Combustion can, combustor for a gas turbine, and gas turbine

Abstract

A combustor of a gas turbine according to at least one of the embodiments of the present application includes a combustor, a plurality of fuel nozzles arranged at intervals in a circumferential direction of the combustor at a side portion of the combustor, and a windbreak wall provided between a compressed air outlet for ejecting compressed air from a compressor into a combustor chamber and the plurality of fuel nozzles. The windbreak wall has a first wall portion extending in the circumferential direction of the combustor, and a second wall portion extending in an axial direction of the combustor from an end portion of the circumferential direction of the first wall portion toward an upstream side of a flow of combustion gas flowing inside the combustor.

Description

Technical Field

[0001] This invention relates to a combustion chamber for a gas turbine, a burner for a gas turbine, and a gas turbine.

[0002] This application claims priority based on Japanese Patent Application No. 2024-058483, filed with the Japan Patent Office on April 1, 2024, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine burner is known to supply fuel into the combustion chamber from a fuel nozzle located on the side of the combustion chamber. In this gas turbine burner, compressed air compressed by a compressor is introduced from the periphery of the gas turbine burner into the interior of the combustion chamber as combustion air (see, for example, Patent Document 1).

[0004] Existing technical documents

[0005] Patent documents

[0006] Patent Document 1: Japanese Patent Application Publication No. 2017-166808 Summary of the Invention

[0007] The problem that the invention aims to solve

[0008] Typically, in industrial gas turbines, multiple burners are arranged in a ring around the rotor. Compressed air from the compressor is supplied to the burner chamber in a region further radially inward of the rotor than in a system where multiple burners are arranged in a ring around the rotor. Therefore, due to the relatively high velocity of the compressed air exiting the compressor, the flow of compressed air supplied to one or more fuel nozzles located on the side of the combustion chamber may deviate circumferentially and within each nozzle. This deviation results in an uneven fuel concentration distribution injected into the combustion chamber from the nozzle, potentially leading to NO₂. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0009] In view of the above, at least one embodiment of the present invention aims to reduce the impact of the relatively fast flow of compressed air ejected from the compressor outlet into the burner chamber.

[0010] Methods for solving problems

[0011] (1) The combustion chamber of the gas turbine according to at least one embodiment of the present invention comprises:

[0012] Combustion tube;

[0013] Multiple fuel nozzles are spaced apart along the circumference of the combustion chamber on the side of the combustion chamber; and

[0014] A windbreak is disposed between the compressed air outlet for injecting compressed air from the compressor into the burner chamber and the plurality of fuel nozzles.

[0015] The windbreak wall has the following features:

[0016] The first wall portion extends circumferentially along the combustion cylinder; and

[0017] The second wall portion extends axially along the combustion cylinder from the circumferential end of the first wall portion toward the upstream side of the flow of combustion gas flowing inside the combustion cylinder.

[0018] (2) The combustor of the gas turbine according to at least one embodiment of the present invention comprises:

[0019] The combustion chamber of the gas turbine with the structure described in (1) above; and

[0020] A burner, located upstream of the combustion chamber, is used to burn fuel.

[0021] (3) The gas turbine according to at least one embodiment of the present invention comprises:

[0022] Rotor; and

[0023] The burner with the structure described above (2) has multiple burners arranged in a ring around the rotor.

[0024] Invention Effects

[0025] According to at least one embodiment of the present invention, the objective is to reduce the impact of the relatively fast flow of compressed air ejected from the compressor outlet into the burner chamber. Attached Figure Description

[0026] Figure 1 This is a schematic structural diagram of a gas turbine involved in one implementation method.

[0027] Figure 2 This is a schematic diagram showing the burner and turbine inlet portion of a gas turbine according to one embodiment.

[0028] Figure 3 yes Figure 2 Enlarged view of the main parts.

[0029] Figure 4 It is a schematic representation Figure 3 A diagram of the AA-direction view section. Detailed Implementation

[0030] Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc., of the constituent parts described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0031] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicate relative or absolute configuration. They not only indicate such configuration in a strict sense, but also indicate a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0032] For example, expressions such as "same," "identical," and "homogeneous" that indicate things are in the same state not only indicate the same state in a strict sense, but also indicate the state where there are differences in tolerance or degree to which the same function can be obtained.

