Transition piece, combustor with transition piece, gas turbine, and gas turbine equipment

Abstract

The transition piece of the present invention comprises: a pair of side plates, which are opposed to each other across an axis; a curved inner plate, which is arranged on the inner side of the curve where the downstream portion of the axis is bent relative to the upstream portion, with the axis as a reference; and a curved outer plate, which is arranged on the outer side of the curve opposite to the inner side of the curve, with the axis as a reference. The curved inner plate, the curved outer plate, and the pair of side plates each comprise: a plurality of passage groups, each comprising a plurality of cooling passages extending in the axial direction and arranged in the circumferential direction for the flow of a cooling medium; and at least one header, which extends in the circumferential direction for the flow of the cooling medium. The number of the at least one header in the curved inner plate is less than the number of the at least one header in the curved outer plate and the pair of side plates.

Description

Technical Field

[0001] The present invention relates to a transition piece defining a flow path for combustion gas, a combustor including the transition piece, a gas turbine, and a gas turbine equipment.

[0002] This application claims priority based on Japanese Patent Application No. 2020-123954 filed in Japan on July 20, 2020, the contents of which are incorporated herein by reference. Background Art

[0003] The combustor of a gas turbine includes a transition piece that defines the flow path for combustion gases and a main body that injects fuel into the transition piece along with air. The transition piece is cylindrical and circumferentially extends around the combustor axis. Fuel burns within the transition piece, and the combustion gases generated by the fuel combustion flow through it. Consequently, the inner circumference of the transition piece is exposed to extremely high-temperature combustion gases.

[0004] For example, the combustor barrel (transition piece) disclosed in Patent Document 1 below has multiple passages formed in it for the flow of cooling medium. These passages include a header extending circumferentially relative to the combustor axis, multiple upstream cooling passages extending from the header along the upstream side of the axis, and multiple downstream cooling passages extending from the header along the downstream side of the axis. The header is provided to adjust the number of upstream cooling passages relative to the number of downstream cooling passages.

[0005] Previous technical literature

[0006] Patent Literature

[0007] Patent Document 1: Japanese Patent Application Laid-Open No. 2007-107541 Summary of the Invention

[0008] Technical issues to be solved by the invention

[0009] The transition piece is required to ensure durability above a certain level, and it is also desired to suppress its manufacturing cost.

[0010] Therefore, an object of the present invention is to provide a transition piece, a combustor including the transition piece, and a gas turbine including the combustor, which can ensure durability while reducing manufacturing costs.

[0011] Means for solving technical problems

[0012] Regarding a transition piece as one embodiment of the invention for achieving the above-mentioned object,

[0013] This is a transition piece formed in a cylindrical shape around an axis that curves within an imaginary plane, along the axis, and defining a combustion gas flow path in which combustion gas flows from the upstream side to the downstream side in the axial direction extending from the axis. The transition piece comprises: a pair of side plates that are opposed to the imaginary plane and face each other across the axis; a curved inner plate that is disposed on the inner side of the curve where the downstream portion of the axis curves relative to the upstream portion, with the axis as a reference, and is connected to one end of the curved inner side of the pair of side plates; and a curved outer plate that is disposed on the outer side of the curve opposite to the inner side of the curve with the axis as a reference, faces the curved inner plate across the axis, and is connected to one end of the curved outer side of the pair of side plates. The curved inner plate, the curved outer plate, and the pair of side plates each have: a plurality of passage groups, each comprising a plurality of cooling passages extending in the axial direction and arranged in a circumferential direction relative to the axis, through which a cooling medium flows; and at least one header extending in the circumferential direction through which the cooling medium flows. The plurality of passage groups in each of the curved inner plate, the curved outer plate, and the pair of side plates are arranged in the axial direction, with the headers arranged between the plurality of passage groups in the axial direction. The plurality of passage groups in each of the curved inner plate, the curved outer plate, and the pair of side plates are interconnected via the headers arranged between the plurality of passage groups. A medium inlet for the cooling medium to flow into is formed at one end on the downstream side of the plurality of cooling passages constituting the first passage group located closest to the downstream side, i.e., the plurality of first cooling passages, of the plurality of passage groups in each of the curved inner plate, the curved outer plate, and the pair of side plates. A medium outlet for the cooling medium to flow out is formed at one end on the upstream side of the plurality of cooling channels, i.e., the plurality of final cooling channels, constituting the final channel group located closest to the upstream side, among the plurality of channel groups in each of the curved inner plate portion, the curved outer plate portion, and the pair of side plates. The number of the at least one header in the curved inner plate portion is less than the number of the at least one header in the curved outer plate portion and the pair of side plates.

[0014] In this embodiment, a cooling medium flows into the first cooling passages of the curved inner plate, curved outer plate, and pair of side plates at their inlets. The cooling medium in each section then passes through at least one header within each section before flowing out of the transition piece through the outlet of the final cooling passage in each section. The cooling medium in each section flows from downstream to upstream. During this process, the transition piece is cooled by the cooling medium, while the cooling medium is heated.

[0015] In this embodiment, a header is provided to change the number of cooling passages on the upstream side relative to the number of cooling passages on the downstream side based on the header, thereby maintaining the cooling capacity of the cooling medium flowing from the downstream side to the upstream side.

[0016] In this embodiment, the curved inner plate is positioned closest to the inner side of the curve, and thus has the shortest axial length. Therefore, even if the number of at least one header in the curved inner plate is smaller than the number of at least one header in the curved outer plate and the pair of side plates, the cooling capacity of the cooling medium flowing in the cooling passages of the curved inner plate can be suppressed relative to the cooling capacity of the cooling medium flowing in the respective cooling passages of the curved outer plate and the pair of side plates. Therefore, in this embodiment, even if the structure of the passages in the curved inner plate is simplified compared to the structure of the passages in the curved outer plate and the pair of side plates, the cooling capacity of the cooling medium flowing in the passages of the curved inner plate can be suppressed relative to the cooling capacity of the cooling medium flowing in the passages of the curved outer plate and the pair of side plates.

[0017] Therefore, in this embodiment, it is possible to suppress manufacturing costs while ensuring durability.

[0018] A burner according to one aspect of the invention for achieving the above-mentioned object includes:

[0019] a transition piece of the above type; and a burner that ejects fuel and compressed air into the combustion gas flow path.

[0020] A gas turbine according to one embodiment of the present invention for achieving the above-mentioned object includes:

[0021] A combustor of the above type; a compressor that compresses air and delivers the compressed air to the combustor; a turbine driven by the combustion gas generated in the combustor; and an intermediate casing. The compressor includes a compressor rotor that can rotate about a rotor axis and a compressor casing that covers the outer circumference of the compressor rotor. The turbine includes a turbine rotor that can rotate about the rotor axis and a turbine casing that covers the outer circumference of the turbine rotor. The compressor rotor and the turbine rotor are connected to each other to form a gas turbine rotor. The compressor casing and the turbine casing are connected to each other via the intermediate casing. The transition piece of the combustor is arranged in the intermediate casing so that the curved outer plate portion faces the gas turbine rotor and the curved inner plate portion faces the intermediate casing.

[0022] A gas turbine plant according to one embodiment of the present invention for achieving the above-mentioned object includes:

[0023] A gas turbine of the above type; a cooler that cools a portion of the air compressed by the compressor; a booster compressor that boosts the pressure of the air cooled by the cooler and delivers the boosted air as the cooling medium to the first cooling passages respectively provided in the curved inner plate portion, the curved outer plate portion, and the pair of side plate portions.

[0024] Effects of the Invention

[0025] In one aspect of the present invention, it is possible to suppress the manufacturing cost of the transition piece while ensuring the durability of the transition piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram showing the structure of a gas turbine facility in one embodiment according to the present invention.

[0027] Figure 2 It is a cross-sectional view of the periphery of a combustor of a gas turbine in one embodiment according to the present invention.

[0028] Figure 3 It is a perspective view of a transition piece in one embodiment of the present invention.

[0029] Figure 4 It is along Figure 3 Cross-sectional view taken along line IV-IV.

