Transition piece for gas turbine combustor, gas turbine combustor, gas turbine, and manufacturing method and modification method for transition piece for gas turbine combustor

Abstract

Provided are a transition piece for a gas turbine combustor that can suppress wear of a seal groove while suppressing detachment of a seal member, a gas turbine combustor, a gas turbine, and a method for manufacturing and modifying a transition piece for a gas turbine combustor. [Solution] A transition piece for a gas turbine combustor comprises a frame portion that forms an outlet portion of the transition piece, and the circumferential side portion of the frame portion is provided on the circumferential end face of the frame portion and includes a radial groove extending along the radial direction, a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece, and an upstream portion located upstream of the radial groove in the flow direction, and comprises a plate-like member at least partially accommodated in the radial groove, and a joining portion that joins one of the two surfaces of the plate-like member in the flow direction that faces downstream in the flow direction and a surface of the downstream portion of the circumferential side portion that faces the circumferential direction.

Description

[Technical Field]

[0001] The present disclosure relates to a transition piece of a combustor for a gas turbine, a combustor for a gas turbine, a gas turbine, and a method for manufacturing and modifying a transition piece of a combustor for a gas turbine. [Background technology]

[0002] A seal is provided at the outlet of a transition piece of a combustor for a gas turbine to prevent air leakage from the combustor casing to the turbine section.

[0003] Patent Document 1 describes a combustor in which side seals are provided in seal grooves provided on the outer periphery of a frame portion provided at the downstream end of a transition piece of a gas turbine combustor. The side seals are provided to be positioned between the frame portions of circumferentially adjacent combustors. In addition, protective plates are provided on portions of the wall surfaces of the seal grooves into which the side seals are inserted that may come into contact with the side seals, thereby providing a measure against wear of the seal grooves. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2003-193866 Summary of the Invention [Problem to be solved by the invention]

[0005] In the gas turbine combustor described in Patent Document 1, a protective plate (plate-shaped member) is provided in the seal groove to suppress wear of the seal groove. However, depending on the method of attaching the plate-shaped member to the seal groove, there is a risk that the plate-shaped member may fall off due to wear caused by friction with the seal member during operation of the gas turbine.

[0006] In view of the above circumstances, at least one embodiment of the present invention has an object to provide a transition piece for a combustor for a gas turbine, a combustor for a gas turbine, a gas turbine, and a manufacturing method and a modification method for a transition piece for a combustor for a gas turbine, which are capable of suppressing wear of a seal groove while suppressing detachment of a seal member. [Means for solving the problem]

[0007] A transition piece of a gas turbine combustor according to at least one embodiment of the present invention includes: A transition piece for a gas turbine combustor, comprising: a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, a plate-like member at least partially received in the radial groove; a joint portion that joins a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; Equipped with.

[0008] Moreover, a gas turbine combustor according to at least one embodiment of the present invention includes: a burner for burning fuel; a combustion liner configured to guide combustion gas generated by the burner; Equipped with The combustion liner includes the transition piece described above.

[0009] Moreover, a gas turbine according to at least one embodiment of the present invention includes: a compressor for compressing air; a plurality of combustors as described above configured to combust compressed air from the compressor and fuel; a turbine configured to be driven by combustion gases from the combustor; radial seal members provided to fit into the radial grooves of a pair of the transition pieces adjacent to each other in the circumferential direction; Equipped with.

[0010] Further, a method for manufacturing a transition piece according to at least one embodiment of the present invention includes: A method for manufacturing a transition piece of a gas turbine combustor, comprising: The transition piece includes a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; joining a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; Prepare.