[0033] For example, descriptions of shapes such as quadrilaterals and cylinders not only refer to quadrilaterals and cylinders in a strict geometric sense, but also include shapes with concave and convex parts, chamfers, etc., within the range where the same effect can be obtained.

[0034] On the other hand, the expression "possessing," "having," "including," "containing," or "having" a constituent element is not an exclusive expression that excludes the existence of other constituent elements.

[0035] First, refer to Figure 1 Hereinafter, we will describe a gas turbine as an example of an application of the combustion chamber according to one embodiment. Figure 1 This is a schematic structural diagram of a gas turbine involved in one implementation method.

[0036] like Figure 1 As shown, the gas turbine 1 includes: a compressor 2 for generating compressed air; a gas turbine combustor 4 for generating combustion gases using compressed air and fuel; and a turbine 6 configured to be driven by the rotation of the combustion gases. In the case of a gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0037] The compressor 2 includes a plurality of stationary blades 16 fixed to the side of the compressor housing 10 and a plurality of moving blades 18 installed on the rotor 8 in an alternating manner with the stationary blades 16.

[0038] Air introduced from air inlet 12 is sent to compressor 2, where it is compressed by multiple stationary blades 16 and multiple moving blades 18, thus becoming high-temperature and high-pressure compressed air.

[0039] Fuel and compressed air generated by compressor 2 are supplied to combustor 4, where the fuel is burned to generate combustion gases that serve as the working fluid of turbine 6. Figure 1 As shown, the gas turbine 1 has a plurality of burners 4 arranged circumferentially around the rotor 8 within the casing 20.

[0040] The turbine 6 has a combustion gas passage 28 formed by the turbine house 22, and includes a plurality of stationary blades 24 and moving blades 26 disposed in the combustion gas passage 28. The stationary blades 24 and moving blades 26 of the turbine 6 are disposed downstream of the combustor 4 relative to the flow of the combustion gas.

[0041] Stationary blades 24 are fixed to the side of the engine room 22, and multiple stationary blades 24 arranged circumferentially along the rotor 8 constitute a stationary blade row. Moving blades 26 are mounted on the rotor 8, and multiple moving blades 26 arranged circumferentially along the rotor 8 constitute a moving blade row. The stationary blade rows and moving blade rows are arranged alternately in the axial direction of the rotor 8.

[0042] In turbine 6, combustion gases from burner 4 flow into combustion gas passage 28, driving rotor 8 to rotate around axis O via multiple stationary blades 24 and multiple moving blades 26. This drives a generator connected to rotor 8 to generate electricity. The combustion gases driving turbine 6 are then discharged to the outside via exhaust chamber 30.

[0043] Next, a burner 4 according to one embodiment will be described.

[0044] Figure 2 This is a schematic diagram showing the burner 4 and the inlet portion of the turbine 6 of the gas turbine 1 according to one embodiment.

[0045] In one embodiment of the gas turbine 1, a plurality of burners 4 are arranged circumferentially around the rotor 8 (see reference). Figure 1 The device includes a combustion tube (burner bushing) 36 disposed in a burner chamber 32 defined by the housing 20, a first combustion burner 38 disposed within the combustion tube 36, and a plurality of second combustion burners 44 disposed around the first combustion burner 38. That is, the combustion tube 36, the first combustion burner 38, and the second combustion burners 44 are housed within the housing 20.

[0046] The combustion tube (burner bushing) 36 has an inner cylinder 48 disposed around the first combustion burner 38 and a plurality of second combustion burners 44, and a tail cylinder 50 connected to the front end of the inner cylinder 48. Alternatively, the inner cylinder 48 and the tail cylinder 50 may be formed as one piece.

[0047] An acoustic device 60 for attenuating combustion vibrations is provided on the outer periphery of the combustion cylinder 36.

