Combustion cylinder of gas turbine, combustor of gas turbine, and gas turbine

Abstract

A combustion cylinder for a gas turbine according to at least one embodiment of the present invention is provided with: a combustion cylinder; a plurality of fuel nozzles disposed on a side portion of the combustion cylinder at intervals in a circumferential direction of the combustion cylinder; and a windshield configured to surround at least one of the plurality of fuel nozzles. The windshield includes: a top plate extending in a circumferential direction; and a circumferential side wall connecting a circumferential end portion of the top plate and the combustion cylinder. The windshield is configured from a top plate and a circumferential side wall, and has a suction opening for introducing combustion air. In at least a partial region in the circumferential direction, the size in the radial direction of the combustion cylinder in the suction opening portion is smaller than the size in the circumferential direction in the suction opening portion.

Description

Technical Field

[0001] The present invention relates to a combustion barrel of a gas turbine, a burner of a gas turbine and a gas turbine.

[0002] This application claims priority based on application No. 63 / 418, 154 filed in the United States Patent and Trademark Office on October 21, 2022, and its contents are incorporated herein. Background Art

[0003] A gas turbine combustor is known that can supply fuel into a combustion tube from a fuel nozzle provided at a side of the combustion tube of the gas turbine combustor. In this gas turbine combustor, compressed air compressed by a compressor is introduced as combustion air into the combustion tube from the periphery of the gas turbine combustor (for example, refer to Patent Document 1).

[0004] Previous technical literature

[0005] Patent Literature

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

[0007] Technical issues to be solved by the invention

[0008] Generally, in industrial gas turbines, a plurality of burners are arranged in a ring around a rotor, so the intervals between adjacent burners are relatively narrow. Therefore, the flow rate of the combustion air flowing between the combustion tubes of adjacent burners becomes relatively fast. As a result, the flow rate of the combustion air flowing into the fuel nozzle provided on the side of the combustion tube is greatly affected by the circumferential position of the combustion tube provided with the fuel nozzle. However, in the above-mentioned patent document, there is no particular mention of suppressing the influence caused by the circumferential position of the combustion tube provided with the fuel nozzle.

[0009] In view of the above situation, an object of at least one embodiment of the present invention is to provide a combustion tube of a gas turbine, which can suppress the flow rate deviation of the combustion air between multiple fuel nozzles arranged at intervals along the circumferential direction of the combustion tube, and can suppress the pressure loss of the combustion air flowing into the fuel nozzles.

[0010] Means for solving technical problems

[0011] (1) A combustion tube of a gas turbine according to at least one embodiment of the present invention comprises: a combustion tube; a plurality of fuel nozzles arranged at intervals along the circumferential direction of the combustion tube on the side of the combustion tube; and a wind shield arranged to surround at least one of the plurality of fuel nozzles, the wind shield comprising: a top plate extending along the circumferential direction; and a circumferential side wall connecting the circumferential end of the top plate and the combustion tube, the wind shield being composed of the top plate and the circumferential side wall and having an intake opening for introducing combustion air, the radial dimension of the combustion tube in the intake opening being smaller than the circumferential dimension of the intake opening in at least a portion of the circumferential direction.

[0012] (2) A combustor for a gas turbine according to at least one embodiment of the present invention includes:

[0013] A combustion tube having the structure of (1) above; and

[0014] The combustion furnace is arranged on the upstream side of the combustion tube and is used for burning the fuel.

[0015] (3) A gas turbine according to at least one embodiment of the present invention includes: a rotor; and a plurality of combustors having the structure of (2) above, the combustors being arranged in a ring around the rotor.

[0016] Effects of the Invention

[0017] According to at least one embodiment of the present invention, it is possible to suppress a flow rate deviation of combustion air between a plurality of fuel nozzles arranged at intervals in the circumferential direction of the combustion tube, and to suppress a pressure loss of combustion air flowing into the fuel nozzles. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0020] Figure 3A is a schematic cross-sectional view of a combustion cylinder according to an embodiment, schematically showing Figure 2 The cross section is shown in the direction of arrows III-III.

