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

Abstract

A combustor of a gas turbine according to at least one embodiment of the present invention 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 wind shield arranged to surround at least one of the plurality of fuel nozzles. The wind shield includes a top plate extending in the circumferential direction and a circumferential side wall connecting an end portion of the circumferential direction in the top plate and the combustor. The wind shield is composed of the top plate and the circumferential side wall, and has a suction opening portion for introducing combustion air. In at least a part of the circumferential direction, a dimension of the combustor in a radial direction in the suction opening portion is smaller than a dimension of the circumferential direction in the suction opening portion.

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 U.S. Patent and Trademark Office application No. 63 / 418,154, filed October 21, 2022, 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] Previous technical documents

[0005] Patent documents

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

[0007] The technical problem to be solved by the invention

[0008] Typically, in industrial gas turbines, multiple burners are arranged in a ring around the rotor, resulting in relatively narrow spacing between adjacent burners. Consequently, the flow velocity of combustion air flowing between the combustion chambers of adjacent burners becomes relatively fast. As a result, the flow rate of combustion air into the fuel nozzles located on the sides of the combustion chambers is largely influenced by the circumferential position of the combustion chambers where the fuel nozzles are located. However, the aforementioned patent documents do not specifically address suppressing the influence caused by the circumferential position of the combustion chambers where the fuel nozzles are located.

[0009] In view of the above, at least one embodiment of the present invention aims to provide a combustion chamber for a gas turbine that can suppress flow deviation of combustion air between a plurality of fuel nozzles arranged circumferentially spaced along the combustion chamber, and can suppress pressure loss of combustion air flowing into the fuel nozzles.

[0010] means for solving technical problems

[0011] (1) A combustion chamber for a gas turbine according to at least one embodiment of the present invention comprises: a combustion chamber; a plurality of fuel nozzles spaced apart along the circumference of the combustion chamber on the side of the combustion chamber; and a wind shield configured to surround at least one of the plurality of fuel nozzles, the wind shield comprising: a top plate extending along the circumference; and a circumferential sidewall connecting the circumferential end of the top plate to the combustion chamber, the wind shield being formed by the top plate and the circumferential sidewall, and having an intake opening for introducing combustion air, wherein the radial dimension of the combustion chamber in the intake opening is smaller than the circumferential dimension in at least a portion of the circumferential region.

[0012] (2) The combustor of the gas turbine according to at least one embodiment of the present invention comprises:

[0013] The combustion chamber with the structure described in (1) above; and

[0014] A combustion furnace is located upstream of the combustion cylinder and is used to burn fuel.

[0015] (3) The gas turbine according to at least one embodiment of the present invention includes: a rotor; and a combustor with the structure of (2) above, wherein a plurality of such combustors are arranged in a ring around the rotor.

[0016] Invention Effects

[0017] According to at least one embodiment of the present invention, it is possible to suppress the flow rate deviation of combustion air between a plurality of fuel nozzles arranged circumferentially spaced along the combustion chamber, and to suppress the pressure loss of combustion air flowing into the fuel nozzles. Attached Figure Description

[0018] Figure 1 This is a schematic structural diagram of a gas turbine according to one embodiment.

[0019] Figure 2 This is a schematic diagram showing the inlet portion of the burner and turbine of a gas turbine according to one embodiment.

[0020] Figure 3A This is a schematic cross-sectional view of a combustion chamber according to one embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0021] Figure 3B This is a schematic cross-sectional view of a combustion chamber according to another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0022] Figure 3CThis is a schematic cross-sectional view of a combustion chamber according to yet another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0023] Figure 3D This is a schematic cross-sectional view of a combustion chamber according to yet another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0024] Figure 3E This is a schematic cross-sectional view of a combustion chamber according to yet another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0025] Figure 4 This is a cross-sectional view used to illustrate the structure of the windshield, showing, as an example, Figure 3A The cross section in the direction of arrow IV-IV.

[0026] Figure 5 This is a schematic diagram illustrating the wind shield used to explain the flow of combustion air into the third fuel nozzle and the radial cross-section of the third fuel nozzle.

[0027] Figure 6 This is a schematic cross-sectional view of two adjacent burners among a plurality of burners arranged circumferentially on the rotor, viewed from the axial downstream side of the combustion chamber, schematically showing the relationship with... Figure 2 The section in the direction of arrow III-III corresponds to the section at the axial position. Detailed Implementation

[0028] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0029] For example, expressions such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" that indicate relative or absolute configuration not only indicate such configuration in a strict sense, but also indicate a state of relative displacement by tolerance or by an angle or distance that can achieve the same level of functionality.