[0048] The first combustion burner 38 is arranged along the central axis C1 of the combustion chamber 36 (i.e., the axial direction of the burner 4 and the combustion chamber 36) and has a first fuel nozzle 40 for injecting fuel. Fuel is supplied to the first fuel nozzle 40 via a first fuel port 42.

[0049] The second combustion burner 44 has a second fuel nozzle 46 for injecting fuel. Fuel is supplied to the second fuel nozzle 46 via a second fuel port 43.

[0050] The burner 4 also includes an outer cylinder 52 disposed inside the housing 20 on the outer periphery of the inner cylinder 48. An air passage 54 for compressed air flow is formed on the outer periphery of the inner cylinder 48 and the inner periphery of the outer cylinder 52.

[0051] Compressor 2 (reference) Figure 1 The generated compressed air is supplied from diffuser outlet 31a to the burner chamber 32 via diffuser 31 of compressor 2. This compressed air, as combustion air, flows from the burner chamber 32 into the air passage 54, and after changing direction on the wall surface 53 provided along a surface orthogonal to the axial direction of burner 4, flows into the first burner tube 41 and the second burner tube 47. Then, in each burner tube, fuel injected from the fuel nozzle and compressed air (combustion air) are mixed. This mixture flows into the combustion tube 36 and is ignited and burned, thereby producing combustion gases.

[0052] Combustion gases produced by the combustion of fuel in burner 4 flow into turbine 6 via the outlet 51 of burner 4, located at the downstream end of tailpipe 50. Figure 2 and Figure 3 In the diagram, arrow FG indicates the direction of combustion gas flow within the combustion chamber 36.

[0053] (Third fuel nozzle 70)

[0054] Figure 3 yes Figure 2 Enlarged view of the main parts.

[0055] Figure 4 It is a schematic representation Figure 3 The diagram shows the IV-IV view section, representing the section viewed along the central axis of the combustion chamber.

[0056] like Figure 4As shown, in one embodiment, the burner 4 includes a plurality of third fuel nozzles 70, which are disposed on the side of the combustion chamber 36 and spaced apart along a circumferential direction centered on the central axis C1 (i.e., the circumferential direction of the burner 4 and the combustion chamber 36). That is, the third fuel nozzles 70 are fuel nozzles for supplying fuel from the side of the combustion chamber 36 into the combustion chamber 36.

[0057] The third fuel nozzle 70 is, for example, fixed to the tailpipe 50.

[0058] exist Figure 2 and Figure 3 The description of the third fuel nozzle 70 is omitted.

[0059] In one embodiment of the third fuel nozzle 70, an intake port (not shown) for the inflow of compressed air from the burner chamber 32 is provided around the entire circumference of the third fuel nozzle 70, which extends from the outside of the combustion chamber 36 toward the inside. Compressed air from the burner chamber 32 flows into the third fuel nozzle 70 from the radially outer side centered on the central axis C2, and then into the combustion chamber 36 from the third fuel nozzle 70.

[0060] Fuel is supplied via fuel port 3, 74 (reference). Figure 2 (It) is supplied to the third fuel nozzle 70. Additionally, in Figures 2 to 4 The description of the fuel supply pipe from the third fuel port 74 to each of the third fuel nozzles 70 is omitted.

[0061] For example, such as Figure 4 As shown, in one embodiment of the burner 4, for example, four third fuel nozzles 70 are arranged at intervals along the circumference of the combustion chamber 36. Furthermore, in one embodiment of the burner 4, as... Figure 4 As shown, the third fuel nozzle 70 can be configured on one side and the other side of the rotor 8 in the circumferential direction, separated by a first imaginary straight line LV1 that passes through the central axis C1 when viewed along the central axis C1 and extends radially along the rotor 8. In a burner 4 according to one embodiment, the third fuel nozzle 70 can be configured on one side and the other side of the rotor 8 in the radial direction, separated by a second imaginary straight line LV2 that passes through the central axis C1 and is orthogonal to the first imaginary straight line LV1 when viewed along the central axis C1.