[0011] Further, a method for modifying a transition piece according to at least one embodiment of the present invention includes: A method for modifying a transition piece of a gas turbine combustor, comprising: The transition piece includes a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; joining a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; Equipped with. [Effects of the Invention]

[0012] According to at least one embodiment of the present invention, there are provided a transition piece for a gas turbine combustor, a gas turbine combustor, a gas turbine, and a manufacturing method and a modification method for a transition piece for a gas turbine combustor, which are capable of suppressing wear of a seal groove while suppressing detachment of a seal member. [Brief explanation of the drawings]

[0013] [Figure 1] FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment. [Figure 2] 1 is a schematic diagram illustrating a combustor and turbine inlet section of a gas turbine according to an embodiment; [Figure 3] FIG. 2 is a schematic exploded view (perspective view) of a transition piece of a combustor according to one embodiment. [Figure 4] 1 is a partial schematic (perspective) view of a combustor according to an embodiment; [Figure 5] 5 is a schematic cross-sectional view of a transition piece according to one embodiment, showing the cross section AA of FIG. 4. FIG. [Figure 6] 5 is a schematic cross-sectional view of a transition piece according to one embodiment, showing the cross section AA of FIG. 4. FIG. [Figure 7] 5 is a schematic cross-sectional view of a transition piece according to one embodiment, showing the cross section AA of FIG. 4. FIG. DETAILED DESCRIPTION OF THE INVENTION

[0014] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present invention.

[0015] (Gas turbine, combustor and transition piece configuration) Fig. 1 is a schematic configuration diagram of a gas turbine according to one embodiment. As shown in Fig. 1, the gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of a gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0016] The compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, becoming high-temperature, high-pressure compressed air.

[0017] The combustor 4 is supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustor 4 to generate combustion gas, which is the working fluid of the turbine 6. As shown in FIG. 1 , the gas turbine 1 has a plurality of combustors 4 arranged in a casing 20 along the circumferential direction around a rotor 8.

[0018] The turbine 6 has a combustion gas passage 28 formed by the turbine casing 22, and includes a plurality of stator vanes 24 and rotor blades 26 provided in the combustion gas passage 28. The stator vanes 24 are fixed to the turbine casing 22 side, and the plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The rotor blades 26 are implanted in the rotor 8, and the plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator vane rows and rotor blade rows are arranged alternately in the axial direction of the rotor 8 (the direction of the central axis O).

[0019] In the turbine 6, the combustion gas from the combustor 4 flows into a combustion gas passage 28 and passes through the plurality of stator vanes 24 and the plurality of rotor blades 26, thereby driving the rotor 8 to rotate, which in turn drives a generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas is discharged to the outside via an exhaust chamber 30.

[0020] FIG. 2 is a schematic diagram showing an inlet portion of a combustor 4 and a turbine 6 of a gas turbine 1 according to one embodiment.

[0021] As shown in FIG. 2, each of the plurality of combustors 4 (see FIG. 1) arranged annularly around the rotor 8 includes a combustion liner 36 provided in a combustor casing 32 defined by the casing 20, and a burner arranged in each of the combustion liner 36 for ejecting fuel. That is, in the gas turbine 1, a plurality of combustion liner 36 of the combustors 4 are arranged in the circumferential direction of the rotor 8. In the exemplary embodiment shown in the figure, the burner includes a first combustion burner 38 and a plurality of second combustion burners 40 arranged to surround the first combustion burner 38. The combustor 4 may also include other components such as a bypass pipe (not shown) for bypassing combustion gas.

[0022] The combustion liner (combustor liner) 36 has an inner liner 48 arranged around the burner, and a transition piece 50 connected to the tip of the inner liner 48. The inner liner 48 and the transition piece 50 may form an integrated combustion liner.

[0023] The first combustion burner 38 and the second combustion burner 40 each include a fuel nozzle (not shown) for injecting fuel and a burner tube (not shown) arranged to surround the fuel nozzle. Fuel is supplied to each fuel nozzle via a fuel port 42, 44, respectively. Compressed air generated by the compressor 2 (see FIG. 1 ) is supplied into the combustor casing 32 via a casing inlet 41, and the compressed air flows from the combustor casing 32 into each burner tube. In each burner tube, the fuel injected from the fuel nozzle is mixed with the compressed air, and the mixture flows into the combustion tube 36, where it is ignited and combusted to generate combustion gas. The first combustion burner 38 may be a burner for generating a diffusion combustion flame, and the second combustion burner 40 may be a burner for combusting a premixed air-fuel mixture to generate a premixed combustion flame.