[0030] Figure 5 It is a development view of a transition piece according to one embodiment of the present invention.

[0031] Figure 6 It is along Figure 5 Cross-sectional view taken along line VI-VI.

[0032] Figure 7 It is along Figure 5 Cross-sectional view taken along line VII-VII. DETAILED DESCRIPTION

[0033] Hereinafter, one embodiment of the gas turbine equipment according to the present invention will be described with reference to the drawings.

[0034] "Implementation Methods for Gas Turbine Plants"

[0035] like Figure 1 As shown, the gas turbine equipment of this embodiment includes a gas turbine 10. The gas turbine 10 includes a compressor 20 for compressing external air Ao to generate compressed air A; a plurality of combustors 40 for burning fuel F in the compressed air A to generate combustion gas G; and a turbine 30 driven by the combustion gas G.

[0036] The compressor 20 includes a compressor rotor 21 that rotates about a rotor axis Ar, a compressor housing 24 that covers the outer circumference of the compressor rotor 21, and a plurality of stationary blade rows 25. The direction in which the rotor axis Ar extends is referred to as the rotor axis direction Da. Furthermore, one side of the rotor axis direction Da is referred to as the rotor axis upstream side Dau, and the other side is referred to as the rotor axis downstream side Dad. The turbine 30 includes a turbine rotor 31 that rotates about the rotor axis Ar, a turbine housing 34 that covers the outer circumference of the turbine rotor 31, and a plurality of stationary blade rows 35.

[0037] The compressor 20 is located on the upstream side Dau of the rotor axis relative to the turbine 30. The compressor rotor 21 and the turbine rotor 31 are located on the same rotor axis Ar and are connected to each other to form the gas turbine rotor 11. For example, the rotor of the generator GEN is connected to the gas turbine rotor 11. The gas turbine 10 further includes an intermediate casing 13 located between the compressor casing 24 and the turbine casing 34. Compressed air A from the compressor 20 flows into the intermediate casing 13. A plurality of combustors 40 are arranged in a circumferential direction relative to the rotor axis Ar and are mounted on the intermediate casing 13. The compressor casing 24, the intermediate casing 13, and the turbine casing 34 are connected to each other to form the gas turbine casing 14.

[0038] The compressor rotor 21 includes a rotor shaft 22 centered on the rotor axis Ar and extending in the rotor axis direction Da, and a plurality of rotating blade rows 23 mounted on the rotor shaft 22. The plurality of rotating blade rows 23 are arranged in the rotor axis direction Da. Each rotating blade row 23 is composed of a plurality of rotating blades arranged in a circumferential direction relative to the rotor axis Ar. One of a plurality of stationary blade rows 25 is arranged on the rotor axis downstream side Dad of each of the plurality of rotating blade rows 23. Each stationary blade row 25 is provided inside the compressor housing 24. Each stationary blade row 25 is composed of a plurality of stationary blades arranged in a circumferential direction relative to the rotor axis Ar.

[0039] The turbine rotor 31 includes a rotor shaft 32 centered on the rotor axis Ar and extending in the rotor axis direction Da, and a plurality of rotor blade rows 33 mounted on the rotor shaft 32. The plurality of rotor blade rows 33 are arranged in the rotor axis direction Da. Each rotor blade row 33 is composed of a plurality of rotor blades arranged in a circumferential direction relative to the rotor axis Ar. One of a plurality of stationary blade rows 35 is arranged on the rotor axis upstream side Dau of each of the plurality of rotor blade rows 33. Each stationary blade row 35 is provided inside the turbine casing 34. Each stationary blade row 35 is composed of a plurality of stationary blades arranged in a circumferential direction relative to the rotor axis Ar.

[0040] In addition to the gas turbine 10 described above, the gas turbine equipment further includes a cooler 15 and a booster compressor 16. The center casing 13 and the intake port of the booster compressor 16 are connected by an air extraction line 18. The cooler 15 is installed on this air extraction line 18. The discharge port of the booster compressor 16 and the combustor 40 are connected by a cooling air line 19. This cooling air line 19 is equipped with a regulating valve 17 for adjusting the flow rate of cooling air. A portion of the compressed air A discharged from the compressor 20 of the gas turbine 10 and flowing into the center casing 13 flows into the air extraction line 18. After being cooled by the cooler 15, this compressed air A is pressurized by the booster compressor 16 and delivered to the combustor 40 as cooling air Ai.

[0041] like Figure 2 As shown, the combustor 40 includes a cylindrical transition piece 50 defining a combustion gas flow path 49 , a cooling air jacket 44 , a muffler 45 , and a main body 41 that ejects fuel F and compressed air A into the transition piece 50 .

[0042] The main body 41 includes a plurality of burners 42 that discharge fuel F and compressed air A into the transition piece 50, and a frame 43 surrounding the burners 42. The burners 42 are fixed to the frame 43. The frame 43 is fixed to the center casing 13.

[0043] The transition piece 50 is formed into a cylindrical shape around the combustor axis Ac, extending along the combustor axis Ac. Here, the direction in which the combustor axis Ac extends is referred to as the combustor axis direction Dca, one of the two sides facing opposite directions in the combustor axis direction Dca is referred to as the combustor axis upstream side Dcu, and the other is referred to as the combustor axis downstream side Dcd.

[0044] like Figure 2 and Figure 3 As shown, the muffler 45 includes a space-delimiting portion 46 as part of the transition piece 50, and a sound cover 48 that, together with the space-delimiting portion 46, forms a sound space on the outer periphery of the transition piece 50. The space-delimiting portion 46 of the transition piece 50 is the portion of the transition piece 50 upstream of the combustor axis Dcu, extending circumferentially relative to the combustor axis Ac. The sound cover 48 covers the space-delimiting portion 46 of the transition piece 50 from the outer periphery. Sound holes 47 are formed in the space-delimiting portion 46 of the transition piece 50, extending from the outer periphery to the inner periphery.

[0045] The cooling air jacket 44 covers a portion of the transition piece 50 and forms a cooling air space on the outer circumference of the transition piece 50. This portion of the transition piece 50 is the portion of the transition piece 50 downstream Dcd of the combustor axis, extending in the circumferential direction relative to the combustor axis Ac. The cooling air line 19 is connected to the cooling air jacket 44.

[0046] like Figure 4 As shown, the transition piece 50 bends the plywood 51 into a cylindrical shape. Figure 4 It is along Figure 3 Cross-sectional view taken along line IV-IV in FIG. The plywood 51 includes an outer plate 52 and an inner plate 54. On the outer plate 52, one of a pair of opposite surfaces facing in opposite directions forms an outer peripheral surface 52o, and the other surface forms a joint surface 52c. The outer peripheral surface 52o of the outer plate 52 forms the outer peripheral surface 52o of the transition piece 50. Furthermore, on the inner plate 54, one of a pair of opposite surfaces facing in opposite directions forms a joint surface 54c, and the other surface forms an inner peripheral surface 54i. On the joint surface 52c of the outer plate 52, the outer peripheral surface 52o side is recessed, and a plurality of long grooves 53 are formed along a certain direction. The joint surfaces 52c, 54 of the outer plate 52 and the inner plate 54 are joined to each other by welding or the like to form the plywood 51. By joining the outer plate 52 and the inner plate 54 , the opening of the long groove 53 formed in the outer plate 52 is closed by the inner plate 54 , and the interior of the long groove 53 becomes a passage 55 through which the cooling air Ai flows.

[0047] like Figure 3 As shown, the combustor axis Ac lies within an imaginary plane Pv that includes the rotor axis Ar. The portion of the combustor axis Ac (hereinafter referred to as axis Ac) on the upstream side Dcu (hereinafter referred to as upstream Dcu) of the combustor axis gradually extends toward the rotor axis Ar as it moves toward the downstream side Dcd (hereinafter referred to as downstream Dcd). Meanwhile, the portion of the axis Ac on the downstream side Dcd extends substantially parallel to the rotor axis Ar. Therefore, within the imaginary plane Pv, the portion of the axis Ac on the downstream side Dcd curves relative to the portion of the axis Ac on the upstream side Dcu. Here, the side of the axis Ac that curves, with respect to the axis Ac, is referred to as the inner curve Dci. Within the imaginary plane Pv, the inner curve Dci is the side farther from the rotor axis Ar with respect to the axis Ac. Furthermore, the side opposite the inner curve Dci, with respect to the axis Ac, is referred to as the outer curve Dco. Within the imaginary plane Pv, the outer curve Dco is the side closer to the rotor axis Ar with respect to the axis Ac.