[0030] For example, expressions such as "same," "equal," and "homogeneous" that indicate things are in the same state not only indicate the same state in a strict sense, but also indicate a state with a difference in the degree to which the same function can be obtained, where there is a tolerance.

[0031] For example, descriptions of shapes such as quadrilaterals or cylinders not only refer to shapes in a strict geometric sense, but also to shapes that include concave or convex parts or chamfered parts within the range where the same effect can be achieved.

[0032] On the other hand, the statement that "possesses," "sets," "includes," "contains," or "has" a constituent element is not an exclusive statement that excludes the existence of other constituent elements.

[0033] First, refer to Figure 1 An example of the applicable object of the fuel supply pipe assembly according to one embodiment is a gas turbine. Figure 1 This is a schematic structural diagram of a gas turbine according to one embodiment.

[0034] 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 the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0035] The compressor 2 includes a plurality of stationary blades 16 fixed to the side of the compressor chamber 10 and a plurality of moving blades 18 installed on the rotor 8 in an alternating manner with the stationary blades 16.

[0036] Air drawn in from the air inlet 12 is sent into the 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.

[0037] Fuel and compressed air generated by compressor 2 are supplied to combustor 4, where the fuel is burned to generate the working fluid, i.e., combustion gas, for turbine 6. Figure 1 As shown, the gas turbine 1 has a plurality of burners 4 arranged circumferentially around the rotor 8 within the housing 20.

[0038] The turbine 6 has a combustion gas passage 28 formed by the turbine housing 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.

[0039] Stationary blades 24 are fixed to the side of the turbine housing 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.

[0040] In the turbine 6, combustion gas from the burner 4 flows into the combustion gas passage 28 and passes through multiple stationary blades 24 and multiple moving blades 26, thereby driving the rotor 8 to rotate around the axis O. This drives the generator connected to the rotor 8 to generate electricity. The combustion gas driving the turbine 6 is then discharged to the outside through the exhaust chamber 30.

[0041] Next, the burner 4 according to one embodiment will be described.

[0042] Figure 2 This is a schematic diagram showing the inlet portion of the burner 4 and turbine 6 of a gas turbine 1 according to one embodiment.

[0043] In some embodiments 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 furnace 38 disposed in the combustion tube 36, and a plurality of second combustion furnaces 44 disposed to surround the first combustion furnace 38. That is, the combustion tube 36, the first combustion furnace 38 and the second combustion furnaces 44 are housed in the housing 20.

[0044] The combustion tube (burner bushing) 36 has an inner cylinder 48 disposed around the first combustion furnace 38 and a plurality of second combustion furnaces 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.

[0045] An acoustic device 60 for reducing combustion vibration is provided on the outer periphery of the combustion cylinder 36.

[0046] The first combustion furnace 38 is arranged along the direction of the central axis C1 of the combustion cylinder 36 (i.e., the axial direction of the burner 4 and the combustion cylinder 36) and has a first fuel nozzle 40 for injecting fuel. The first fuel nozzle 40 can supply fuel via a first fuel port 42.

[0047] The second combustion chamber 44 has a second fuel nozzle 46 for injecting fuel. The second fuel nozzle 46 can supply fuel via a second fuel port 43.

[0048] 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.

[0049] via compressor 2 (reference) Figure 1The generated compressed air is supplied to the burner chamber 32 via the chamber inlet 31. This compressed air, as combustion air, flows from the burner chamber 32 into the air passage 54 and changes direction on the wall surface 53, which is provided along a surface orthogonal to the axial direction of the burner 4, thereby flowing into the first combustion chamber 41 and the second combustion chamber 47. Furthermore, in each combustion chamber, the fuel injected from the fuel nozzle and the compressed air (combustion air) are mixed, and the mixed gas flows into the combustion tube 36 where it is ignited and burned, thereby producing combustion gases.

[0050] Combustion gases generated by the combustion of fuel in the burner 4 flow into the turbine 6 through the outlet 51 of the burner 4 located at the downstream end of the tailpipe 50.

[0051] (Third fuel nozzle 70)

[0052] Figure 3A This is a schematic cross-sectional view of the combustion chamber 36 according to one embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0053] Figure 3B This is a schematic cross-sectional view of the combustion chamber 36 according to another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0054] Figure 3C This is a schematic cross-sectional view of the combustion chamber 36 according to another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0055] Figure 3D This is a schematic cross-sectional view of the combustion chamber 36 according to another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0056] Figure 3E This is a schematic cross-sectional view of the combustion chamber 36 according to another embodiment, schematically showing... Figure 2 The cross section in the direction of arrow III-III.