[0024] The combustion gas generated by the combustion of fuel in the combustor 4 as described above flows into the first stage stator vane 23 (the stator vane 24 located most upstream in the flow direction of the combustion gas) of the turbine 6 through the outlet portion 52 of the combustor 4 located at the downstream end of the transition piece 50.

[0025] Fig. 3 is a schematic exploded view (perspective view) of a transition piece of a combustor according to one embodiment. Fig. 4 is a partial schematic view (perspective view) of a combustor according to one embodiment. Figs. 5 to 7 are each a schematic cross-sectional view of a transition piece according to one embodiment, showing a cross section taken along line AA in Fig. 4. In the following description, unless otherwise specified, the circumferential direction, radial direction, and axial direction refer to the circumferential direction, radial direction, and axial direction, respectively, of the gas turbine 1.

[0026] As shown in FIGS. 3 and 4 , the transition piece 50 of the combustor 4 includes a frame portion 54 (frame portion) that forms an outlet portion of the transition piece 50 (i.e., an outlet portion 52 of the combustor 4). The frame portion 54 may form an outlet opening 51 of the transition piece 50. The frame portion 54 may have a flange shape that protrudes from the transition piece 50 toward the outside of the combustion liner 36 in the circumferential and radial directions. As shown in FIGS. 3 and 4 , the frame portion 54 includes an outer circumferential portion 56 and an inner circumferential portion 58 that each extend along the circumferential direction, and a pair of circumferential side portions 60 that are located at both ends in the circumferential direction and each extend along the radial direction. Each of the pair of circumferential side portions 60 is provided to connect the outer circumferential portion 56 and the inner circumferential portion 58.

[0027] 3 and 4, the frame portion 54 is provided with a seal groove 63 recessed from the outer peripheral surface of the frame portion 54. The seal groove 63 is provided in each of the outer peripheral portion 56 and the inner peripheral portion 58 and includes circumferential grooves 64, 66 extending along the circumferential direction, and a radial groove 68 recessed from the circumferential end faces 60a of the pair of circumferential side portions 60 and extending along the radial direction.

[0028] A seal is fitted in the seal groove 63 to reduce air leakage from the combustor casing 32 (see FIG. 2) to the combustion gas passage 28 (see FIG. 1) of the turbine 6. As shown in FIGS. 3 and 4, the seal may include circumferential seal members 70, 71 fitted in the circumferential grooves 64, 66, and a radial seal member 74 fitted in the radial groove 68. As shown in FIG. 4, the radial seal member 74 is provided to be fitted in the radial groove 68 of the transition pieces 50 of a pair of circumferentially adjacent combustors 4. The radial seal member 74 may be a plate-shaped seal member.

[0029] As shown in Figures 5 to 7, the circumferential side portion 60 of the frame portion 54 includes the above-mentioned radial groove 68, an upstream portion 61 located upstream of the radial groove 68 in the flow direction of the combustion gas in the transition piece, and a downstream portion 62 located downstream of the radial groove 68 in the flow direction.

[0030] As shown in FIGS. 5 to 7, the transition piece 50 includes a plate-like member 76 that is at least partially housed in the radial groove 68, and a joint 80 that joins the plate-like member 76 and the frame portion 54.

[0031] The plate-shaped member 76 has two surfaces in the flow direction of the combustion gas, a first surface 76a facing the upstream side in the flow direction, and a second surface 76b facing the downstream side in the flow direction. The plate-shaped member 76 may be provided so as to extend in the radial direction.

[0032] As shown in Figures 5 to 7, the above-mentioned joint 80 is arranged to join the second surface 76b (the surface facing downstream in the flow direction) of the plate-shaped member 76 to the surface facing circumferentially of the downstream portion 62 of the circumferential side portion 60 of the frame portion 54.