[0048] As described above, since the axis Ac is curved, the transition piece 50 formed in a cylindrical shape is also curved around the axis Ac in a manner along the axis Ac.

[0049] The transition piece 50 has four regions arranged along the circumferential direction Dcc relative to the axis Ac. Figure 3 and Figure 4 As shown, one of the four regions is a curved inner plate portion 60a, another of the four regions is a curved outer plate portion 60b, and the remaining two of the four regions are a pair of side plate portions 60c.

[0050] The pair of side plates 60c are positioned opposite the imaginary plane Pv and face each other across the axis Ac. The inner curved plate 60a is positioned on the inner curved side Dci with the axis Ac as the reference, and is connected to one end of the inner curved side Dci of the pair of side plates 60c. The outer curved plate 60b is positioned on the outer curved side Dco with the axis Ac as the reference, facing the inner curved plate 60a across the axis Ac, and is connected to one end of the outer curved side Dco of the pair of side plates 60c. Of the four regions, the inner curved plate 60a is positioned closest to the inner curved side Dci, and therefore has the shortest length in the burner axial direction Dca (hereinafter referred to as the axial direction Dca).

[0051] like Figure 5 As shown, the curved inner plate portion 60a has two passage groups 61a and 66a and a header 69a. The two passage groups 61a and 66a are arranged along the axial direction Dca. The header 69a is located between the two passage groups 61a and 66a in the axial direction Dca. Here, of the two passage groups 61a and 66a, the passage group 61a located further downstream Dcd than the header 69a is designated as the first passage group. Furthermore, the remaining passage group 66a is designated as the final passage group. The two passage groups 61a and 66a each extend along the axial direction Dca and are composed of a plurality of cooling passages 62a and 67a arranged along the circumferential direction Dcc. The header 69a extends along the circumferential direction Dcc. The plurality of cooling passages 62a and 67a and the header 69a are all the aforementioned passages 55 through which the cooling air Ai flows.

[0052] An inlet 63a is formed at one end on the downstream side Dcd of the plurality of cooling passages 62a (hereinafter referred to as first cooling passages) that comprise the first passage group 61a. This inlet 63a opens into the outer peripheral surface 52o of the transition piece 50. The plurality of first cooling passages 62a communicate with the cooling air space of the cooling air jacket 44 via the inlet 63a. One end on the upstream side Dcu of the plurality of first cooling passages 62a is connected to a header 69a.

[0053] One end of the downstream side Dcd of the plurality of cooling passages (hereinafter referred to as final cooling passages) 67a that comprise the final passage group 66a is connected to a header 69a. An outlet 68a is formed at one end of the upstream side Dcu of the plurality of final cooling passages 67a. This outlet 68a opens onto the outer peripheral surface 52o of the transition piece 50. The plurality of final cooling passages 67a communicate with the space within the intermediate casing 13 via the outlet 68a.

[0054] The number of the plurality of final cooling passages 67a is smaller than the number of the plurality of first cooling passages 62a. Specifically, the number of the plurality of final cooling passages 67a is approximately half the number of the plurality of first cooling passages 62a.

[0055] Here, if Figure 6 As shown, the channel height of the portion 67ad on the downstream side Dcd of the final cooling channel 67a is H1, and the channel width of the portion 67ad on the downstream side Dcd of the final cooling channel 67a is W. Figure 7 As shown, the channel height H2 of the upstream portion Dcu of the final cooling channel 67a is slightly lower than the channel height H1 of the downstream portion Dcd of the final cooling channel 67a. Furthermore, the channel width W of the upstream portion Dcu of the final cooling channel 67a is the same as the channel width W of the downstream portion Dcd of the final cooling channel 67a. Therefore, the cross-sectional area of ​​the upstream portion Dcu of the final cooling channel 67a is slightly narrower than the cross-sectional area of ​​the downstream portion Dcd of the final cooling channel 67a. Furthermore, the cross-sectional area of ​​the downstream portion Dcd of the final cooling channel 67a is substantially the same as that of the first cooling channel 62a.

[0056] in addition, Figure 6 It is along Figure 5 The cross-sectional view taken along line VI-VI in the figure is: Figure 7 It is along Figure 5 VII-VII in FIG. Furthermore, the portion 67ad on the downstream side Dcd of the final cooling passage 67a is the portion including one end of the downstream side Dcd of the final cooling passage 67a. Furthermore, the portion 67au on the upstream side Dcu of the final cooling passage 67a is the portion excluding the portion 67ad on the downstream side Dcd of the final cooling passage 67a, including one end of the upstream side Dcu of the final cooling passage 67a.

[0057] As described above, the number of final cooling passages 67a constituting the final passage group 66a located upstream of the header 69a (Dcu) is smaller than the number of first cooling passages 62a constituting the first passage group 61a located downstream of the header 69a (Dcd). Furthermore, the cross-sectional area of ​​the final cooling passages 67a is smaller than that of the first cooling passages 62a. Therefore, if the total cross-sectional area of ​​the cooling passages per unit circumferential length is defined as the passage density, the passage density of the final cooling passages 67a constituting the final passage group 66a is smaller than the passage density of the first cooling passages 62a constituting the first passage group 61a.

[0058] In the curved inner plate portion 60a, the channel density of the final channel group 66a on the upstream side Dcu of the header 69a is 20% to 45% of the channel density of the first channel group 61a on the downstream side Dcd of the header 69a.

[0059] like Figure 5 As shown, the curved outer plate portion 60b has three passage groups 61b, 64b, and 66b and two headers 69bu and 69bd. The three passage groups 61b, 64b, and 66b are arranged along the axial direction Dca. Here, the passage group 61b located most downstream (Dcd) of the three passage groups 61b, 64b, and 66b is designated as the first passage group. The passage group 66b located most upstream (Dcu) of the three passage groups 61b, 64b, and 66b is designated as the final passage group. The passage group 64b between the first passage group 61b and the final passage group 66b is designated as the second passage group. The two headers 69bu and 69bd are arranged along the axial direction Dca. Of the two headers 69bu and 69bd, the downstream header 69bd is located between the first passage group 61b and the second passage group 64b in the axial direction Dca. Of the two headers 69bu and 69bd, the upstream header 69bu is located between the second passage group 64b and the final passage group 66b in the axial direction Dca. The three passage groups 61b, 64b, and 66b extend along the axial direction Dca and are composed of multiple cooling passages 62b, 65b, and 67b arranged along the circumferential direction Dcc. The two headers 69bu and 69bd extend along the circumferential direction Dcc. The multiple cooling passages 62b, 65b, and 67b and the multiple headers 69bu and 69bd are all the aforementioned passages 55 through which the cooling air Ai flows.

[0060] An inlet 63b is formed at one end on the downstream side Dcd of the plurality of cooling passages (hereinafter referred to as first cooling passages) 62b that constitute the first passage group 61b of the curved outer plate portion 60b. This inlet 63b opens into the outer peripheral surface 52o of the transition piece 50. The plurality of first cooling passages 62b communicate with the cooling air space of the cooling air jacket 44 via the inlet 63b. One end on the upstream side Dcu of the plurality of first cooling passages 62b is connected to the downstream header 69bd.

[0061] The downstream ends Dcd of the plurality of cooling passages (hereinafter referred to as second cooling passages) 65b constituting the second passage group 64b of the curved outer plate portion 60b are connected to the downstream header 69bd. The upstream ends Dcu of the plurality of second cooling passages 65b are connected to the upstream header 69bu.