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

[0022] Figure 3Cis a schematic cross-sectional view of a combustion cylinder according to another embodiment, schematically showing Figure 2 The cross section is shown in the direction of arrows III-III.

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

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

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

[0026] Figure 5 The diagram schematically shows a wind shield and a radial cross section of the third fuel nozzle for explaining the flow of combustion air flowing into the third fuel nozzle.

[0027] Figure 6 The schematic cross-sectional view is a schematic diagram showing two adjacent burners among a plurality of burners arranged in the circumferential direction of the rotor, viewed from the axial downstream side of the combustion tube, schematically showing the Figure 2 The cross section in the direction of arrows III-III is equivalent to the cross section in the axial position. DETAILED DESCRIPTION

[0028] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, relative arrangements, etc. of the components described in the embodiments or shown in the accompanying 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 with a tolerance or an angle or distance that can achieve the same degree of functionality.

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

[0031] For example, expressions indicating shapes such as a quadrilateral or a cylinder not only indicate shapes such as a quadrilateral or a cylinder in a strict geometric sense, but also indicate shapes including concave-convex portions or chamfered portions as long as the same effect can be obtained.

[0032] On the other hand, the expression “having”, “configured”, “including”, “containing” or “having” a constituent element is not an exclusive expression that excludes the existence of other constituent elements.

[0033] First, refer to Figure 1 Next, a gas turbine, which is an example of an application target of the fuel supply pipe assembly according to one embodiment, will be described. Figure 1 This is a schematic configuration diagram of a gas turbine according to an embodiment.

[0034] like Figure 1 As shown, the gas turbine 1 includes a compressor 2 for generating compressed air, a gas turbine combustor (combustor) 4 for generating combustion gas using compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. 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 compressor chamber 10 side, and a plurality of moving blades 18 implanted on the rotor 8 so as to be alternately arranged with the stationary blades 16 .

[0036] The air sucked in from the air inlet 12 is sent to the compressor 2 , and the air is compressed by the plurality of stationary blades 16 and the plurality of moving blades 18 , thereby becoming high-temperature and high-pressure compressed air.

[0037] The fuel and the compressed air generated by the compressor 2 are supplied to the combustor 4, and the fuel is burned in the combustor 4 to generate the working fluid of the turbine 6, that is, the combustion gas. Figure 1 As shown, the gas turbine 1 includes a plurality of combustors 4 arranged in a circumferential direction around a rotor 8 in a casing 20 .

[0038] The turbine 6 has a combustion gas passage 28 formed by a turbine casing 22, and includes a plurality of stationary blades 24 and moving blades 26 provided in the combustion gas passage 28. The stationary blades 24 and moving blades 26 of the turbine 6 are provided downstream of the combustor 4 with respect to the flow of the combustion gas.

[0039] The stationary blades 24 are fixed to the turbine housing 22 side, and a plurality of stationary blades 24 arranged along the circumferential direction of the rotor 8 constitute a stationary blade row. Furthermore, the moving blades 26 are planted on the rotor 8, and a plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row. The stationary blade row and the moving blade row are alternately arranged in the axial direction of the rotor 8.

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

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

[0042] Figure 2 It is a schematic diagram showing an inlet portion of a combustor 4 and a turbine 6 of a gas turbine 1 according to an embodiment.

[0043] In the gas turbine 1 according to some embodiments, a plurality of combustors 4 are arranged in the circumferential direction around the rotor 8 (see Figure 1 ) each includes a combustion tube (combustor liner) 36 provided in a combustor chamber 32 defined by a casing 20, a first combustion furnace 38 disposed in each of the combustion tubes 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 furnace 44 are accommodated in the casing 20.

[0044] The combustion tube (combustor liner) 36 includes an inner tube 48 disposed around the first combustion furnace 38 and the plurality of second combustion furnaces 44, and a tail tube 50 connected to the front end of the inner tube 48. The inner tube 48 and the tail tube 50 may be formed integrally.

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

[0046] The first combustion furnace 38 is arranged along the direction of the central axis C1 of the combustion tube 36 (ie, the axial direction of the burner 4 and the combustion tube 36 ), and has a first fuel nozzle 40 for injecting fuel. The first fuel nozzle 40 can be supplied with fuel through a first fuel port 42 .