[0057] In some embodiments, the burner 4 includes a plurality of third fuel nozzles 70 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.

[0058] The third fuel nozzle 70 is, for example, fixed to the tailpipe 50.

[0059] In some embodiments of the burner 4, the third fuel nozzle 70 is respectively disposed in the area defined by the wind shield 100 (described later) and the burner 36, which cover the burner 36 radially from the outer side of the burner 36 centered on the central axis C1.

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

[0061] In some embodiments of the burner 4, four third fuel nozzles 70 are spaced apart circumferentially on the combustion chamber 36. Furthermore, in some embodiments of the burner 4, the third fuel nozzles 70 may also be configured such that, when viewed along the central axis C1, they intersect a virtual straight line LV (see reference LV) that passes through the center Cp (i.e., the central axis C1) of the combustion chamber 36 and extends radially along the rotor 8. Figure 3A The rotor 8 is symmetrical on one side and the other side of its circumference.

[0062] In addition, the number of third fuel nozzles 70 provided in a burner 4 in some embodiments is not limited to four; as long as there is one or more, it can be two, three, or five or more.

[0063] 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 burns. 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 suppresses nitrogen oxides (NOx). x This generates [something] and improves combustion efficiency.

[0064] In addition, the burner 4 may also include other components such as a bypass pipe (not shown) for bypassing combustion gases.

[0065] (Regarding the necessity of the windproof cover 100)

[0066] In some embodiments of the gas turbine 1, as described above, a plurality of burners 4 are arranged circumferentially around the rotor 8. Therefore, the spacing between adjacent burners 4 is relatively narrow.

[0067] via compressor 2 (reference) Figure 1The generated compressed air is supplied to the combustor chamber 32 via the chamber inlet 31 at a position radially inward of the combustor 4, which is closer to the rotor 8 than the plurality of combustors 4 adjacent to it in the circumferential direction. As shown by arrow a, the flow of the combustion compressed air introduced into the combustor chamber 32 is as shown by arrows b and c. Then, as shown by arrows d and e, the flow of the combustion compressed air into the combustor 36 is turned in a manner toward the axial upstream side of the gas turbine 1, and flows into the combustor 36 from the axial upstream side of the combustor 36.

[0068] Thus, after the compressed air flows into the burner chamber 32, as it flows into the combustion cylinder 36, as shown by arrow c, a portion of the compressed air passes through the narrow space (gap) between the combustion cylinders 36 of the burners 4 that are circumferentially adjacent to each other with respect to the rotor 8.

[0069] Therefore, the flow rate of combustion air flowing into the plurality of third fuel nozzles 70, which are arranged at intervals along the circumference of the combustion chamber 36, will deviate. That is, among the plurality of third fuel nozzles 70, for example, Figure 3A The two third fuel nozzles 70 shown in the diagram below are located at a ratio of Figure 3A The two third fuel nozzles 70 shown in the diagram are positioned radially inward from the rotor 8, thus allowing for a higher flow rate of combustion air than the rotor 8. Figure 3A The diagram shows the two third fuel nozzles 70 at the top.

[0070] If the concentration of the mixture injected from the third fuel nozzle 70 varies depending on the third fuel nozzle 70 due to the flow rate deviation of the combustion air among the multiple third fuel nozzles 70, the concentration of the mixture injected into the combustion cylinder 36 from multiple circumferential locations of the combustion cylinder 36 becomes uneven, which may lead to abnormal combustion.

[0071] Therefore, in the burner 4 according to some embodiments, by providing the wind shield 100, the flow deviation of combustion air between the plurality of third fuel nozzles 70 as described above is suppressed.

[0072] (Regarding the structure of windproof cover 100)

[0073] Figure 4 This is a cross-sectional view used to illustrate the structure of the windshield 100, showing, as an example, Figure 3A The cross section in the direction of arrow IV-IV.

[0074] Figure 5 This is a schematic diagram showing the wind shield 100 and the radial section of the third fuel nozzle 70 for illustrating the flow of combustion air into the third fuel nozzle 70.

[0075] In addition, in the following description, the circumferential direction, the radial direction, and the axial direction of the combustion cylinder 36 will be referred to as circumferential direction, radial direction, and axial direction, respectively.

[0076] Furthermore, in the following description, the upstream side of the flow of combustion gas in the combustion chamber 36 is referred to as the upstream side or axial upstream side of the combustion chamber 36, and the downstream side of the flow of combustion gas in the combustion chamber 36 is referred to as the downstream side or axial downstream side of the combustion chamber 36.