[0062] One end of the downstream side Dcd of the multiple cooling passages (hereinafter referred to as final cooling passages) 67b that comprise the final passage group 66b of the curved outer plate portion 60b is connected to the upstream header 69bu. An outlet 68b is formed at one end of the upstream side Dcu of the multiple final cooling passages 67b. This outlet 68b opens onto the outer peripheral surface 52o of the transition piece 50. The multiple final cooling passages 67b communicate with the space within the center casing 13 via the outlet 68b.

[0063] The number of the second cooling passages 65b is smaller than the number of the first cooling passages 62b. Furthermore, the number of the final cooling passages 67b is smaller than the number of the second cooling passages 65b. Specifically, the number of the final cooling passages 67b is approximately half the number of the second cooling passages 65b.

[0064] The cross-sectional area of ​​the second cooling passage 65b is substantially the same as that of the first cooling passage 62b. The cross-sectional area of ​​the final cooling passage 67b is slightly narrower than that of the second cooling passage 65b. Furthermore, the cross-sectional areas of the first cooling passages 62a and 62b in the curved inner plate portion 60a and the curved outer plate portion 60b are substantially the same.

[0065] Therefore, the passage density of the plurality of second cooling passages 65b constituting the second passage group 64b located upstream Dcu of the downstream header 69bd in the curved outer plate portion 60b is lower than the passage density of the plurality of first cooling passages 62b constituting the first passage group 61b located downstream Dcd of the downstream header 69bd in the curved outer plate portion 60b. Furthermore, the passage density of the plurality of final cooling passages 67b constituting the final passage group 66b located upstream Dcu of the upstream header 69bu in the curved outer plate portion 60b is lower than the passage density of the plurality of second cooling passages 65b constituting the second passage group 64b located downstream Dcd of the upstream header 69bu in the curved outer plate portion 60b.

[0066] In the curved outer plate portion 60b, the passage density of the final passage group 66b located upstream Dcu of the upstream header 69bu is 20% to 45% of the passage density of the second passage group 64b located downstream Dcd of the upstream header 69bu.

[0067] Similar to the curved outer plate portion 60b, the pair of side plates 60c also includes three passage groups 61c, 64c, and 66c and two headers 69cu and 69cd. The three passage groups 61c, 64c, and 66c are arranged along the axial direction Dca. Here, the passage group 61c located most downstream (Dcd) of the three passage groups 61c, 64c, and 66c is designated as the first passage group. Furthermore, the passage group 66c located most upstream (Dcu) of the three passage groups 61c, 64c, and 66c is designated as the final passage group. The passage group 64c located between the first passage group 61c and the final passage group 66c is designated as the second passage group. The two headers 69cu and 69cd are arranged along the axial direction Dca. Of the two headers 69cu and 69cd, the downstream header 69cd is located between the first passage group 61c and the second passage group 64c in the axial direction Dca. Of the two headers 69cu and 69cd, the upstream header 69cu is located between the second passage group 64c and the second passage group 66c in the axial direction Dca. The three passage groups 61c, 64c, and 66c each extend along the axial direction Dca and are composed of a plurality of cooling passages 62c, 65c, and 67c arranged along the circumferential direction Dcc. The two headers 69cu and 69cd each extend along the circumferential direction Dcc. The plurality of cooling passages 62c, 65c, and 67c, as well as the plurality of headers 69cu and 69cd, are the aforementioned passages 55 through which the cooling air Ai flows.

[0068] An inlet 63c is formed at one end on the downstream side Dcd of the plurality of cooling passages (hereinafter referred to as first cooling passages) 62c that constitute the first passage group 61c of the pair of side plates 60c. This inlet 63c opens into the outer peripheral surface 52o of the transition piece 50. The plurality of first cooling passages 62c communicate with the cooling air space of the cooling air jacket 44 via the inlet 63c.

[0069] One ends of the upstream side Dcu of the plurality of first cooling passages 62c are connected to the downstream side header 69cd.

[0070] The downstream ends Dcd of the plurality of cooling passages (hereinafter referred to as second cooling passages) 65c constituting the second passage group 64c of the pair of outer plates 60c are connected to the downstream header 69cd. The upstream ends Dcu of the plurality of second cooling passages 65c are connected to the upstream header 69cu.

[0071] One end of the downstream side Dcd of the plurality of cooling passages (hereinafter referred to as final cooling passages) 67c that constitute the final passage group 66c of the pair of outer plate portions 60c is connected to the upstream header 69cu. An outlet 68c is formed at one end of the upstream side Dcu of the plurality of final cooling passages 67c. This outlet 68c opens into the outer peripheral surface 52o of the transition piece 50. The plurality of final cooling passages 67c communicate with the space within the center casing 13 via the outlet 68c.

[0072] The number of the second cooling passages 65c is smaller than the number of the first cooling passages 62c. Furthermore, the number of the final cooling passages 67c is smaller than the number of the second cooling passages 65c. Specifically, the number of the final cooling passages 67c is approximately half the number of the second cooling passages 65c.

[0073] The cross-sectional area of ​​the second cooling passage 65c is substantially the same as that of the first cooling passage 62c. The cross-sectional area of ​​the final cooling passage 67c is slightly narrower than that of the second cooling passage 65c. Furthermore, the cross-sectional areas of the first cooling passages 62a, 62b, and 62c in the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plates 60c are substantially the same.

[0074] Therefore, the passage density of the plurality of second cooling passages 65c constituting the second passage group 64c located upstream Dcu of the downstream header 69cd in the pair of side plates 60c is lower than the passage density of the plurality of first cooling passages 62c constituting the first passage group 61c located downstream Dcd of the downstream header 69cd in the pair of side plates 60c. Furthermore, the passage density of the plurality of final cooling passages 67c constituting the final passage group 66c located upstream Dcu of the upstream header 69cu in the pair of side plates 60c is lower than the passage density of the plurality of second cooling passages 65c constituting the second passage group 64c located downstream Dcd of the upstream header 69cu in the pair of side plates 60c.

[0075] In the pair of side plates 60c, the passage density of the final passage group 66c located upstream Dcu of the upstream header 69cu is 20% to 45% of the passage density of the second passage group 64c located downstream Dcd of the upstream header 69cu.

[0076] The multiple first cooling passages 62a of the first passage group 61a constituting the curved inner plate portion 60a, the multiple first cooling passages 62b of the first passage group 61b constituting the curved outer plate portion 60b, and the multiple first cooling passages 62c of the first passage group 61c constituting a pair of side plate portions 60c have almost the same cross-sectional area and almost the same length in the axial direction Dca.

[0077] Next, the operation of the gas turbine equipment described above will be described.

[0078] The compressor 20 compresses external air Ao to generate compressed air A. This compressed air A is discharged from the compressor 20 into the center casing 13. The compressed air A within the center casing 13 flows into the combustor 42 of the combustor 40. Furthermore, fuel F also flows into the combustor 42 from the outside. The combustor 42 discharges the fuel F together with the compressed air A into the transition piece 50. Within the transition piece 50, the fuel F combusts in the compressed air A to generate combustion gas G. This combustion gas G is delivered from the transition piece 50 to the turbine 30 through the combustion gas flow path 49 within the transition piece 50. The turbine 30 is driven by this combustion gas G.

[0079] A portion of the compressed air A within the center casing 13 flows into the cooler 15 via the air extraction line 18 and is cooled by the cooler 15. The cooled compressed air A is boosted in pressure by the booster compressor 16 and delivered as cooling air Ai to the transition piece 50 of the combustor 40 via the cooling air line 19 and the cooling air jacket 44.

[0080] The inner peripheral surface 54 i of the transition piece 50 is exposed to the extremely high temperature combustion gas G. Therefore, in the present embodiment, cooling air Ai is supplied as a cooling medium to the transition piece 50 to cool the transition piece 50 .

[0081] A portion of the cooling air Ai within the cooling air jacket 44 flows into the first cooling passages 62a, 62b, 62c from the inlets 63a, 63b, 63c of the plurality of first cooling passages 62a, 62b, 62c of the first passage groups 61a, 61b, 61c of the curved outer plate portion 60b and the pair of side plates 60c. The cooling air Ai flowing into the first cooling passages 62a, 62b, 62c flows toward the upstream side Dcu. During this process, the cooling air Ai exchanges heat with the transition piece 50. As a result, the transition piece 50 is cooled, while the cooling air Ai is heated.