[0047] The second combustion furnace 44 includes a second fuel nozzle 46 for injecting fuel. The second fuel nozzle 46 can be supplied with fuel via the second fuel port 43 .

[0048] The combustor 4 further includes an outer tube 52 provided on the outer peripheral side of the inner tube 48 in the casing 20. An air passage 54 through which compressed air flows is formed on the outer peripheral side of the inner tube 48 and on the inner peripheral side of the outer tube 52.

[0049] By compressor 2 (reference Figure 1) is supplied to the burner chamber 32 through the engine chamber inlet 31, and the compressed air flows from the burner chamber 32 into the air passage 54 as combustion air, and changes direction on the wall surface 53 provided along the surface orthogonal to the axial direction of the burner 4, thereby flowing into the first combustion furnace tube 41 and the second combustion furnace tube 47. Then, in each combustion furnace tube, 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, is ignited and burns, thereby generating combustion gas.

[0050] The combustion gas generated by the combustion of the fuel in the combustor 4 flows into the turbine 6 through the outlet portion 51 of the combustor 4 located at the downstream end portion of the tail pipe 50 .

[0051] (Third fuel nozzle 70)

[0052] Figure 3A is a schematic cross-sectional view of a combustion tube 36 according to an embodiment, schematically showing Figure 2 The cross section is shown in the direction of arrows III-III.

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

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

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

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

[0057] The burner 4 according to some embodiments includes a plurality of third fuel nozzles 70, which are provided on the side of the combustion tube 36 and are arranged at intervals along the circumferential direction (i.e., the circumferential direction of the burner 4 and the combustion tube 36) centered on the central axis C1. That is, the third fuel nozzle 70 is a fuel nozzle for supplying fuel into the combustion tube 36 from the side of the combustion tube 36.

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

[0059] In the combustor 4 according to some embodiments, the third fuel nozzles 70 are respectively arranged in a region defined by a wind shield 100 (described later) covering the combustion tube 36 from the radially outer side of the combustion tube 36 centered on the central axis C1 and the combustion tube 36 .

[0060] The third fuel nozzle 70 is connected to the third fuel port 74 (see Figure 2 ) to supply fuel. Figure 2 In FIG. 1 , the description of the fuel supply pipe from the third fuel port 74 to each third fuel nozzle 70 is omitted.

[0061] In the combustor 4 according to some embodiments, four third fuel nozzles 70 are provided at intervals in the circumferential direction of the combustion tube 36. In addition, in the combustor 4 according to some embodiments, the third fuel nozzles 70 may be arranged so as to sandwich a virtual straight line LV (refer to FIG. 1 ) passing through the center Cp of the combustion tube 36 (i.e., the center axis C1) and extending in the radial direction of the rotor 8 when viewed along the center axis C1. Figure 3A ) is symmetrical on one side and the other side of the circumferential direction of the rotor 8.

[0062] In addition, the number of the third fuel nozzles 70 provided in one combustor 4 according to some embodiments is not limited to four, and may be one or more, and may be two, three, or five or more.

[0063] When fuel is injected from the third fuel nozzle 70 into the combustion tube 36, the combustion air in the combustion tube 36 is mixed with the injected fuel and burns. By injecting fuel from the third fuel nozzle 70 into the combustion tube 36, the fuel can be supplied to the secondary combustion area in the transition section downstream of the primary combustion area where the fuel from the first fuel nozzle 40 and the second fuel nozzle 46 is burned. This can suppress the generation of nitrogen oxides (NO x ) and improve combustion efficiency.

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

[0065] (About the necessity of windshield 100)

[0066] In the gas turbine 1 according to some embodiments, as described above, a plurality of combustors 4 are arranged in the circumferential direction around the rotor 8. Therefore, the interval between adjacent combustors 4 is relatively narrow.

[0067] By compressor 2 (reference Figure 1) is supplied to the combustor chamber 32 through the chamber inlet 31 at a position radially inward of the plurality of combustors 4 adjacent in the circumferential direction with the rotor 8 as shown by arrow a. The flow of the compressed air for combustion introduced into the combustor chamber 32 is directed to the radially outer side of the gas turbine as shown by arrows b and c, and then turns toward the axially upstream side of the gas turbine 1 as shown by arrows d and e, and flows into the combustor 36 from the axially upstream side of the combustor 36.