[0077] like Figures 3A to 3E As shown, in some embodiments of the combustion chamber 36, the wind shield 100 includes a top plate 110 extending circumferentially and a circumferential end 111 connecting the top plate 110 to the circumferential sidewall 120 of the combustion chamber 36.

[0078] like Figures 3A to 3E As shown, in some embodiments of the combustion chamber 36, the wind shield 100 is composed of a top plate 110 and a circumferential sidewall 120, and has an intake opening 130 for introducing combustion air.

[0079] Figures 3A to 3E The wind shield 100 shown may include an end 113 on the upstream side of the combustion cylinder 36 connected to the top plate 110 (see reference). Figure 5 ) and the upstream side wall 140 of the combustion tube 36.

[0080] exist Figures 3A to 3E In the wind shield 100 shown, the top plate 110 is a plate-shaped component that is spaced apart from the outer peripheral surface 36a of the combustion cylinder 36 in such a way that it covers the third fuel nozzle 70 from the radial outside, and extends in both the circumferential and axial directions.

[0081] exist Figures 3A to 3E In the wind shield 100 shown, the circumferential sidewall 120 is a plate-shaped component connecting the circumferential end 111 of the top plate 110 on one side and the other side to the combustion cylinder 36. Figures 3A to 3E In the wind shield 100 shown, the circumferential sidewall 120 blocks the gap between the top plate 110 and the combustion cylinder 36 at one end 111 on one side and the other end 111 on the other side.

[0082] exist Figures 3A to 3E In the wind shield 100 shown, the upstream side wall 140 is a plate-shaped component connecting the upstream end 113 of the combustion cylinder 36 in the top plate 110 to the combustion cylinder 36. Figures 3A to 3E In the wind shield 100 shown, the upstream side wall 140 blocks the gap between the top plate 110 and the combustion cylinder 36 at the end 113 on the upstream side of the combustion cylinder 36 in the top plate 110.

[0083] exist Figures 3A to 3E In the wind shield 100 shown, the intake opening 130 is the opening of the wind shield 100 defined by the top plate 110, the end 111 on one side of the top plate 110 in the circumferential direction, and the circumferential sidewall 120 of the end 111 on the other side.

[0084] In addition, although not shown, an intake opening 130 is also formed in the upstream end 113 of the combustion cylinder 36 in the top plate 110 even without the upstream side wall 140.

[0085] Figure 3A and Figure 3B The wind shield 100 shown is configured such that all the third fuel nozzles 70 are housed within a space defined by the wind shield 100.

[0086] Figure 3C The wind shield 100 shown is configured such that a third fuel nozzle 70 is housed within a space defined by the wind shield 100.

[0087] Figure 3D and Figure 3E The wind shield 100 shown is configured such that two third fuel nozzles 70 are housed within a space defined by the wind shield 100. Figure 3D and Figure 3E In the example shown, within the virtual line LV (reference) Figure 3A Wind shields 100 are respectively provided on one side and the other side of the rotor 8 in the circumferential direction.

[0088] exist Figure 3A and Figure 3E The wind shield 100 shown is provided with a partition 150, which connects the top plate 110 and the combustion cylinder 36, and divides the space along the circumference into a space surrounded by the top plate 110, the circumferential side wall 120 and the combustion cylinder 36.

[0089] exist Figure 3A and Figure 3E In the wind shield 100 shown, the partition wall 150 is disposed within the wind shield 100 between two adjacent third fuel nozzles 70 in the circumferential direction.

[0090] exist Figure 3A In the combustion chamber 36 shown, two third fuel nozzles 70 located on the radially outer side are respectively disposed between a circumferential sidewall 120 located on one side of the circumferential direction and a partition wall 150 located on the other side of the circumferential direction.

[0091] exist Figure 3A In the combustion chamber 36 shown, two third fuel nozzles 70 located on the radial inner side are respectively disposed between partition walls 150 located on one side and the other side in the circumferential direction.

[0092] exist Figure 3E In the combustion chamber 36 shown, four third fuel nozzles 70 are respectively disposed between a circumferential sidewall 120 disposed on one side of the circumference and a partition wall 150 disposed on the other side of the circumference.

[0093] Additionally, although not shown, the combustion chamber 36 may include: a wind shield 100 configured to accommodate two third fuel nozzles 70 disposed on the radially outer side; and a wind shield 100 configured to accommodate two third fuel nozzles 70 disposed on the radially inner side.

[0094] At this point, you can sandwich the virtual straight line LV (reference). Figure 3A A partition wall 150 may be provided between the third fuel nozzle 70 on one side of the rotor 8 and the third fuel nozzle 70 on the other side, or the partition wall 150 may not be provided.