[0033] 5 and 6, the above-mentioned joint 80 joins the second surface 76b of the plate-shaped member 76 to the circumferential end surface 62a (part of the circumferential end surface 60a of the circumferential side portion 60) of the downstream portion 62 of the circumferential side portion 60 of the frame portion 54. In the exemplary embodiment shown in Fig. 7, the downstream portion 62 of the frame portion 54 has through openings 82 that open to the upstream end surface 62b and the downstream end surface 62c of the downstream portion 62 in the flow direction, and the above-mentioned joint 80 joins the second surface 76b of the plate-shaped member 76 to the inner wall surface 82a of the through openings 82.

[0034] In the above-described embodiment, the plate-like member 76 joined to the downstream portion 62 of the circumferential side portion 60 is provided inside the radial groove 68 of the circumferential side portion 60 of the frame portion 54. Therefore, when the radial seal member 74 is provided in the radial groove 68, the plate-like member 76 is positioned between the radial seal member 74 and the downstream portion 62. This effectively suppresses wear of the radial groove 68 due to friction between the radial seal member 74 and the downstream portion 62. Furthermore, the joint 80 is provided to join the surface of the plate-like member 76 facing downstream (the second surface 76b) to the surface of the downstream portion 62 facing circumferentially (the circumferential end surface 62a or the inner wall surface 82a of the through opening 82). Therefore, the plate-like member 76 and the frame portion 54 can be firmly joined by the joint 80. Furthermore, since the joint 80 can be provided in an area opposite the radial seal member 74 across the plate member 76 in the flow direction, even if wear occurs in the plate member 76 due to friction with the radial seal member 74, the joint 80 is less susceptible to this effect, and therefore, damage is less likely to occur in the joint 80. Therefore, according to the above-described embodiment, it is possible to effectively suppress wear of the radial groove 68 (seal groove) while suppressing detachment of the radial seal member 74.

[0035] In some embodiments, as shown in FIGS. 5 and 6, for example, the plate-like member 76 is provided so as to protrude beyond the circumferential end surface 62a of the downstream portion 62 in the circumferential direction.

[0036] In the embodiment described above, the plate-like member 76 protrudes in the circumferential direction beyond the circumferential end surface 62a (60a) of the downstream portion 62, and therefore the portion to be joined is exposed when viewed from the downstream side in the flow direction. Therefore, even without providing a through-opening 82 as shown in Fig. 7, for example, the plate-like member 76 can be easily joined to the frame portion 54 by working from the downstream side in the flow direction.

[0037] In some embodiments, as shown in FIG. 6, for example, the circumferential end face 62a (60a) of the downstream portion 62 is located closer to the combustion gas passage 49 formed by the transition piece than the circumferential end face 61a (60a) of the upstream portion 61.

[0038] According to the above-described embodiment, the circumferential end face 62a (60a) of the downstream portion 62 of the circumferential side portion 60 of the frame portion 54 is located closer to the combustion gas passage 49 than the circumferential end face 61a (60a) of the upstream portion 61, and therefore it is easy to arrange the plate-like member 76 so that it protrudes circumferentially beyond the circumferential end face 62a (60a) of the downstream portion 62. Therefore, it is easy to appropriately join the plate-like member 76 to the frame portion 54.

[0039] When forming the radial grooves 68 in the circumferential side portion 60 of the frame portion 54, the circumferential end surface 60a is usually flat before the grooves are formed. Therefore, the circumferential end surface 62a (60a) of the downstream portion 62 and the circumferential end surface 61a (60a) of the upstream portion 61 are positioned in the same circumferential direction. The plate-like member 76 needs to be positioned so as not to exceed the thermal elongation limiting position L1 (see FIGS. 5 to 7 ). If the position of the circumferential end surface 60a is close to the thermal elongation limiting position L1, the downstream portion 62 can be cut away or otherwise processed to position the circumferential end surface 62a of the downstream portion 62 closer to the combustion gas passage 49. By joining the plate-like member 76 to the downstream portion 62 thus obtained, the plate-like member 76 can be positioned so as not to exceed the thermal elongation limiting position L1.