[0082] The cooling air Ai flowing through the multiple first cooling passages 62b and 62c of the first passage groups 61b and 61c that make up the curved outer plate 60b and the pair of side plates 60c flows into the downstream headers 69bd and 69cd of the curved outer plate 60b and the pair of side plates 60c. The cooling air Ai flowing through the downstream headers 69bd and 69cd of the curved outer plate 60b and the pair of side plates 60c flows into the multiple second cooling passages 65b and 65c of the second passage groups 64b and 64c that make up the curved outer plate 60b and the pair of side plates 60c. The cooling air Ai flowing into the second cooling passages 65b and 65c flows toward the upstream side Dcu. During this process, the cooling air Ai exchanges heat with the transition piece 50. As a result, the transition piece 50 is cooled, while the cooling air Ai is heated.

[0083] Because the passage density of the second passage groups 64b and 64c is lower than that of the first passage groups 61b and 61c, the flow rate of the cooling air Ai flowing through the plurality of second cooling passages 65b and 65c constituting the second passage groups 64b and 64c is faster than the flow rate of the cooling air Ai flowing through the plurality of first cooling passages 62b and 62c constituting the first passage groups 61b and 61c. Consequently, the heat transfer rate between the cooling air Ai flowing through the plurality of second cooling passages 65b and 65c and the portion of the transition piece 50 where the second passage groups 64b and 64c are formed is substantially equal to or higher than the heat transfer rate between the cooling air Ai flowing through the plurality of first cooling passages 62b and 62c and the portion of the transition piece 50 where the first passage groups 61b and 61c are formed.

[0084] The cooling air Ai flowing through the multiple second cooling passages 65b and 65c of the second passage groups 64b and 64c that make up the curved outer plate 60b and the pair of side plates 60c flows into the upstream headers 69bu and 69cu of the curved outer plate 60b and the pair of side plates 60c. The cooling air Ai flowing through the upstream headers 69bu and 69cu of the curved outer plate 60b and the pair of side plates 60c flows into the multiple final cooling passages 67b and 67c of the final passage groups 66b and 66c of the curved outer plate 60b and the pair of side plates 60c. The cooling air Ai flowing into the final cooling passages 67b and 67c flows toward the upstream side Dcu. During this process, the cooling air Ai exchanges heat with the transition piece 50. As a result, the transition piece 50 is cooled, while the cooling air Ai is heated.

[0085] Because the channel density of the final channel groups 66b and 66c is lower than the channel density of the second channel groups 64b and 64c, the flow rate of the cooling air Ai flowing through the plurality of final cooling channels 67b and 67c constituting the final channel groups 66b and 66c is faster than the flow rate of the cooling air Ai flowing through the plurality of second cooling channels 65b and 65c constituting the second channel groups 64b and 64c. Therefore, the heat transfer rate between the cooling air Ai flowing through the plurality of final cooling channels 67b and 67c and the portion of the transition piece 50 where the final channel groups 66b and 66c are formed is substantially equal to or higher than the heat transfer rate between the cooling air Ai flowing through the plurality of second cooling channels 65b and 65c and the portion of the transition piece 50 where the second channel groups 64b and 64c are formed.

[0086] The cooling air Ai flowing through the plurality of final cooling passages 67b, 67c of the final passage groups 66b, 66c constituting the curved outer plate portion 60b and the pair of side plates 60c flows out from the outlets 68b, 68c of the final cooling passages 67b, 67c into the center casing 13.

[0087] As described above, in this embodiment, the curved outer plate portion 60 b and the pair of side plate portions 60 c in the transition piece 50 can be sufficiently cooled.

[0088] A portion of the cooling air Ai within the cooling air cuff 44 flows into the first cooling passages 62a from the inlets 63a of the plurality of first cooling passages 62a that form the first passage group 61a of the curved inner plate portion 60a. The cooling air Ai flowing into the first cooling passages 62a flows toward the upstream side Dcu. During this process, the cooling air Ai exchanges heat with the transition piece 50. As a result, the transition piece 50 is cooled, while the cooling air Ai is heated.

[0089] The cooling air Ai flowing through the multiple first cooling passages 62a of the first passage group 61a that constitutes the curved inner plate portion 60a flows into the header 69a of the curved inner plate portion 60a. The cooling air Ai flowing into the header 69a then flows into the multiple final cooling passages 67a of the final passage group 66a that constitutes the curved inner plate portion 60a. The cooling air Ai flowing into the final cooling passages 67a flows toward the upstream side Dcu. During this process, the cooling air Ai exchanges heat with the transition piece 50. As a result, the transition piece 50 is cooled, while the cooling air Ai is heated.

[0090] Because the channel density of the final channel group 66a is lower than that of the first channel group 61a, the flow rate of the cooling air Ai flowing through the plurality of final cooling channels 67a constituting the final channel group 66a is faster than the flow rate of the cooling air Ai flowing through the plurality of first cooling channels 62a constituting the first channel group 61a. Therefore, the heat transfer rate between the cooling air Ai flowing through the plurality of final cooling channels 67a and the portion of the transition piece 50 where the final channel group 66a is formed is substantially equal to or higher than the heat transfer rate between the cooling air Ai flowing through the plurality of first cooling channels 62a and the portion of the transition piece 50 where the first channel group 61a is formed.

[0091] However, in this embodiment, the cross-sectional area of ​​the upstream Dcu portion 67au of the final cooling passage 67a of the curved inner plate portion 60a is smaller than the cross-sectional area of ​​the downstream Dcd portion 67ad of the final cooling passage 67a. Therefore, the flow rate of the cooling air Ai flowing through the upstream Dcu portion 67au of the final cooling passage 67a is faster than the flow rate of the cooling air Ai flowing through the downstream Dcd portion 67ad of the final cooling passage 67a. Consequently, the heat transfer rate between the cooling air Ai flowing through the upstream Dcu portion 67au of the final cooling passage 67a and the area surrounding the upstream Dcu portion 67au of the final cooling passage 67a in the transition piece 50 is substantially equal to or higher than the heat transfer rate between the cooling air Ai flowing through the downstream Dcd portion 67ad of the final cooling passage 67a and the area surrounding the downstream Dcd portion 67ad of the final cooling passage 67a in the transition piece 50.

[0092] In this embodiment, headers 69a, 69bu, 69bd, 69cu, and 69cd are provided to change the number of cooling passages 67a, 65b, 67b, 65c, and 67c on the upstream side Dcu relative to the number of cooling passages 62a, 62b, 65b, 62c, and 65c on the downstream side Dcd based on the headers 69a, 69bu, 69bd, 69cu, and 69cd, thereby maintaining the cooling capacity of the cooling medium flowing from the downstream side Dcd to the upstream side Dcu.

[0093] In this embodiment, the number of headers 69a on the curved inner plate portion 60a is one, while the number of headers 69bu and 69bd on the curved outer plate portion 60b and the number of headers 69cu and 69cd on the pair of side plates 60c are two. In other words, the number of headers 69a on the curved inner plate portion 60a is less than the number of headers 69bu, 69bd, 69cu, and 69cd on the curved outer plate portion 60b and the pair of side plates 60c. As described above, in the transition piece 50, of the four regions arranged along the circumferential direction Dcc, the curved inner plate portion 60a is positioned closest to the curved inner side Dci, and therefore has the shortest length in the axial direction Dca. Therefore, the total path length of the first cooling path 62a and the final cooling path 67a combined by the curved inner plate portion 60a is shorter than the total flow path length of the first cooling path 62b, the second cooling path 65b and the final cooling path 67b combined by the curved outer plate portion 60b, and the total flow path length of the first cooling path 62c, the second cooling path 65c and the final cooling path 67c combined by the pair of side plate portions 60c. Therefore, even if the number of collecting pipes 69a of the curved inner plate portion 60a is less than the number of collecting pipes 69bu, 69bd, 69cu, and 69cd of the curved outer plate portion 60b and the pair of side plate portions 60c, the reduction in the cooling capacity of the cooling air Ai flowing in the cooling passages 62a and 67a of the curved inner plate portion 60a relative to the cooling capacity of the cooling air Ai flowing in the respective cooling passages 62b, 65b, 67b, 62c, 65c, and 67c of the curved outer plate portion 60b and the pair of side plate portions 60c can be suppressed.

