area of ​​the fuel ring cavity 321 and increase the fuel flow pressure loss, which is not conducive to the control of fuel supply and fuel quantity. Even if the auxiliary support structure detaches during operation and enters the downstream fuel flow channel to cause blockage, it will seriously affect the fuel supply.

[0037] In some embodiments, the flange 3 also has a first fuel channel 332 and a second fuel channel 312. The first fuel channel 332 extends along the circumference of the flange 3 and is connected to the feed port 331. There are at least two second fuel channels 312, and at least two second fuel channels 312 are arranged at intervals along the extension direction of the first fuel channel 332. The second fuel channel 312 connects the first fuel channel 332 and the fuel ring cavity 321.

[0038] Specifically, the arrangement of the first fuel channel 332 and the second fuel channel 312 facilitates fuel flow regulation. At least two second fuel channels 312 are evenly spaced along the extension direction of the first fuel channel 332 and alternate with the bolt holes on the flange 3. This facilitates fuel distribution and improves the efficiency of fuel flow from the first fuel channel 332 to the second fuel channel 312.

[0039] It can be understood that the fuel enters the first fuel channel 332, the second fuel channel 312, the fuel ring cavity 321, the tube cavity 24 in sequence through the feed port 331 and then enters the axial stage burner, thereby realizing the staged injection of fuel, making the fuel combustion process more uniform, reducing local high temperature areas, reducing the generation of NOx, and facilitating the flexible adjustment of the fuel injection amount and distribution, thereby improving combustion efficiency and operational flexibility, and enabling the gas turbine to maintain combustion stability during rapid start-up or load changes, with a wide load range adaptability, rapid start-up and response capabilities. Moreover, by rationally distributing fuel at different combustion stages, the flame propagation speed and shape in the combustion chamber are more controllable, reducing the impact of pressure fluctuations in the combustion chamber on the flame, and reducing the risk of thermoacoustic oscillations. Lower combustion oscillations enable the gas turbine to operate more smoothly under different operating conditions, reducing energy loss and equipment failure risks due to unstable combustion.

[0040] In some embodiments, the first fuel channel 332 has a first side surface 3321, a second side surface 3322 and a bottom surface 3323 that are interconnected. The second side surface 3322 is located outside the first side surface 3321 and adjacent to the feed port 331. There is an inclination angle b between the first side surface 3321 and the bottom surface 3323 of the flange 3, and b>45°.

[0041] Specifically, the inclination angle b>45°, ensuring that the first side surface 3321 has self-supporting ability, avoiding the use of auxiliary support during additive manufacturing, ensuring the effective area within the first fuel channel 332, and facilitating fuel flow. Preferably, the inclination angle b is 60°.

[0042] In some embodiments, the cross-section of the first fuel passage 332 has a polygonal profile.

[0043] Specifically, the cross-section of the first fuel channel 332 is in the shape of an equilateral triangle, which ensures that the structure of the first fuel channel 332 is stable and does not require auxiliary support during manufacturing.

[0044] In some embodiments, the cross-sectional area of ​​the first fuel channel 332, the cross-sectional area of ​​the second fuel channel 312, the cross-sectional area of ​​the fuel ring cavity 321, and the cross-sectional area of ​​the tube cavity 24 are all a certain multiple greater than the sum of the cross-sectional areas of all the fuel nozzles in the axial stage burner, thereby ensuring that the fuel flow of each fuel nozzle of the axial stage burner is evenly distributed and reducing the pressure loss.

[0045] In some embodiments, the fuel pipeline 2 includes a first pipe segment 21, a second pipe segment 22 and a third pipe segment 23 arranged in sequence, one end of the first pipe segment 21 is connected to the fuel ring cavity 321, the other end of the first pipe segment 21 extends toward the other end of the bushing 1 and is connected to one end of the second pipe segment 22, the other end of the second pipe segment 22 extends toward the other end of the bushing 1 and is inclined in a direction away from the bushing 1, one end of the third pipe segment 23 is connected to the other end of the second pipe segment 22, and the other end of the third pipe segment 23 extends toward the other end of the bushing 1.

[0046] Specifically, one end of the first pipe section 21 is embedded in the fuel annular cavity 321 to ensure sealing between the first pipe section 21 and the fuel annular cavity 321. The fuel pipeline 2 has a simple structure and is easy to manufacture.

[0047] In some embodiments, an inclination angle c is formed between the second pipe section 22 and the bottom surface 3323 of the flange 3 , where c>45°.

[0048] Specifically, the inclination angle c is greater than 45°, ensuring that the second pipe section 22 has self-supporting ability, avoiding the use of auxiliary supports during additive manufacturing, ensuring the effective area within the second pipe section 22, and facilitating fuel flow. Preferably, the inclination angle c is 65°.

[0049] In some embodiments, the flange 3 includes a main body 31, an extension portion 32 and a protrusion 33, the main body 31 has a through-hole 311, the extension portion 32 is arranged on the top surface of the main body 31 and is arranged around the through-hole 311, the fuel ring cavity 321 is arranged on the extension portion 32, the protrusion 33 is arranged on the peripheral wall of the main body 31, the first fuel channel 332 is arranged on the protrusion 33, and the second fuel channel 312 is arranged on the main body 31.