[0068] In this way, after the compressed air flows into the combustor chamber 32, while flowing into the combustion tube 36, as shown by arrow c, a portion of the compressed air passes through the narrow space (gap) between the combustion tubes 36 of the combustor 4 adjacent in the circumferential direction around the rotor 8.

[0069] Therefore, the flow rate of the combustion air flowing into the third fuel nozzle 70 may be uneven among the plurality of third fuel nozzles 70 arranged at intervals in the circumferential direction of the combustion tube 36. That is, among the plurality of third fuel nozzles 70, for example, Figure 3A The two third fuel nozzles 70 shown in the figure below are located at a position greater than Figure 3A The two third fuel nozzles 70 shown in the upper part of the figure are located further inward in the radial direction with respect to the rotor 8 as the center, so the flow rate of the combustion air flowing in is likely to be greater than Figure 3A The upper two third fuel nozzles 70 are shown.

[0070] If the concentration of the mixed gas injected from the third fuel nozzle 70 differs according to the third fuel nozzle 70 due to the flow rate deviation of the combustion air between such multiple third fuel nozzles 70, the concentration of the mixed gas injected into the combustion tube 36 from multiple circumferential positions of the combustion tube 36 becomes uneven, which may cause combustion abnormality.

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

[0072] (Regarding the structure of the windshield 100)

[0073] Figure 4 is a cross-sectional view for explaining the structure of the wind shield 100, and shows, as an example, Figure 3A The cross section in the direction of arrow IV-IV.

[0074] Figure 5 The diagram schematically shows a radial cross section of the wind shield 100 and the third fuel nozzle 70 for explaining the flow of the combustion air flowing into the third fuel nozzle 70 .

[0075] In the following description, the circumferential direction of the combustion tube 36 , the radial direction of the combustion tube 36 , and the axial direction of the combustion tube 36 are simply referred to as the circumferential direction, the radial direction, and the axial direction, respectively.

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

[0077] like FIG. 3A to FIG. 3E As shown, in the combustion tube 36 involved in some embodiments, the wind shield 100 includes a top plate 110 extending in the circumferential direction, and a circumferential end 111 connecting the top plate 110 and the circumferential side wall 120 of the combustion tube 36 .

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

[0079] FIG. 3A to FIG. 3E The wind shield 100 shown may include an end portion 113 (see FIG. 1 ) connected to the upstream side of the combustion tube 36 in the top plate 110. Figure 5 ) and the upstream side wall 140 of the combustion tube 36.

[0080] exist FIG. 3A to FIG. 3E In the illustrated wind shield 100 , the top plate 110 is a plate-like member that is arranged at a distance from the outer peripheral surface 36 a of the combustion tube 36 so as to cover the third fuel nozzle 70 from the radially outer side, and extends in the circumferential direction and the axial direction.

[0081] exist FIG. 3A to FIG. 3E In the wind shield 100 shown, the circumferential side wall 120 is a plate-shaped member that connects the end 111 on one side and the end 111 on the other side of the top plate 110 in the circumferential direction with the combustion tube 36. FIG. 3A to FIG. 3E In the illustrated wind shield 100 , the circumferential side wall 120 blocks the gap between the top plate 110 and the combustion tube 36 at one end 111 and the other end 111 in the circumferential direction.

[0082] exist FIG. 3A to FIG. 3E In the wind shield 100 shown, the upstream side wall 140 is a plate-shaped member that connects the upstream end 113 of the combustion tube 36 in the top plate 110 and the combustion tube 36. FIG. 3A to FIG. 3E In the illustrated wind shield 100 , the upstream side wall 140 closes the gap between the top plate 110 and the combustion tube 36 at the end 113 on the upstream side of the combustion tube 36 in the top plate 110 .