[0094] As a result, in this embodiment, even if the structure of the passages in the curved inner plate portion 60a is simplified compared to the structures of the passages in the curved outer plate portion 60b and the pair of side plates 60c, the curved inner plate portion 60a in the transition piece 50 can be sufficiently cooled.

[0095] Therefore, in the present embodiment, the manufacturing cost of the transition piece 50 can be suppressed while ensuring the durability of the transition piece 50 .

[0096] "Variation"

[0097] In the above embodiment, the outlets 68a, 68b, and 68c of the final cooling passages 67a, 67b, and 67c are formed on the outer circumferential surface 52o of the transition piece 50, at a portion downstream Dcd from the space defining portion 46 of the muffler 45. Therefore, in the above embodiment, the cooling air Ai passing through the final cooling passages 67a, 67b, and 67c of the transition piece 50 flows out of the outlets 68a, 68b, and 68c of the final cooling passages 67a, 67b, and 67c into the center casing 13. However, the outlets 68a, 68b, and 68c of the final cooling passages 67a, 67b, and 67c may also be formed on the outer circumferential surface 52o of the transition piece 50, at the space defining portion 46 of the muffler 45. In this case, the cooling air Ai passing through the final cooling passages 67a, 67b, 67c of the transition piece 50 flows into the sound space from the outlets 68a, 68b, 68c of the final cooling passages 67a, 67b, 67c, and then flows into the combustion gas flow path 49 of the transition piece 50 from the sound hole 47 of the muffler 45.

[0098] In the above embodiment, the number of headers 69a on the curved inner plate portion 60a is one, and the number of headers 69bu, 69bd, 69cu, and 69cd on the curved outer plate portion 60b and the pair of side plates 60c are two each. However, if the number of headers on the curved outer plate portion 60b and the pair of side plates 60c is greater than the number of headers on the curved inner plate portion 60a, the number of headers on the curved inner plate portion 60a may be two or more.

[0099] Postscript

[0100] The transition piece in the above embodiment can be understood, for example, as follows.

[0101] (1) Regarding the transition piece 50 in the first embodiment,

[0102] The transition piece 50 is a transition piece 50 formed in a cylindrical shape around an axis Ac that curves within an imaginary plane Pv so as to be along the axis Ac and demarcates a combustion gas flow path 49 in which the combustion gas G flows from the upstream side Dcu to the downstream side Dcd in the axial direction Dca extending from the axis Ac. The transition piece 50 includes: a pair of side plates 60c that are opposed to the imaginary plane Pv and are opposed to each other across the axis Ac; a curved inner plate 60a that is arranged on the curved inner side Dci on the side where the downstream side Dcd portion of the axis Ac curves relative to the upstream side Dcu, with the axis Ac as a reference, and is connected to one end of the curved inner side Dci of the pair of side plates 60c; and a curved outer plate 60b that is arranged on the curved outer side Dco on the opposite side of the curved inner side Dci with the axis Ac as a reference, is opposed to the curved inner plate 60a across the axis Ac, and is connected to one end of the curved outer side Dco of the pair of side plates 60c. The curved inner plate portion 60a, the curved outer plate portion 60b and the pair of side plate portions 60c respectively have: a plurality of passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c consisting of a plurality of cooling passages 62a, 67a, 62b, 65b, 67b, 62c, 65c, 67c extending along the axial direction Dca and arranged along the circumferential direction Dcc relative to the axis Ac for the flow of cooling medium; and at least one collecting pipe 69a, 69bu, 69bd, 69cu, 69cd extending along the circumferential direction Dcc for the flow of the cooling medium. The multiple passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c of the curved inner plate portion 60a, the curved outer plate portion 60b and the pair of side plate portions 60c are arranged along the axial direction Dca, and the collecting pipes 69a, 69bu, 69bd, 69cu, 69cd are arranged between the multiple passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c in the axial direction Dca. The multiple passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c of the curved inner plate portion 60a, the curved outer plate portion 60b and the pair of side plate portions 60c are connected to each other via the collection pipes 69a, 69bu, 69bd, 69cu, 69cd arranged between the multiple passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c.At one end of the downstream side Dcd of the multiple cooling passages, i.e., the multiple first cooling passages 62a, 62b, 62c, constituting the first passage group 61a, 61b, 61c located closest to the downstream side Dcd, among the multiple passage groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, 66c of the curved inner plate portion 60a, the curved outer plate portion 60b and the pair of side plate portions 60c, medium inlets 63a, 63b, 63c for the cooling medium to flow in are formed. A medium outlet 68a, 68b, 68c for discharging the cooling medium is formed at one end of the upstream Dcu of the plurality of cooling channels, namely, the plurality of final cooling channels 67a, 67b, 67c, constituting the final channel group 66a, 66b, 66c located closest to the upstream Dcu, among the plurality of channel groups 61a, 66a, 61b, 64b, 66b, 61c, 64c, and 66c of the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plates 60c. The number of the at least one header 69a of the curved inner plate portion 60a is less than the number of the at least one header 69bu, 69bd, 69cu, and 69cd of the curved outer plate portion 60b and the pair of side plates 60c.

[0103] In this embodiment, a cooling medium flows into each of the first cooling passages 62a, 62b, and 62c of the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plate portions 60c through their inlets 63a, 63b, and 63c. The cooling medium within each section then passes through at least one header 69a, 69bu, 69bd, 69cu, and 69cd within each section before flowing out of the transition piece 50 through the outlets 68a, 68b, and 68c of the final cooling passages 67a, 67b, and 67c of each section. The cooling medium within each section flows from the downstream side Dcd to the upstream side Dcu. During this process, the transition piece 50 is cooled by the cooling medium while being heated.

[0104] In this embodiment, headers 69a, 69bu, 69bd, 69cu, and 69cd are provided to change the number of cooling passages 67a, 65b, 67b, 65c, and 67c on the upstream side Dcu relative to the number of cooling passages 62a, 62b, 65b, 62c, and 65c on the downstream side Dcd based on the headers 69a, 69bu, 69bd, 69cu, and 69cd, thereby maintaining the cooling capacity of the cooling medium flowing from the downstream side Dcd to the upstream side Dcu.

[0105] In this embodiment, the curved inner plate 60a is positioned closest to the inner curve Dci among the curved inner plate 60a, the curved outer plate 60b, and the pair of side plates 60c, and therefore has the shortest length in the axial direction Dca. Therefore, even if the number of at least one header 69a in the curved inner plate 60a is smaller than the number of at least one headers 69bu, 69bd, 69cu, and 69cd in the curved outer plate 60b and the pair of side plates 60c, it is possible to suppress a decrease in the cooling capacity of the cooling medium flowing through the cooling passages 62b, 65b, 67b, 62c, 65c, and 67c in the curved outer plate 60b and the pair of side plates 60c. Therefore, in this embodiment, even if the structure of the passage in the curved inner plate portion 60a is simplified compared to the structure of the passage in the curved outer plate portion 60b and the pair of side plate portions 60c, the reduction in the cooling capacity of the cooling medium flowing in the passage in the curved inner plate portion 60a relative to the cooling capacity of the cooling medium flowing in the passage in the curved outer plate portion 60b and the pair of side plate portions 60c can be suppressed.

[0106] Therefore, in this embodiment, it is possible to suppress manufacturing costs while ensuring durability.