[0050] Specifically, the fuel ring cavity 321, the first fuel channel 332 and the second fuel channel 312 are all arranged on the flange 3, and do not occupy the internal and external space of the combustion chamber. Compared with the existing technology, the number of parts is greatly reduced, the structure is streamlined, the flow process is reduced, and the weight is reduced.

[0051] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0052] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0053] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0054] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0055] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0056] Although the above embodiments have been shown and described, it is understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those skilled in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine axial stage fuel distribution device, characterized in that: include: Bushing (1); A fuel pipeline (2), wherein the fuel pipeline (2) is at least two and the at least two fuel pipelines (2) are arranged at intervals along the circumference of the liner (1), the fuel pipeline (2) extends along the extension direction of the liner (1), the fuel pipeline (2) has a lumen (24), and the fuel pipeline (2) is in communication with the axial stage burner to supply fuel to the axial stage burner; A flange (3), the flange (3) being arranged at one end of the bushing (1), the flange (3) having a feed port (331) and a fuel annular cavity (321), the feed port (331) being communicated with the fuel annular cavity (321), the fuel annular cavity (321) being arranged along the circumference of the bushing (1) and being communicated with the tube cavity (24), the flange (3), the fuel pipeline (2) and the bushing (1) being integrally formed.

2. The gas turbine axial stage fuel distribution device according to claim 1, characterized in that: The flange (3), the fuel pipeline (2) and the bushing (1) are integrally formed by means of additive manufacturing technology.

3. The gas turbine axial stage fuel distribution device according to claim 1, characterized in that: The fuel ring cavity (321) has a first circumferential wall (3211), a second circumferential wall (3212) and a bottom wall (3213) which are connected to each other, wherein the first circumferential wall (3211) is adjacent to the bushing (1), the second circumferential wall (3212) is located on the outside of the first circumferential wall (3211), and the bottom wall (3213) is lower than the top surface of the flange (3), and an inclination angle a is formed between the second circumferential wall (3212) and the bottom surface (3323) of the flange (3), and a>45°.

4. The gas turbine axial stage fuel distribution device according to claim 1, characterized in that: The flange (3) further comprises a first fuel channel (332) and a second fuel channel (312), wherein the first fuel channel (332) extends along the circumference of the flange (3) and is connected to the feed port (331), and there are at least two second fuel channels (312), and at least two second fuel channels (312) are arranged at intervals along the extension direction of the first fuel channel (332), and the second fuel channel (312) connects the first fuel channel (332) and the fuel annular cavity (321).

5. The gas turbine axial stage fuel distribution device according to claim 4, characterized in that: The first fuel channel (332) has a first side surface (3321), a second side surface (3322) and a bottom surface (3323) that are connected to each other, the second side surface (3322) is located outside the first side surface (3321) and adjacent to the feed port (331), and an inclination angle b is formed between the first side surface (3321) and the bottom surface (3323) of the flange (3), where b>45°.

6. The gas turbine axial stage fuel distribution device according to claim 4, characterized in that: The cross-section of the first fuel channel (332) is polygonal in outline.

7. The gas turbine axial stage fuel distribution device according to claim 4, characterized in that: The cross-sectional area of ​​the first fuel channel (332), the cross-sectional area of ​​the second fuel channel (312), the cross-sectional area of ​​the fuel annular cavity (321), and the cross-sectional area of ​​the fuel pipeline (2) are all greater than the sum of the cross-sectional areas of the fuel injection holes in the axial stage burner.

8. The gas turbine axial stage fuel distribution device according to claim 1, characterized in that: The fuel pipeline (2) comprises a first pipe section (21), a second pipe section (22) and a third pipe section (23) which are arranged in sequence, one end of the first pipe section (21) is connected to the fuel ring cavity (321), the other end of the first pipe section (21) extends toward the other end of the bushing (1) and is connected to one end of the second pipe section (22), the other end of the second pipe section (22) extends toward the other end of the bushing (1) and is inclined in a direction away from the bushing (1), one end of the third pipe section (23) is connected to the other end of the second pipe section (22), and the other end of the third pipe section (23) extends toward the other end of the bushing (1).

9. The gas turbine axial stage fuel distribution device according to claim 8, characterized in that: There is an inclination angle c between the second pipe section (22) and the bottom surface (3323) of the flange (3), and c>45°.

10. The gas turbine axial stage fuel distribution device according to claim 4, characterized in that: The flange (3) includes a main body (31), an extension portion (32) and a protrusion (33); the main body (31) has a through hole (311); the extension portion (32) is arranged on the top surface of the main body (31) and surrounds the through hole (311); the fuel annular cavity (321) is arranged on the extension portion (32); the protrusion (33) is arranged on the peripheral wall of the main body (31); the first fuel channel (332) is arranged on the protrusion (33); and the second fuel channel (312) is arranged on the main body (31).

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