[0083] exist FIG. 3A to FIG. 3E In the wind shield 100 shown, the intake opening 130 is an opening of the wind shield 100 defined by the top plate 110, the end 111 on one side of the circumference of the top plate 110, and the circumferential side wall 120 arranged at the end 111 on the other side in the end 115 on the downstream side of the combustion tube 36 in the top plate 110.

[0084] Although not shown, when the upstream side wall 140 is not provided, the suction opening 130 is also formed in the upstream end 113 of the combustion tube 36 in the top plate 110 .

[0085] Figure 3A and Figure 3B The illustrated wind shield 100 is configured so that all the third fuel nozzles 70 are accommodated in a space defined by one wind shield 100 .

[0086] Figure 3C The illustrated wind shield 100 is configured such that one third fuel nozzle 70 is accommodated in a space defined by one wind shield 100 .

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

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

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

[0090] exist Figure 3A In the combustion tube 36 shown, the two third fuel nozzles 70 provided on the radially outer side are respectively arranged between the circumferential side wall 120 provided on one side in the circumferential direction and the partition wall 150 provided on the other side in the circumferential direction.

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

[0092] exist Figure 3E In the combustion tube 36 shown, the four third fuel nozzles 70 are respectively arranged between a circumferential side wall 120 provided on one side in the circumferential direction and a partition wall 150 provided on the other side in the circumferential direction.

[0093] Although not shown, the combustion tube 36 may include: one wind shield 100 configured to accommodate the two third fuel nozzles 70 provided on the radially outer side; and one wind shield 100 configured to accommodate the two third fuel nozzles 70 provided on the radially inner side.

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

[0095] exist FIG. 3A to FIG. 3E In the combustion tube 36 shown, by providing the wind shield 100 configured as described above, it is possible to suppress the above-described flow rate deviation of the combustion air between the plurality of third fuel nozzles 70 arranged at intervals in the circumferential direction on the side of the combustion tube 36 .

[0096] In the above-mentioned structure, FIG. 3A to FIG. 3E In the illustrated wind shield 100 , in at least a portion of the circumferential direction, a radial dimension Ld of the suction opening 130 is smaller than a circumferential dimension Ls of the suction opening 130 .

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

[0098] The circumferential dimension Ls of the suction opening 130 may be a dimension measured in the circumferential direction along the outer circumferential surface 36a of the combustion tube 36, or may be a dimension measured in the circumferential direction along the inner circumferential surface 110a of the top plate 110. Furthermore, the circumferential dimension Ls of the suction opening 130 may be a dimension obtained by adding a dimension measured in the circumferential direction along the outer circumferential surface 36a of the combustion tube 36 and a dimension measured in the circumferential direction along the inner circumferential surface 110a of the top plate 110, and then dividing the sum by 2. The circumferential dimension Ls of the suction opening 130 may be a dimension measured in the circumferential direction along the middle position between the outer circumferential surface 36a of the combustion tube 36 and the inner circumferential surface 110a of the top plate 110.

[0099] According to the above-mentioned structure, FIG. 3A to FIG. 3EThe combustion tube 36 shown can prevent interference with the wind shield 100 provided on the adjacent combustion tube 36 even when a plurality of combustion tubes 36 are arranged in a ring around the rotor 8 of the gas turbine 1, and can 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 according to some embodiments comprises: FIG. 3A to FIG. 3E and a first combustion furnace 38 and a second combustion furnace 44 which are provided on the axially upstream side of the combustion tube 36 and serve as combustion furnaces for burning fuel.

[0101] Thus, a burner 4 can be realized which can suppress flow deviation of combustion air between a plurality of third fuel nozzles 70 arranged at intervals on the side of the combustion tube 36 along the circumferential direction of the combustion tube 36 and can suppress pressure loss of combustion air flowing into the third fuel nozzles 70.

[0102] The gas turbine 1 according to some embodiments includes a rotor 8 and a plurality of combustors 4 having the above-described structure arranged in an annular shape around the rotor 8 .

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

[0104] exist FIG. 3A to FIG. 3E In the wind shield 100 shown in the figure, as described above, the circumferential side portion is closed by the circumferential side wall 120, and the end portion on the axial upstream side is closed by the upstream side wall 140, so that the combustion air is sucked in from the suction opening 130 provided on the axial downstream side. Figure 5 The liquid flows into the wind shield 100 as shown by the arrow f.