[0062] In addition, such as Figure 2 and Figure 3 As shown, in one embodiment of the burner 4, as Figure 2 and Figure 3As shown, the extension direction of the combustion chamber 36 changes in the downstream region of the combustion gas flow, indicated by arrow FG. Specifically, in the downstream region of the combustion gas flow, the central axis C1 of the combustion chamber 36 changes its extension direction along the axial direction of the rotor 8 as it moves towards the downstream side of the combustion gas flow. Therefore, this curved central axis C1 is contained within an imaginary plane PV that includes the axis O of the rotor 8 and extends radially along the rotor 8. In other words, the central axis C1 is curved within the imaginary plane PV in the downstream region of the combustion gas flow in the combustion chamber 36.

[0063] In addition, the aforementioned first imaginary line LV1 is also contained in the imaginary plane PV.

[0064] In addition, the number of third fuel nozzles 70 provided in a burner 4 in one embodiment is not limited to four, as long as there is one or more, such as two, three or more.

[0065] If fuel is injected into the combustion chamber 36 through the third fuel nozzle 70, the combustion air inside the combustion chamber 36 mixes with the injected fuel and undergoes combustion. By injecting fuel into the combustion chamber 36 through the third fuel nozzle 70, fuel can be supplied to a secondary combustion zone downstream of the primary combustion zone from the first fuel nozzle 40 and the second fuel nozzle 46. This allows for the suppression of nitrogen oxides (NOx). x This generates [something] and improves combustion efficiency.

[0066] In addition, the burner 4 may include other components such as a bypass pipe (not shown) for bypassing the combustion gases.

[0067] (Regarding the necessity of windbreak wall 100)

[0068] The necessity of the windbreak wall 100, which will be described later, will be explained.

[0069] In a typical industrial gas turbine, including the gas turbine 1 described in one embodiment, multiple burners 4 are arranged in a ring around the rotor 8. Combustion compressed air from the compressor 2 is supplied to the burner chamber 32 in a region further radially inward of the rotor 8 than the multiple burners 4 arranged in a ring around the rotor 8. Therefore, due to the relatively fast flow velocity of the compressed air ejected from the outlet (diffuser outlet 31a) of the compressed air from the compressor 2, the flow of compressed air supplied to the third fuel nozzle 70 located on the side of the combustion chamber 36 may deviate circumferentially about the central axis C2 of the third fuel nozzle 70. If this deviation occurs, it will result in a fuel concentration distribution from the third fuel nozzle 70 into the combustion chamber 36, potentially leading to NO₂.x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0070] Therefore, in some embodiments of the burner 4, by providing the windproof wall 100 described later, the third fuel nozzle 70 is less susceptible to the influence of the relatively fast flow of compressed air ejected from the diffuser outlet 31a, thereby suppressing the flow deviation of combustion air in the plurality of third fuel nozzles 70 as described above.

[0071] (Regarding the structure of windbreak wall 100)

[0072] like Figures 2 to 4 As shown, in one embodiment, the windbreak 100 is a plate-shaped component erected radially from the outer peripheral surface 36a (outer peripheral surface 50a of the tail cylinder 50) of the combustion cylinder 36, such as... Figure 3 and Figure 4 As shown, it has: a first wall portion 101 extending circumferentially along the combustion cylinder 36; and a second wall portion 102 extending axially from the circumferential end 101a of the first wall portion 101 toward the upstream side of the flow of combustion gas flowing inside the combustion cylinder 36.

[0073] In one embodiment, a windbreak 100 is disposed between a diffuser outlet 31a, which serves as a compressed air outlet for injecting compressed air from the compressor 2 into the burner chamber 32, and a plurality of third fuel nozzles 70.

[0074] In order to make the third fuel nozzle 70 less susceptible to the relatively fast flow of compressed air ejected from the diffuser outlet 31a, the windproof wall 100 can be configured such that each third fuel nozzle 70 is hidden on the back side of the windproof wall 100 when viewed from the diffuser outlet 31a.

[0075] Therefore, the height of the windbreak wall 100 in the radial direction of the combustion tube 36 can be set such that each of the third fuel nozzles 70 is hidden behind the windbreak wall 100 when viewed from the diffuser outlet 31a.