[0040] As already mentioned above, in some embodiments, as shown in FIG. 7, for example, the joint 80 joins the second surface 76b of the plate-like member 76 and the inner wall surface 82a of the through-opening 82 together.

[0041] According to the above-described embodiment, the plate-like member 76 provided in the radial groove 68 and the inner wall surface 82a of the through opening 82 are joined at the joint 80. Therefore, even if it is not possible to dispose the plate-like member 76 so that it protrudes beyond the circumferential end surface 62a of the downstream section 72 as described above for some reason (for example, when considering restrictions on thermal expansion of the frame portion 54), the plate-like member 76 can be appropriately joined to the frame portion 54. Therefore, it is possible to effectively suppress wear of the radial groove 68 while suppressing detachment of the radial seal member 74.

[0042] In some embodiments, the joint 80 may include a weld that joins the second surface 76b of the plate-shaped member 76 to a circumferentially facing surface of the downstream portion 62 (such as the circumferential end surface 62a or the inner wall surface 82a of the through opening 82). The weld may be a fillet weld.

[0043] According to the embodiment described above, the plate-shaped member 76 and the circumferential surface of the downstream portion 62 are joined via a weld, thereby firmly joining the plate-shaped member 76 and the frame portion 54. Therefore, it is possible to effectively prevent the radial seal member 74 from falling off and also effectively prevent wear of the radial groove 68 (seal groove).

[0044] In some embodiments, the plate-shaped member 76 may be formed from a cobalt-based alloy, which may contain 15 to 35 weight percent chromium and 0.7 to 1.5 weight percent carbon.

[0045] According to the above-described embodiment, the plate-like member 76 is formed from a cobalt-based alloy. That is, a member that is smaller than the frame portion 54 is made from a cobalt-based alloy, which is a wear-resistant material. Therefore, wear of the radial grooves 68 (seal grooves) can be effectively suppressed at lower cost than when the entire frame portion 54 is made from a cobalt-based alloy.

[0046] (Manufacturing and modification methods for transition pieces) A method for manufacturing and modifying the transition piece 50 according to several embodiments will now be described. In one embodiment, first, a plate-like member 76 is placed in the radial groove 68 of a transition piece having a frame portion 54 in which the radial groove 68 is formed. Next, the second surface 76b of the plate-like member 76 (the surface facing downstream in the flow direction of combustion gas) is joined to the surface facing the circumferential direction of the downstream portion 62 of the circumferential side portion 60 of the frame portion 54 (the circumferential end surface 62a or the inner wall surface 82a of the through opening 82). In this way, the transition piece 50 according to one embodiment can be obtained.

[0047] In one embodiment, before joining the plate-like member 76 and the frame portion 54, the circumferential side portion 60 of the frame portion 54 is processed (e.g., by cutting off the circumferential end portion of the downstream portion 62, as described above) so that the circumferential end surface 62a of the downstream portion 62 is positioned closer to the combustion gas passage 49 of the transition piece 50 than the circumferential end surface 61a of the upstream portion 61 in the circumferential direction. Then, after performing this processing, the plate-like member 76 and the downstream portion 62 are joined. In this way, even if the position of the circumferential end surface 62a before processing is close to the restricted position L1 due to thermal elongation, it is possible to position the circumferential end surface 62a of the downstream portion 62 closer to the combustion gas passage 49. By joining the plate-like member 76 to the downstream portion 62 obtained in this way, it is possible to install the plate-like member 76 at a position that does not exceed the restricted position L1 due to thermal elongation.

[0048] The contents described in each of the above embodiments can be understood, for example, as follows.