[0107] (2) Regarding the transition piece 50 in the second embodiment,

[0108] In the transition piece 50 of the first embodiment, in each of the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plate portions 60c, each of the plurality of cooling passages 67a, 65b, 67b, 65c, 67c of the passage group 66a, 64b, 66b, 64c, 66c that communicate with the headers 69a, 69bu, 69bd, 69cu, 69cd and constitute the upstream side Dcu with the headers 69a, 69bu, 69bd, 69cu, 69cd as a reference is provided. The total cross-sectional area of ​​the multiple cooling passages 67a, 65b, 67b, 65c, 67c per unit circumferential length, that is, the passage density, is smaller than the passage density of the multiple cooling passages 62a, 62b, 65b, 62c, 65c of the passage group 61a, 61b, 64b, 61c, 64c that are connected to the collecting pipes 69a, 69bu, 69bd, 69cu, 69cd and constitute the downstream side Dcd based on the collecting pipes 69a, 69bu, 69bd, 69cu, 69cd.

[0109] In this embodiment, the channel density of the channel groups 66a, 64b, 66b, 64c, and 66c on the upstream side Dcu is lower than the channel density of the channel groups 61a, 61b, 64b, 61c, and 64c on the downstream side Dcd. Therefore, the flow rate of the cooling air Ai flowing through the multiple cooling channels 67a, 65b, 67b, 65c, and 67c that constitute the channel groups 66a, 64b, 66b, 64c, and 66c on the upstream side Dcu is faster than the flow rate of the cooling air Ai flowing through the multiple cooling channels 62a, 62b, 65b, 62c, and 65c that constitute the channel groups 61a, 61b, 64b, 61c, and 64c on the downstream side Dcd. Therefore, the heat transfer rate between the cooling air Ai flowing through the multiple cooling passages 67a, 65b, 67b, 65c, 67c of the passage group 66a, 64b, 66b, 64c, 66c constituting the upstream side Dcu and the portion of the passage group 66a, 64b, 66b, 64c, 66c forming the upstream side Dcu in the transition piece 50 is almost equal to or higher than the heat transfer rate between the cooling air Ai flowing through the multiple cooling passages 62a, 62b, 65b, 62c, 65c of the passage group 61a, 61b, 64b, 61c, 64c constituting the downstream side Dcd and the portion of the passage group 61a, 61b, 64b, 61c, 64c forming the downstream side Dcd in the transition piece 50.

[0110] (3) Regarding the transition piece 50 in the third embodiment,

[0111] In the transition piece 50 of the second embodiment, in each of the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plate portions 60c, the passage density in the final passage group 66a, 66b, 66c is 25% to 45% of the passage density in the passage group 62a, 64b, 64c located on the downstream side Dcd of the headers 69a, 69bu, 69cu connected to the final passage group 66a, 66b, 66c.

[0112] (4) Regarding the transition piece 50 in the fourth embodiment,

[0113] In the transition piece 50 of any one of the first to third aspects, in each of the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plate portions 60c, the passage groups 66a, 64b, 66b, 64c, 66d, which are connected to the headers 69a, 69bu, 69bd, 69cu, and 69cd and constitute the upstream side Dcu with the headers 69a, 69bu, 69bd, 69cu, and 69cd as a reference, c is less than the number of the multiple cooling passages 67a, 65b, 67b, 65c, 67c of the passage group 61a, 61b, 64b, 61c, 64c which are connected to the headers 69a, 69bu, 69bd, 69cu, 69cd and constitute the downstream side Dcd with the headers 69a, 69bu, 69bd, 69cu, 69cd as the reference.

[0114] In this embodiment, the number of the plurality of cooling passages 67a, 65b, 67b, 65c, and 67c in the passage group 66a, 64b, 66b, 64c, and 66c constituting the upstream side Dcu is smaller than the number of the plurality of cooling passages 62a, 62b, 65b, 62c, and 65c in the passage group 61a, 61b, 64b, 61c, and 64c constituting the downstream side Dcd. Therefore, the flow rate of the cooling air Ai flowing through the plurality of cooling passages 67a, 65b, 67b, 65c, and 67c in the passage group 66a, 64b, 66b, 64c, and 66c constituting the upstream side Dcu is faster than the flow rate of the cooling air Ai flowing through the plurality of cooling passages 62a, 62b, 65b, 62c, and 65c in the passage group 61a, 61b, 64b, 61c, and 64c constituting the downstream side Dcd. Therefore, the heat transfer rate between the cooling air Ai flowing through the multiple cooling passages 67a, 65b, 67b, 65c, 67c of the passage group 66a, 64b, 66b, 64c, 66c constituting the upstream side Dcu and the portion of the passage group 66a, 64b, 66b, 64c, 66c forming the upstream side Dcu in the transition piece 50 is almost equal to or higher than the heat transfer rate between the cooling air Ai flowing through the multiple cooling passages 62a, 62b, 65b, 62c, 65c of the passage group 61a, 61b, 64b, 61c, 64c constituting the downstream side Dcd and the portion of the passage group 61a, 61b, 64b, 61c, 64c forming the downstream side Dcd in the transition piece 50.

[0115] (5) Regarding the transition piece 50 in the fifth embodiment,

[0116] In the transition piece 50 of any one of the first to fourth aspects, each cross-sectional area of ​​the upstream side Dcu portion 67au of the multiple final cooling passages 67a possessed by the curved inner plate portion 60a is smaller than any cross-sectional area of ​​the downstream side Dcd portion 67ad of the multiple final cooling passages 67a possessed by the curved inner plate portion 60a.

[0117] The cross-sectional area of ​​the upstream Dcu portion 67au of the final cooling passage 67a of the curved inner plate portion 60a is smaller than the cross-sectional area of ​​the downstream Dcd portion 67ad of the final cooling passage 67a. Therefore, the flow rate of the cooling air Ai flowing through the upstream Dcu portion 67au of the final cooling passage 67a is faster than the flow rate of the cooling air Ai flowing through the downstream Dcd portion 67ad of the final cooling passage 67a. Consequently, the heat transfer rate between the cooling air Ai flowing through the upstream Dcu portion 67au of the final cooling passage 67a and the area surrounding the upstream Dcu portion 67au of the final cooling passage 67a in the transition piece 50 is substantially equal to or higher than the heat transfer rate between the cooling air Ai flowing through the downstream Dcd portion 67ad of the final cooling passage 67a and the area surrounding the downstream Dcd portion 67ad of the final cooling passage 67a in the transition piece 50.

[0118] (6) Regarding the transition piece 50 in the sixth embodiment,

[0119] In the transition connector 50 of any one of the first to fifth modes, the number of the at least one collecting pipe 69a of the curved inner plate portion 60a is 1, and the number of the at least one collecting pipe 69bu, 69bd, 69cu, 69cd of the curved outer plate portion 60b and the pair of side plate portions 60c is 2 or more.

[0120] The burner in the above embodiment is explained as follows, for example.

[0121] (7) Regarding the burner 40 in the seventh embodiment,

[0122] It includes the transition piece 50 of any one of the first to sixth aspects and the combustor 42 that ejects fuel F and compressed air A into the combustion gas flow path 49 .

[0123] The gas turbine in the above embodiment can be understood, for example, as follows.

[0124] (8) Regarding the gas turbine 10 in the eighth embodiment,

[0125] The combustor 40 includes the seventh embodiment; a compressor 20 that compresses air and delivers the compressed air A to the combustor 40; a turbine 30 driven by the combustion gas G generated in the combustor 40; and an intermediate casing 13. The compressor 20 includes a compressor rotor 21 rotatable about a rotor axis Ar and a compressor casing 24 covering the outer circumference of the compressor rotor 21. The turbine 30 includes a turbine rotor 31 rotatable about the rotor axis Ar and a turbine casing 34 covering the outer circumference of the turbine rotor 31. The compressor rotor 21 and the turbine rotor 31 are connected to form the gas turbine rotor 11. The compressor casing 24 and the turbine casing 34 are connected to each other via the intermediate casing 13. The transition piece 50 of the combustor 40 is disposed within the intermediate casing 13 such that the curved outer plate portion 60b faces the gas turbine rotor 11 and the curved inner plate portion 60a faces the intermediate casing 13.

[0126] The gas turbine equipment in the above-mentioned embodiment can be understood, for example, as follows.