[0095] exist Figures 3A to 3E In the combustion chamber 36 shown, by having a wind shield 100 configured as described above, the flow rate deviation of the combustion air between the plurality of third fuel nozzles 70 arranged circumferentially at intervals on the side of the combustion chamber 36 as described above can be suppressed.

[0096] As described above, Figures 3A to 3E In the wind shield 100 shown, in at least a portion of the circumferential region, the radial dimension Ld of the intake opening 130 is smaller than the circumferential dimension Ls of the intake opening 130.

[0097] like Figures 3A to 3E In the example shown, the radial dimension Ld in the suction opening 130 may be smaller than the circumferential dimension Ls in all circumferential regions.

[0098] Furthermore, the circumferential dimension Ls in the intake opening 130 can be either the dimension measured circumferentially along the outer circumferential surface 36a of the combustion cylinder 36, or the dimension measured circumferentially along the inner circumferential surface 110a of the top plate 110. Alternatively, the circumferential dimension Ls in the intake opening 130 can be obtained by adding the dimension measured circumferentially along the outer circumferential surface 36a of the combustion cylinder 36 and the dimension measured circumferentially along the inner circumferential surface 110a of the top plate 110, and then dividing by 2. The circumferential dimension Ls in the intake opening 130 can also be the dimension measured circumferentially at the midpoint between the outer circumferential surface 36a of the combustion cylinder 36 and the inner circumferential surface 110a of the top plate 110.

[0099] Based on the above-described structure, Figures 3A to 3EEven when multiple combustion tubes 36 are arranged in a ring around the rotor 8 of the gas turbine 1, the combustion tube 36 shown can prevent interference with the wind shield 100 provided on the adjacent combustion tube 36, and ensure the size of the intake opening 130, thereby suppressing the pressure loss of the combustion air flowing into the third fuel nozzle 70.

[0100] The burner 4 in some embodiments includes: Figures 3A to 3E The combustion chamber 36 of any of the structures shown; and the first combustion furnace 38 and the second combustion furnace 44, which are disposed on the axial upstream side of the combustion chamber 36 and serve as combustion furnaces for burning fuel.

[0101] Thus, a burner 4 can be realized that can suppress the flow rate deviation of combustion air between a plurality of third fuel nozzles 70 arranged at intervals along the circumference of the combustion cylinder 36 and can suppress the pressure loss of combustion air flowing into the third fuel nozzles 70.

[0102] Some embodiments of the gas turbine 1 include: a rotor 8; and a combustor 4 with the above structure, having a plurality of such combustors arranged in a ring around the rotor 8.

[0103] This contributes to improving the efficiency of gas turbine 1.

[0104] exist Figures 3A to 3E In the wind shield 100 shown, as described above, the circumferential side is closed by the circumferential sidewall 120, and the axial upstream end is closed by the upstream sidewall 140. Therefore, combustion air enters from the intake opening 130 located on the axial downstream side. Figure 5 As indicated by arrow f, it flows into the windproof cover 100.

[0105] Therefore, in Figures 3A to 3E In the wind shield 100 shown, combustion air flows into the third fuel nozzle 70 from the axial downstream side. Figure 5 As indicated by arrow f, combustion air flows into the third fuel nozzle 70 from the axial downstream side. In the third fuel nozzle 70, as... Figure 5 As indicated by arrow g, the flow direction is changed and the air flows into the combustion chamber 36. Therefore, a region Ro on the axial upstream side near the outlet of the third fuel nozzle 70 is less likely to experience a decrease in the velocity of the combustion air. This helps to suppress abnormal combustion near the outlet of the third fuel nozzle 70.

[0106] In addition, Figure 5 In the diagram, arrow h indicates the flow of combustion gas within the combustion chamber 36.

[0107] exist Figures 3A to 3EIn the wind shield 100 shown, the axial dimension Lax in the top plate 110 (reference) Figure 5 It can be smaller than the circumferential dimension in the top plate 110, that is, the circumferential dimension Ls in the suction opening 130.

[0108] Therefore, interference between the sound device 60, which is located on the combustion cylinder 36 at a position further upstream of the wind shield 100 in the axial direction, and the wind shield 100 can be suppressed.

[0109] Figure 6 This is a schematic cross-sectional view of two adjacent burners 4 among a plurality of burners 4 arranged circumferentially on the rotor 8, viewed from the axial downstream side of the combustion chamber 36, schematically showing the relationship with... Figure 2 The section in the direction of arrow III-III corresponds to the section at the axial position.