[0105] Therefore, in FIG. 3A to FIG. 3E In the wind shield 100 shown in FIG. 1 , combustion air flows into the third fuel nozzle 70 from the axial downstream side. Figure 5 As shown by the arrow f, the combustion air flowing into the third fuel nozzle 70 from the axial downstream side is in the third fuel nozzle 70. Figure 5 The direction of the flow is changed as shown by the arrow g and flows toward the combustion tube 36. As a result, it is difficult to generate a region where the flow velocity of the combustion air decreases in the region Ro on the axial upstream side near the outlet of the third fuel nozzle 70. As a result, the occurrence of abnormal combustion near the outlet of the third fuel nozzle 70 can be suppressed.

[0106] In addition, Figure 5 In FIG. 1 , arrow h indicates the flow of the combustion gas in the combustion tube 36 .

[0107] exist FIG. 3A to FIG. 3EIn the windshield 100 shown in FIG. 1 , the axial dimension Lax (reference Figure 5 ) may be smaller than the circumferential dimension of the top plate 110 , that is, the circumferential dimension Ls of the suction opening 130 .

[0108] This can suppress interference between the acoustic device 60 provided in the combustion tube 36 at a position axially upstream of the wind shield 100 and the wind shield 100 .

[0109] Figure 6 2 is a schematic cross-sectional view of two adjacent combustors 4 among a plurality of combustors 4 arranged in the circumferential direction of the rotor 8, viewed from the axial downstream side of the combustion tube 36, schematically showing the relationship between the combustor 4 and the rotor 8. Figure 2 The cross section in the direction of arrows III-III is equivalent to the cross section in the axial position.

[0110] For example, Figure 6 As shown, FIG. 3A to FIG. 3E The burner tube 36 shown includes at least a first burner tube 36A and a second burner tube 36B arranged next to the first burner tube 36A, and a plurality of the first burner tube 36A and the second burner tube 36B are arranged in a ring shape around the rotor 8 of the gas turbine 1. When viewed from the axis O direction of the rotor 8 (from the axial downstream side of the burner tube 36), a straight line passing through the axis O of the rotor 8 and the center Cp of the first burner tube 36A is set as a first straight line L1, and a straight line passing through the axis O and the center Cp of the second burner tube 36B is set as a second straight line L2, a part of the top plate 110 located in the area sandwiched 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] Generally, in the industrial gas turbine 1 , a plurality of combustion tubes 36 are arranged in a ring shape around the rotor 8 of the gas turbine 1 , and the interval between two adjacent combustion tubes 36 is relatively narrow.

[0112] according to FIG. 3A to FIG. 3E The combustion tube 36 shown can easily ensure the size of the suction opening 130 even when the interval between the first combustion tube 36A and the second combustion tube 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 tube 36 shown, the wind shield 100 is configured so that all of the plurality of third fuel nozzles 70 are located between the circumferential side wall 120 on one side and the circumferential side wall 120 on the other side in the circumferential direction.

[0114] Thus, since all of the plurality of third fuel nozzles 70 arranged at intervals in the circumferential direction of the combustion tube 36 can be covered by one wind shield 100 , the structure of the wind shield 100 can be relatively simple.

[0115] exist Figure 3A and Figure 3E In the combustion tube 36 shown in the figure, the partition wall 150 is provided on the wind shield 100, so the opening area of ​​the suction opening 130 can be appropriately set according to the circumferential position of the partition wall 150. This makes it easy to suppress the flow rate deviation of the combustion air between the plurality of third fuel nozzles 70. Figure 3A and Figure 3E The combustion tube 36 shown can reinforce the top plate 110 by means of a partition wall 150 .

[0116] exist FIG. 3A to FIG. 3E In the combustion tube 36 shown, the radial dimension Ld in the intake opening portion 130 can be smaller than the circumferential distance Ls1 between two circumferentially adjacent partitions 150 sandwiching at least one third fuel nozzle 70, or the circumferential distance Ls2 between the circumferential side wall 120 and the partition 150 sandwiching the third fuel nozzle 70, in at least a portion of the circumferential area.