[0076] Here, at a position further radially inward from the rotor 8 than the multiple burners 4 adjacent to the rotor 8 in the circumferential direction, such as... Figure 3 As indicated by arrow a, compressor 2 (reference) Figure 1 The generated compressed air is supplied to the burner chamber 32 via diffuser outlet 31a.

[0077] One embodiment of the windbreak wall 100 is configured such that, when viewed from the diffuser outlet 31a, the third fuel nozzle 70 is hidden on the back side of the first wall portion 101 or the second wall portion 102 extending circumferentially along the combustion cylinder 36.

[0078] Therefore, as Figure 3 As indicated by arrow a, the relatively fast-flowing compressed air is blocked by the first wall portion 101 or the second wall portion 102, and therefore does not flow directly toward the third fuel nozzle 70. Thus, through the first wall portion 101 or the second wall portion 102, the third fuel nozzle 70 is less affected by the relatively fast-flowing compressed air ejected from the diffuser outlet 31a.

[0079] Thus, in the burner 4 according to one embodiment, by providing the windbreak wall 100 according to one embodiment, the influence of the relatively fast flow of compressed air ejected from the diffuser outlet 31a into the burner chamber 32 can be reduced with a relatively simple structure, thereby reducing the generation of NO. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0080] Some embodiments of the burner 4 include: a combustion chamber 36 of the gas turbine 1 with the above-described structure; and a first combustion burner 38 and a second combustion burner 44, which are disposed on the upstream side of the combustion chamber 36, that is, on the upstream side of the flow of combustion gas, for burning fuel.

[0081] Therefore, NO is not easily generated in burner 4. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0082] Some embodiments of the gas turbine 1 include: a rotor 8; and a burner 4 with the above-described structure, with a plurality of burners arranged in a ring around the rotor 8.

[0083] Therefore, NO is not easily generated in gas turbine 1. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0084] In one embodiment, the windbreak 100 does not have a component that overlaps with each of the third fuel nozzles 70 when the combustion chamber 36 is viewed radially from the outside of the combustion chamber 36, i.e., it covers each of the third fuel nozzles 70 radially from the outside. As a result, it facilitates the installation of the third fuel nozzles 70 or components arranged around them onto the combustion chamber 36, facilitates maintenance of the third fuel nozzles 70, and reduces costs.

[0085] In one embodiment of the windbreak wall 100, the second wall portion 102 extends axially along the combustion cylinder 36 from the ends 101a of the first wall portion 101 on one and the other side of the circumferential direction relative to the combustion cylinder 36, respectively, toward the upstream side of the flow of combustion gases. That is, the second wall portion 102 is provided at both ends of the first wall portion 101 in the circumferential direction relative to the combustion cylinder 36.

[0086] This further reduces the impact of the relatively fast flow of compressed air ejected from diffuser outlet 31a into burner chamber 32.

[0087] One embodiment of the windbreak wall 100 may include a connecting portion 103 that connects a first wall portion 101 and a second wall portion 102 and has a curved surface that bends from the first wall portion 101 to the second wall portion 102. The connecting portion 103 has a curved surface that, within the space between the first wall portion 101 and the second wall portion 102, i.e., in... Figure 3 The space located upstream of the combustion gas flow than the first wall portion 101 and radially inward of the rotor 8 than the second wall portion 102 has a center of curvature.

[0088] Therefore, compared to the case where the first wall portion 101 and the second wall portion 102 are not connected by a curved surface based on the connecting portion 103, the possibility of unexpected turbulence in the flow of compressed air in the burner chamber 32 is reduced, and thermal stress is less likely to concentrate on the windproof wall 100.

[0089] Here, for example, Figure 4 As shown, in the cross section of the combustion cylinder 36 orthogonal to the central axis C1 of the combustion cylinder 36, the following position is taken as the reference position Pr: the intersection of the imaginary straight line (second imaginary straight line LV2) extending along the normal direction of the imaginary plane (imaginary plane PV) of the combustion cylinder 36 that includes the central axis C1 of the combustion cylinder 36 which changes in the extension direction with the combustion cylinder 36 (for example, the intersection with the outer peripheral surface 36a of the combustion cylinder 36).