[0110] For example, such as Figure 6 As shown, Figures 3A to 3E The combustion chamber 36 shown includes at least a first combustion chamber 36A and a second combustion chamber 36B disposed next to the first combustion chamber 36A. Multiple first combustion chambers 36A and second combustion chambers 36B are arranged in a ring around the rotor 8 of the gas turbine 1. When viewed from the direction of the axis O of the rotor 8 (from the axial downstream side of the combustion chamber 36), if a straight line passing through the axis O of the rotor 8 and the center Cp of the first combustion chamber 36A is designated as the first straight line L1, and a straight line passing through the axis O and the center Cp of the second combustion chamber 36B is designated as the second straight line L2, a portion of the top plate 110 located in the region enclosed by the first straight line L1 and the second straight line L2 can extend parallel to the bisector Lh of the angle formed by the first straight line L1 and the second straight line L2.

[0111] Typically, in an industrial gas turbine 1, multiple adjacent combustion chambers 36 are arranged in a ring around the rotor 8 of the gas turbine 1, and the spacing between them is relatively narrow.

[0112] according to Figures 3A to 3E The combustion chamber 36 shown can easily ensure the size of the intake opening 130 even when the interval between the first combustion chamber 36A and the second combustion chamber 36B is relatively narrow, and can easily suppress the pressure loss of the combustion air flowing into the third fuel nozzle 70.

[0113] exist Figure 3A and Figure 3B In the combustion chamber 36 shown, the wind shield 100 is configured such that all of the plurality of third fuel nozzles 70 are located between the circumferential sidewall 120 on one side and the circumferential sidewall 120 on the other side.

[0114] Therefore, a single wind shield 100 can cover all of the multiple third fuel nozzles 70 that are spaced apart circumferentially along the combustion cylinder 36, thus making the structure of the wind shield 100 relatively simple.

[0115] exist Figure 3A and Figure 3E In the combustion chamber 36 shown, a partition wall 150 is provided on the wind shield 100, so the opening area of ​​the intake opening 130 can be appropriately set according to the circumferential position of the partition wall 150. This easily suppresses the flow rate deviation of combustion air among the multiple third fuel nozzles 70. Furthermore, according to... Figure 3A and Figure 3E The combustion chamber 36 shown can reinforce the top plate 110 through the partition wall 150.

[0116] exist Figures 3A to 3E In the combustion chamber 36 shown, the radial dimension Ld in the intake opening 130 may be less than the circumferential distance Ls1 between two adjacent partitions 150 sandwiching at least one third fuel nozzle 70 in the circumferential direction, or the circumferential distance Ls2 between the adjacent circumferential sidewall 120 and partition 150 sandwiching the third fuel nozzle 70 in the circumferential direction.

[0117] Therefore, even when multiple combustion chambers 36 are arranged in a ring around the rotor 8 of the gas turbine 1, interference with the wind shield 100 provided on the adjacent combustion chamber 36 can be prevented, and the size of the intake opening 130 can be ensured, thereby suppressing the pressure loss of the combustion air flowing into the third fuel nozzle 70.

[0118] Furthermore, distances Ls1 and Ls2 can be dimensions measured circumferentially along the outer peripheral surface 36a of the combustion cylinder 36, or dimensions measured circumferentially along the inner peripheral surface 110a of the top plate 110. Also, distances Ls1 and Ls2 can be obtained by adding the dimensions measured circumferentially along the outer peripheral surface 36a of the combustion cylinder 36 and the dimensions measured circumferentially along the inner peripheral surface 110a of the top plate 110, and then dividing by 2. Distances Ls1 and Ls2 can also be dimensions measured circumferentially at the midpoint between the outer peripheral surface 36a of the combustion cylinder 36 and the inner peripheral surface 110a of the top plate 110.

[0119] The present invention is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments or appropriate combinations thereof.

[0120] The contents described in the above embodiments can be understood, for example, as follows.

[0121] (1) The combustion chamber 36 of the gas turbine 1 according to at least one embodiment of the present invention comprises: a combustion chamber 36; a plurality of fuel nozzles (third fuel nozzles 70) arranged at intervals along the circumference of the combustion chamber 36 on the side portion of the combustion chamber 36; and a wind shield 100 configured to surround at least one of the plurality of fuel nozzles (third fuel nozzles 70). The wind shield 100 includes: a top plate 110 extending circumferentially; and a circumferential sidewall 120 connecting the circumferential end 111 of the top plate 110 to the combustion chamber 36. The wind shield 100 is composed of the top plate 110 and the circumferential sidewall 120, and has an intake opening 130 for introducing combustion air. In at least a portion of the circumferential region, the radial dimension Ld of the combustion chamber 36 in the intake opening 130 is smaller than the circumferential dimension Ls in the intake opening 130.