[0117] Thus, even when a plurality of combustion tubes 36 are arranged in a ring shape around the rotor 8 of the gas turbine 1, interference with the wind shield 100 provided on the adjacent combustion tube 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] In addition, the distance Ls1 and the distance Ls2 may be the dimensions measured in the circumferential direction along the outer peripheral surface 36a of the combustion tube 36, or may be the dimensions measured in the circumferential direction along the inner peripheral surface 110a of the top plate 110. Furthermore, the distance Ls1 and the distance Ls2 may be the dimensions obtained by adding the dimensions measured in the circumferential direction along the outer peripheral surface 36a of the combustion tube 36 and the dimensions measured in the circumferential direction along the inner peripheral surface 110a of the top plate 110, and then dividing the sum by 2. The distance Ls1 and the distance Ls2 may be the dimensions measured in the circumferential direction along the middle position between the outer peripheral surface 36a of the combustion tube 36 and the inner peripheral surface 110a of the top plate 110.

[0119] The present invention is not limited to the above-described embodiments, and includes modified embodiments of the above-described embodiments or embodiments in which these embodiments are appropriately combined.

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

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

[0122] According to the configuration of (1) above, by providing the wind shield 100, it is possible to suppress the flow rate deviation of the combustion air between the plurality of fuel nozzles (third fuel nozzles 70) arranged at intervals in the circumferential direction of the combustion tube 36 and on the side of the combustion tube 36. Furthermore, by making the radial dimension Ld of the combustion tube 36 in the suction opening 130 smaller than the circumferential dimension Ls in the suction opening 130 in at least a part of the circumferential direction, even when a plurality of combustion tubes 36 are arranged in an annular shape around the rotor 8 of the gas turbine 1, it is possible to prevent interference with the wind shield 100 provided on the adjacent combustion tube 36 and ensure the size of the suction opening 130, thereby suppressing the pressure loss of the combustion air flowing into the fuel nozzle (third fuel nozzle 70).

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

[0124] According to the configuration of (2) above, since the space between the top plate 110 and the combustion tube 36 is blocked by the upstream side wall 140 at the end 113 on the upstream side of the combustion tube 36 in the top plate 110, the combustion air flows into the fuel nozzle (the third fuel nozzle 70) from the downstream side of the combustion tube 36. In this way, the combustion air flowing into the fuel nozzle (the third fuel nozzle 70) from the downstream side of the combustion tube 36 changes its flow direction in the fuel nozzle (the third fuel nozzle 70) and flows toward the combustion tube 36, so that a region where the flow velocity of the combustion air is reduced is less likely to be generated on the upstream side of the combustion tube 36 at the outlet of the fuel nozzle (the third fuel nozzle 70). As a result, the occurrence of abnormal combustion near the outlet of the fuel nozzle (the third fuel nozzle 70) can be suppressed.

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

[0126] According to the configuration of (3) above, interference between the acoustic device 60 provided on the combustion tube 36 at a position upstream of the wind shield 100 and the wind shield 100 can be suppressed.

[0127] (4) In some embodiments, in any of the structures of (1) to (3) above, the combustion tube 36 may include at least a first combustion tube 36A and a second combustion tube 36B arranged next to the first combustion tube 36A, and a plurality of the first combustion tube 36A and the second combustion tube 36B are arranged in a ring around the rotor 8 of the gas turbine 1. When viewed from the axis O direction of the rotor 8, a straight line passing through the axis O of the rotor 8 and the center Cp of the first combustion tube 36A is set as the first straight line L1, and a straight line passing through the axis O and the center Cp of the second combustion tube 36B is set as the second straight line L2, a portion of the top plate 110 located in the area sandwiched 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 configuration of (4) above, even when the interval between the first combustion tube 36A and the second combustion tube 36B is relatively narrow, it is easy to ensure the size of the suction 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 (1) to (4) above, the wind shield 100 may be configured so that all of the plurality of fuel nozzles (third fuel nozzles 70 ) are located between the circumferential side wall 120 on one side and the circumferential side wall 120 on the other side in the circumferential direction.