[0090] In one embodiment of the windbreak wall 100, the second wall portion 102 may be configured in a region R in which the absolute value of the difference Δθ between the circumferential angular positions of the combustion cylinder 36 centered on the reference position Pr is within 15 degrees.

[0091] Therefore, compared to the case where the second wall portion 102 is located outside the range of region R, the influence of the relatively fast flow of compressed air can be effectively reduced.

[0092] For example, such as Figure 3 and Figure 4 As clearly shown, in one embodiment of the windbreak wall 100, the first wall portion 101 may be positioned closer to the diffuser outlet 31a in the circumferential direction of the combustion tube 36 than the second wall portion 102.

[0093] Therefore, the influence of the relatively fast flow of compressed air can be effectively reduced. Furthermore, in the burner 4 according to one embodiment, the combustion chamber 36 is inclined toward the radially inner side of the rotor 8 as it flows toward the downstream side of the combustion gas. Therefore, by configuring the first wall portion 101, which is located closer to the diffuser outlet 31a in the circumferential direction of the combustion chamber 36 than the second wall portion 102, the influence of the relatively fast flow of compressed air can be effectively reduced.

[0094] The present invention is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments or appropriate combinations thereof.

[0095] The contents described in the above embodiments can be understood as follows, for example.

[0096] (1) The combustor 36 of the gas turbine 1 according to at least one embodiment of the present invention is the combustor 36 of the gas turbine 1. The combustor 36 of the gas turbine 1 according to at least one embodiment of the present invention includes: a combustor 36; a plurality of fuel nozzles (third fuel nozzles 70) arranged at intervals along the circumference of the combustor 36 on the side of the combustor 36; and a windbreak wall 100 disposed between a compressed air outlet (diffuser outlet 31a) for injecting compressed air from the compressor 2 into the burner chamber 32 and the plurality of fuel nozzles (third fuel nozzles 70). The windbreak wall 100 has: a first wall portion 101 extending along the circumference of the combustor 36; and a second wall portion 102 extending axially along the combustor 36 from the aforementioned circumferential end 101a of the first wall portion 101 toward the upstream side of the flow of combustion gas flowing inside the combustor 36.

[0097] According to the structure described in (1) above, since a windbreak wall 100 is provided between the compressed air outlet (diffuser outlet 31a) and the multiple fuel nozzles (third fuel nozzle 70), the influence of the relatively fast flow velocity of the compressed air ejected from the compressor outlet (diffuser outlet 31a) into the burner chamber 32 can be reduced. Therefore, NO generation is less likely. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0098] (2) In some embodiments, in the structure described in (1) above, the second wall portion 102 may extend along the axial direction from the end 101a of the first wall portion 101 on one side and the other side of the circumferential direction.

[0099] According to the structure described in (2) above, since the second wall portion 102 is provided on one side and the other side of the end 101a of the first wall portion 101 in the circumferential direction, the influence of the relatively fast flow of compressed air ejected from the compressor outlet (diffuser outlet 31a) into the burner chamber 32 can be further reduced.

[0100] (3) In some embodiments, in the structure described in (1) or (2) above, a connecting portion 103 may be provided, which connects the first wall portion 101 and the second wall portion 102 and has a curved surface that bends from the first wall portion 101 to the second wall portion 102.

[0101] According to the structure described above (3), compared to the case where the first wall portion 101 and the second wall portion 102 are not connected by a curved surface based on the above-described connecting portion 103, the possibility of unexpected turbulence in the flow of compressed air in the burner chamber 32 is reduced, and thermal stress is less likely to concentrate on the windproof wall 100.

[0102] (4) In some embodiments, in any of the structures described in (1) to (3) above, the extension direction of the combustion tube 36 may change in the downstream region of the combustion gas flow. In a cross-section of the combustion tube 36 orthogonal to the central axis C1 of the combustion tube 36, the following position is taken as the reference position Pr: the intersection of the combustion tube 36 with an imaginary straight line (second imaginary straight line LV2) orthogonal to the imaginary plane (imaginary plane PV) containing the central axis C1 of the combustion tube 36 whose extension direction has changed. The second wall portion 102 may be disposed in a region R centered on the reference position Pr, where the absolute value of the difference Δθ between the aforementioned circumferential angular positions is within 15 degrees.