[0127] (9) With respect to the gas turbine equipment according to the ninth embodiment,

[0128] It comprises: the gas turbine 10 of the eighth embodiment; a cooler 15 for cooling a portion of the air compressed by the compressor 20; and a booster compressor 16 for boosting the air cooled by the cooler 15 and delivering the boosted air as the cooling medium to the first cooling passages 62a, 62b, and 62c respectively provided in the curved inner plate portion 60a, the curved outer plate portion 60b, and the pair of side plate portions 60c.

[0129] Industrial applicability

[0130] In one aspect of the present invention, it is possible to suppress the manufacturing cost of the transition piece while ensuring the durability of the transition piece.

[0131] Explanation of symbols

[0132] 10-gas turbine, 11-gas turbine rotor, 13-intermediate casing, 14-gas turbine casing, 15-cooler, 16-boost compressor, 17-regulating valve, 18-extraction pipeline, 19-cooling air pipeline, 20-compressor, 21-compressor rotor, 22-rotor shaft, 23-rotating blade row, 24-compressor casing, 25-stationary blade row, 30-turbine, 31-turbine rotor, 32-rotor shaft, 33-rotating blade row, 34-turbine casing, 35-stationary blade row, 40-burner, 41-main body, 42-burner, 43-frame, 44-cooling air envelope, 45-muffler, 46-space demarcation part, 47-sound hole, 48-sound cover, 49-combustion gas flow path, 50-transition connector, 51-plywood, 52-outer plate, 52o-outer peripheral surface, 52c-joining surface, 53-long groove, 54-inner plate, 54i-inner peripheral surface, 54c-joining surface, 55-passage, 60a-curved inner plate portion, 61a-first passage group (of the curved inner plate portion), 62a-first cooling passage (of the curved inner plate portion), 63a-inlet (of the curved inner plate portion), 66a-final passage group (of the curved inner plate portion), 67a-final cooling passage (of the curved inner plate portion), 68a-outlet (of the curved inner plate portion), 67ad-downstream portion (of the final cooling passage), 67au-upstream portion (of the final cooling passage) Points, 69a-(bent inner plate) header, 60b-bent outer plate, 61b-(bent outer plate) first passage group, 62b-(bent outer plate) first cooling passage, 63b-(bent outer plate) inlet, 64b-(bent outer plate) second passage group, 65b-(bent outer plate) second cooling passage, 66b-(bent outer plate) final passage group, 67b-(bent outer plate) final cooling passage, 68b-(bent outer plate) outlet, 69bd-(bent outer plate) downstream side header, 69bu-(bent outer plate) upstream side header, 60c-side plate, 61c-(side plate) first passage group, 62c -(side plate portion) first cooling passage, 63c-(side plate portion) inlet, 64c-(side plate portion) second passage group, 65c-(side plate portion) second cooling passage, 66c-(side plate portion) final passage group, 67c-(side plate portion) final cooling passage, 68c-(side plate portion) outlet, 69cd-(side plate portion) downstream side header, 69cu-(side plate portion) upstream side header, Ao-outside air, A-compressed air, Ai-cooling air (cooling medium), F-fuel, G-combustion gas, Ar-rotor axis, Da-rotor axis direction, Dau-rotor axis upstream side, Dad-rotor axis downstream side, Pv-virtual plane, Ac-combustor axis (or simply axis),Dca-burner axis direction (or simply axis direction), Dcu-upstream side, Dcd-downstream side, Dcd-circumferential direction, Dci-inner side of the bend, Dco-outer side of the bend.

Claims

1. A transition piece, formed in a cylindrical shape around an axis curved in an imaginary plane so as to be along the axis, and defining a combustion gas flow path for combustion gas flowing from upstream to downstream in an axial direction extending from the axis, the transition piece comprising: a pair of side plates facing the imaginary plane and facing each other across the axis; a curved inner plate portion, disposed on the inner side of the curve where the downstream portion of the axis curves relative to the upstream portion, with the axis as a reference, and connected to one end of the inner side of the curve of the pair of side plates; and The curved outer plate portion is arranged on the curved outer side opposite to the curved inner side with the axis as a reference, faces the curved inner side plate portion across the axis, and is connected to one end of the curved outer side of the pair of side plates. The curved inner plate portion, the curved outer plate portion, and the pair of side plates each have: a plurality of passage groups, each consisting of a plurality of cooling passages extending in the axial direction and arranged in a circumferential direction relative to the axis for allowing a cooling medium to flow; and at least one header extending in the circumferential direction for allowing the cooling medium to flow. The plurality of passage groups of the curved inner plate portion, the curved outer plate portion, and the pair of side plates are arranged along the axial direction, and the headers are arranged between the plurality of passage groups in the axial direction. The plurality of passage groups of the curved inner plate portion, the curved outer plate portion, and the pair of side plate portions are connected to each other via the headers disposed between the plurality of passage groups. A medium inlet for the cooling medium to flow in is formed at one end on the downstream side of the plurality of cooling channels constituting the first channel group located closest to the downstream side among the plurality of channel groups of the curved inner plate portion, the curved outer plate portion, and the pair of side plates. A medium outlet for the cooling medium to flow out is formed at one end on the upstream side of the plurality of cooling channels constituting the final channel group located closest to the upstream side among the plurality of channel groups of the curved inner plate portion, the curved outer plate portion, and the pair of side plates. The number of the at least one header of the curved inner plate portion is smaller than the number of the at least one header of the curved outer plate portion and the pair of side plate portions.

2. The transition piece according to claim 1, wherein: In each of the curved inner plate portion, the curved outer plate portion and the pair of side plate portions, the total cross-sectional area per unit circumferential length of the plurality of cooling passages connected to the manifold and constituting the passage group on the upstream side with the manifold as a reference, that is, the passage density, is smaller than the passage density of the plurality of cooling passages connected to the manifold and constituting the passage group on the downstream side with the manifold as a reference.

3. The transition piece according to claim 2, wherein: In each of the curved inner plate portion, the curved outer plate portion, and a pair of side plate portions, the passage density in the final passage group is 25% to 45% of the passage density in the passage group located downstream of the header connected to the final passage group.

4. The transition piece according to any one of claims 1 to 3, wherein: In each of the curved inner plate portion, the curved outer plate portion and the pair of side plate portions, the number of multiple cooling passages connected to the header and constituting the passage group on the upstream side with the header as a reference is less than the number of multiple cooling passages connected to the header and constituting the passage group on the downstream side with the header as a reference.

5. The transition piece according to any one of claims 1 to 3, wherein: Each cross-sectional area of ​​the upstream side portion of the plurality of final cooling passages included in the curved inner plate portion is smaller than any cross-sectional area of ​​the downstream side portion of the plurality of final cooling passages included in the curved inner plate portion.

6. The transition piece according to any one of claims 1 to 3, wherein: The number of the at least one header on the curved inner plate portion is one, The number of the at least one header of the curved outer plate portion and the pair of side plate portions is two or more.

7. A burner comprising: The transition piece according to any one of claims 1 to 6; and The burner sprays fuel and compressed air into the combustion gas flow path.

8. A gas turbine comprising: The burner according to claim 7; a compressor, compressing air and delivering the compressed air to the burner; a turbine driven by the combustion gases generated in said combustor; and Intermediate housing, The compressor includes a compressor rotor rotatable about a rotor axis and a compressor housing covering an outer circumference of the compressor rotor. The turbine includes a turbine rotor rotatable about the rotor axis and a turbine housing covering an outer circumference of the turbine rotor. The compressor rotor and the turbine rotor are connected to each other to form a gas turbine rotor, The compressor housing and the turbine housing are connected to each other via the intermediate housing. The transition piece of the combustor is arranged in the center casing so that the curved outer plate portion faces the gas turbine rotor and the curved inner plate portion faces the center casing.

9. A gas turbine device comprising: The gas turbine according to claim 8; a cooler to cool a portion of the air compressed by the compressor; and The booster compressor boosts the pressure of the air cooled by the cooler and delivers the boosted air as the cooling medium to the first cooling passages provided in the curved inner plate portion, the curved outer plate portion, and the pair of side plates.

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