[0130] According to the configuration of (5) above, all of the plurality of fuel nozzles (third fuel nozzles 70 ) arranged at intervals in the circumferential direction of the combustion tube 36 can be covered by one wind shield 100 , so that the configuration of the wind shield 100 can be relatively simple.

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

[0132] According to the structure of (6) above, the opening area of ​​the suction 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 the combustion air between the plurality of fuel nozzles (third fuel nozzle 70). In addition, according to the structure of (6) above, the partition wall 150 can be used to reinforce the top plate 110.

[0133] (7) In some embodiments, in the structure of (6) above, the radial dimension Ld of the combustion tube 36 in the suction opening portion 130 may be smaller than the circumferential distance Ls1 between two circumferentially adjacent partitions 150 sandwiching at least one fuel nozzle (the third fuel nozzle 70), or the circumferential distance Ls2 between the circumferential side wall 120 and the partition 150 sandwiching the fuel nozzle (the third fuel nozzle 70), in at least a portion of the circumferential region.

[0134] According to the structure of (7) above, even when a plurality of combustion tubes 36 are arranged in a ring shape around the rotor 8 of the gas turbine 1, interference with the wind shield 100 provided on the adjacent combustion tube 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 fuel nozzle (the third fuel nozzle 70).

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

[0136] According to the structure of (8) above, a burner 4 can be realized, which can suppress the flow deviation of the combustion air between the multiple fuel nozzles (the third fuel nozzle 70) arranged at intervals along the circumferential direction of the combustion tube 36 on the side of the combustion tube 36, and can suppress the pressure loss of the combustion air flowing into the fuel nozzle (the third fuel nozzle 70).

[0137] (9) A gas turbine 1 according to at least one embodiment of the present invention includes a rotor 8 and a plurality of combustors 4 having the structure of (8) above, which are arranged in an annular shape around the rotor 8 .

[0138] According to the above-mentioned configuration (9), it contributes to improvement of the efficiency of the gas turbine 1 .

[0139] Explanation of symbols

[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- suction opening, 140- upstream side wall, 150- partition wall.

Claims

1. A combustion chamber of a gas turbine, comprising: Combustion tube; A plurality of fuel nozzles are arranged at intervals on the side of the combustion tube along the circumferential direction of the combustion tube; and a wind shield configured to surround at least one of the plurality of fuel nozzles, The windshield comprises: a top plate extending along the circumferential direction; and a circumferential side wall, connecting the circumferential end of the top plate and the combustion tube, The wind shield is composed of the top plate and the circumferential side wall and has an intake opening for introducing combustion air. A radial dimension of the combustion tube in the intake opening is smaller than a circumferential dimension of the intake opening in at least a portion of the circumferential direction.

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

3. The combustion chamber of the gas turbine according to claim 1 or 2, wherein: The axial dimension of the combustion tube 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 combustion tube at least includes a first combustion tube and a second combustion tube arranged next to the first combustion tube, and a plurality of the first combustion tube and the second combustion tube are arranged in a ring around the rotor of the combustion turbine. When viewed from the axial direction of the rotor, a straight line passing through the axis of the rotor and the center of the first combustion tube is set as the first straight line, and a straight line passing through the axis and the center of the second combustion tube is set as the second straight line, a portion of the top plate located in the area sandwiched by the first straight line and the second straight line extends parallel to the bisector of the angle formed by the first straight line and the second straight line.

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

6. 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 tube and divides a space surrounded by the top plate, the circumferential side wall, and the combustion tube in the circumferential direction.

7. The combustion can of the gas turbine according to claim 6, wherein: The radial dimension of the combustion tube in the intake opening is, in at least a portion of the circumferential area, smaller than the circumferential distance between two circumferentially adjacent partitions sandwiching at least one fuel nozzle, or the circumferential distance between the circumferential side wall and the partition wall adjacent in the circumferential direction sandwiching the fuel nozzle.

8. A combustor for a gas turbine, comprising: The combustion tube according to claim 1 or 2; and The combustion furnace is arranged on the upstream side of the combustion tube and is used for burning the fuel.

9. A gas turbine comprising: rotor; and The burner according to claim 8 is arranged in plurality in a ring shape around the rotor.

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