[0103] According to the structure described above (4), compared to the case where the second wall portion 102 is located outside the range of the aforementioned region R, the influence of the relatively fast flow of compressed air can be effectively reduced.

[0104] (5) In some embodiments, in any of the structures in (1) to (3) above, the first wall portion 101 may be positioned closer to the compressed air outlet (diffuser outlet 31a) in the circumferential direction than the second wall portion 102.

[0105] Based on the structure described in (5) above, the influence of relatively fast flow of compressed air can be effectively reduced.

[0106] (6) The combustor 4 of the gas turbine 1 according to at least one embodiment of the present invention includes: a combustion chamber 36 of the gas turbine 1 with any of the structures in (1) to (5) above; and a burner (a first combustion burner 38 and a second combustion burner 44) disposed on the upstream side of the combustion chamber 36 for burning fuel.

[0107] Based on the structure described in (6) above, NO is not easily generated in the burner 4 of the gas turbine 1. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0108] (7) The gas turbine 1 according to at least one embodiment of the present invention includes: a rotor 8; and a burner 4 with the structure of (6) above, with a plurality of burners arranged in a ring around the rotor 8.

[0109] Based on the structure described in (7) above, NO is not easily generated in gas turbine 1. x This could lead to adverse conditions such as locally increased concentrations or an increased risk of backfire.

[0110] Symbol explanation:

[0111] 1-Gas turbine, 2-Compressor, 4-Gas turbine burner, 6-Turbine, 8-Rotor, 20-Casing, 31-Diffuser, 31a-Diffuser outlet, 32-Burner chamber, 36-Burner casing (burner bushing), 50-Tail stack, 70-Third fuel nozzle, 100-Windproof wall, 101-First wall section, 101a-End section, 102-Second wall section, 103-Connecting section.

Claims

1. A combustion chamber for a gas turbine, comprising: Combustion tube; Multiple fuel nozzles are spaced apart along the circumference of the combustion chamber on the side of the combustion chamber; and A windbreak is disposed between the compressed air outlet for injecting compressed air from the compressor into the burner chamber and the plurality of fuel nozzles. The windbreak wall has the following features: The first wall portion extends circumferentially along the combustion cylinder; and The second wall portion extends axially along the combustion cylinder from the circumferential end of the first wall portion toward the upstream side of the flow of combustion gas flowing inside the combustion cylinder.

2. The combustion chamber of the gas turbine according to claim 1, wherein, The second wall portion extends axially from one end of the first wall portion in the circumferential direction and the other end toward the upstream side.

3. The combustion chamber of the gas turbine according to claim 1 or 2, comprising a connecting portion that connects the first wall portion and the second wall portion and has a curved surface that bends from the first wall portion to the second wall portion.

4. The combustion chamber of the gas turbine according to claim 1 or 2, wherein, The direction of extension of the combustion chamber changes in the downstream region of the combustion gas flow. In a cross-section of the combustion cylinder orthogonal to its central axis, the following position is taken as a reference position: the intersection of the combustion cylinder with an imaginary straight line orthogonal to an imaginary plane containing the central axis of the combustion cylinder (where the extension direction changes) and an imaginary straight line passing through the central axis. The second wall portion is disposed in a region where the absolute value of the difference in circumferential angular position centered on the reference position is within 15 degrees.

5. The combustion chamber of the gas turbine according to claim 1 or 2, wherein, The first wall portion is positioned closer to the compressed air outlet in the circumferential direction than the second wall portion.

6. A combustor for a gas turbine, comprising: The combustion chamber of the gas turbine as described in claim 1 or 2; and A burner, located upstream of the combustion chamber, is used to burn fuel.

7. A gas turbine, comprising: Rotor; and The burner of claim 6 has a plurality of burners arranged in a ring around the rotor.

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