[0122] According to the structure described in (1) above, by providing the wind shield 100, the flow rate deviation of combustion air between the multiple fuel nozzles (third fuel nozzle 70) arranged at intervals along the circumference of the combustion cylinder 36 can be suppressed. Furthermore, by making the radial dimension Ld of the combustion cylinder 36 in the intake opening 130 smaller than the circumferential dimension Ls in the intake opening 130 in at least a portion of the circumferential region, even when multiple combustion cylinders 36 are arranged in a ring around the rotor 8 of the gas turbine 1, interference with the wind shield 100 provided on adjacent combustion cylinders 36 can be prevented, and the size of the intake opening 130 can be ensured, thereby suppressing the pressure loss of combustion air flowing into the fuel nozzles (third fuel nozzle 70).

[0123] (2) In some embodiments, in the structure described in (1) above, the wind shield 100 may include the end 113 of the combustion cylinder 36 in the top plate 110 connected to the upstream side wall 140 of the combustion cylinder 36.

[0124] According to the structure described in (2) above, since the upstream sidewall 140 blocks the space between the top plate 110 and the combustion cylinder 36 at the upstream end 113 of the combustion cylinder 36 in the top plate 110, combustion air flows into the fuel nozzle (third fuel nozzle 70) from the downstream side of the combustion cylinder 36. Thus, the combustion air flowing into the fuel nozzle (third fuel nozzle 70) from the downstream side of the combustion cylinder 36 changes its flow direction within the fuel nozzle (third fuel nozzle 70) and flows towards the combustion cylinder 36. Therefore, a region where the flow velocity of combustion air decreases is less likely to occur on the upstream side of the combustion cylinder 36 at the outlet of the fuel nozzle (third fuel nozzle 70). This suppresses the generation of abnormal combustion near the outlet of the fuel nozzle (third fuel nozzle 70).

[0125] (3) In some embodiments, in the structure described in (1) or (2) above, the axial dimension Lax of the combustion cylinder 36 in the top plate 110 may be smaller than the circumferential dimension in the top plate 110 (the circumferential dimension Ls of the intake opening 130).

[0126] According to the structure described in (3) above, interference between the sound device 60, which is located on the upstream side of the combustion chamber 36, and the wind shield 100, can be suppressed.

[0127] (4) In some embodiments, in any of the structures described in (1) to (3) above, the combustion chamber 36 may include at least a first combustion chamber 36A and a second combustion chamber 36B disposed next to the first combustion chamber 36A, with a plurality of first combustion chambers 36A and second combustion chambers 36B arranged in a ring around the rotor 8 of the gas turbine 1. When viewed from the axis O of the rotor 8, if a straight line passing through the axis O of the rotor 8 and the center Cp of the first combustion chamber 36A is designated as the first straight line L1, and a straight line passing through the axis O and the center Cp of the second combustion chamber 36B is designated as the second straight line L2, a portion of the top plate 110 located in the region enclosed by the first straight line L1 and the second straight line L2 may extend parallel to the bisector Lh of the angle formed by the first straight line L1 and the second straight line L2.

[0128] According to the structure described above (4), even when the gap between the first combustion chamber 36A and the second combustion chamber 36B is relatively narrow, it is easy to ensure the size of the intake opening 130 and to suppress the pressure loss of the combustion air flowing into the fuel nozzle (third fuel nozzle 70).

[0129] (5) In some embodiments, in any of the structures described in (1) to (4) above, the wind shield 100 may be configured such that all of the plurality of fuel nozzles (the third fuel nozzle 70) are located between the circumferential sidewall 120 on one side and the circumferential sidewall 120 on the other side.

[0130] According to the structure described in (5) above, a single wind shield 100 can cover all of the multiple fuel nozzles (third fuel nozzle 70) that are spaced apart along the circumference of the combustion cylinder 36, thus making the structure of the wind shield 100 relatively simple.

[0131] (6) In some embodiments, in any of the structures in (1) to (5) above, the wind shield 100 may have a partition 150 that connects the top plate 110 and the combustion cylinder 36 and divides the space in the circumferential direction into a space surrounded by the top plate 110, the circumferential sidewall 120 and the combustion cylinder 36.

[0132] According to the structure described in (6) above, the opening area of ​​the intake opening 130 can be appropriately set according to the circumferential position of the partition wall 150. As a result, it is easy to suppress the flow rate deviation of combustion air between the multiple fuel nozzles (the third fuel nozzle 70). Furthermore, according to the structure described in (6) above, the top plate 110 can be reinforced by the partition wall 150.

[0133] (7) In some embodiments, in the structure described in (6) above, the radial dimension Ld of the combustion cylinder 36 in the intake opening 130 may be less than the circumferential distance Ls1 between two adjacent partitions 150 that sandwich at least one fuel nozzle (the third fuel nozzle 70) in the circumferential direction, or the circumferential distance Ls2 between the adjacent circumferential sidewall 120 and the partition 150 that sandwich the fuel nozzle (the third fuel nozzle 70) in the circumferential direction.

[0134] According to the structure described above (7), even when multiple combustion tubes 36 are arranged in a ring around the rotor 8 of the gas turbine 1, interference with the wind shield 100 provided on the adjacent combustion tubes 36 can be prevented, and the size of the intake opening 130 can be ensured, thereby suppressing the pressure loss of combustion air flowing into the fuel nozzle (third fuel nozzle 70).

[0135] (8) The burner 4 of the gas turbine 1 according to at least one embodiment of the present invention includes: a combustion tube 36 with any of the structures in (1) to (7) above; and a combustion furnace (first combustion furnace 38 and second combustion furnace 44) disposed on the upstream side of the combustion tube 36 for burning fuel.

[0136] According to the structure described in (8) above, a burner 4 can be realized that can suppress the flow rate deviation of combustion air between a plurality of fuel nozzles (third fuel nozzle 70) arranged at intervals along the circumference of the combustion cylinder 36 on the side of the combustion cylinder 36, and can suppress the pressure loss of combustion air flowing into the fuel nozzles (third fuel nozzle 70).

[0137] (9) The gas turbine 1 according to at least one embodiment of the present invention includes: a rotor 8; and a combustor 4 with the structure described in (8) above, having a plurality of such combustors arranged in a ring around the rotor 8.

[0138] According to the structure described above (9), it helps to improve the efficiency of the gas turbine 1.

[0139] Symbol Explanation

[0140] 1-Gas turbine, 8-Rotor, 36-Combustion tube, 36A-First combustion tube, 36B-Second combustion tube, 100-Wind shield, 110-Top plate, 120-Circumferential side wall, 130-Intake opening, 140-Upstream side wall, 150-Block wall.

Claims

1. A combustion chamber for a gas turbine, comprising: Combustion tube; Multiple fuel nozzles are spaced apart on the side of the combustion cylinder along its circumference; and A wind shield, configured to surround at least one of the plurality of fuel nozzles, The windproof cover includes: Top plate, extending along the circumferential direction; and the circumferential sidewall, connecting the circumferential end of the top plate to the combustion chamber, The wind shield is composed of the top plate and the circumferential sidewalls, and has an intake opening for introducing combustion air. The radial dimension of the intake opening in the combustion chamber is smaller than the circumferential dimension in at least a portion of the circumferential region. The combustion chamber includes at least a first combustion chamber and a second combustion chamber disposed next to the first combustion chamber, wherein multiple first and second combustion chambers are arranged in a ring around the rotor of the gas turbine. When viewed from the axial direction of the rotor, if a straight line passing through the axis of the rotor and the center of the first combustion chamber is designated as the first straight line, and a straight line passing through the axis and the center of the second combustion chamber is designated as the second straight line, a portion of the top plate located in the area enclosed by the first and second straight lines extends parallel to the bisector of the angle formed by the first and second straight lines.

2. The combustion chamber of the gas turbine according to claim 1, wherein, The wind shield includes an end portion connecting the upstream side of the combustion chamber in the top plate to the upstream side wall of the combustion chamber.

3. The combustion chamber of the gas turbine according to claim 1 or 2, wherein, The axial dimension of the combustion chamber in the top plate is smaller than the circumferential dimension of the top plate.

4. The combustion chamber of the gas turbine according to claim 1 or 2, wherein, The wind shield is configured such that all of the plurality of fuel nozzles are located between the circumferential sidewall on one side and the circumferential sidewall on the other side of the circumferential direction.

5. The combustion chamber of the gas turbine according to claim 1 or 2, wherein, The wind shield has a partition wall that connects the top plate and the combustion cylinder, and divides the space in the circumferential direction into a space surrounded by the top plate, the circumferential side wall and the combustion cylinder.

6. The combustion chamber of the gas turbine according to claim 5, wherein, The radial dimension of the combustion cylinder in the intake opening is less than the circumferential distance between two adjacent partitions sandwiching at least one fuel nozzle in the circumferential direction, or the circumferential distance between the adjacent circumferential sidewalls of the fuel nozzle and the partition.

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

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

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