[0049] [1] At least one embodiment of the transition piece (50) of the present invention comprises: A transition piece for a combustor (4) for a gas turbine (1), a frame portion (54) that forms an outlet portion of the transition piece; The circumferential side portion (60) of the frame portion is a radial groove (68) provided on a circumferential end surface (60a) of the frame portion and extending along a radial direction; a downstream portion (62) located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion (61) located upstream of the radial groove in the flow direction; Including, a plate-like member (76) at least partially received in the radial groove; a joint (80) that joins a surface (second surface 76b) of the plate-like member facing downstream in the flow direction to a surface of the downstream portion of the circumferential side portion facing the circumferential direction; Equipped with.

[0050] In the configuration [1] described above, a plate-shaped member is provided inside the radial groove in the circumferential side of the frame portion and is joined to the downstream portion of the circumferential side. Therefore, when the seal member (radial seal member 74) is installed in the radial groove, the plate-shaped member is positioned between the seal member and the downstream portion. This effectively suppresses wear of the radial groove due to friction between the seal member and the downstream portion. Furthermore, a joint is provided that joins the downstream-facing surface of the plate-shaped member to the circumferential-facing surface of the downstream portion. This joint firmly joins the plate-shaped member to the frame portion. Furthermore, this joint can be provided in an area opposite the seal member across the plate-shaped member in the flow direction. Therefore, even if wear occurs in the plate-shaped member due to friction with the seal member, the joint is less affected, and therefore, the joint is less likely to break. Therefore, the configuration [1] described above effectively suppresses wear of the radial groove (seal groove) while suppressing detachment of the seal member.

[0051] [2] In some embodiments, in the configuration of [1] above, The plate-like member protrudes in the circumferential direction beyond the circumferential end surface (62a, 60a) of the downstream portion.

[0052] In the configuration [2] above, the plate-like member protrudes in the circumferential direction beyond the circumferential end face of the downstream portion, so that the portion to be joined is exposed when viewed from the downstream side in the flow direction. Therefore, the plate-like member can be easily joined to the frame portion by working from the downstream side in the flow direction.

[0053] [3] In some embodiments, in the configuration of [2] above, The portion of the plate-like member that protrudes beyond the circumferential end face of the downstream portion and the circumferential end face of the downstream portion are joined at the joint.

[0054] According to the configuration [3] above, the portion of the plate-like member that protrudes beyond the circumferential end face of the downstream portion is joined to the circumferential end face of the downstream portion. Therefore, as described in [2] above, the plate-like member can be easily joined to the frame portion, and as described in [1] above, it is possible to effectively suppress wear of the radial groove while suppressing detachment of the radial seal member.

[0055] [4] In some embodiments, in the configuration of [1] or [2] above, the downstream portion of the frame portion has through-openings (82) that open to an upstream end face (62b) and a downstream end face (62c) of the downstream portion in the flow direction, The plate-like member and the inner wall surface (82a) of the through opening are joined at the joint.

[0056] According to the configuration [4] above, a through-hole is provided in the downstream portion of the frame portion, and the plate-shaped member provided in the radial groove is joined to the inner wall surface of the through-hole at a joint. Therefore, even if, for some reason (for example, when considering thermal expansion of the frame portion), it is not possible to arrange the plate-shaped member so that it protrudes beyond the circumferential end face of the downstream portion as in [3] above, the plate-shaped member can be appropriately joined to the frame portion. This makes it possible to effectively suppress wear of the radial groove while suppressing detachment of the sealing member, as described in [1] above.

[0057] [5] In some embodiments, in any of the configurations [1] to [4] above, The circumferential end face of the downstream portion is located closer to the combustion gas passage (49) formed by the transition piece than the circumferential end face of the upstream portion in the circumferential direction.

[0058] According to the configuration [5] above, the circumferential end face of the downstream portion of the circumferential side of the frame is located closer to the combustion gas passage than the circumferential end face of the upstream portion, making it easier to position the plate-like member so that it protrudes circumferentially beyond the circumferential end face of the downstream portion. This makes it easier to properly join the plate-like member to the frame.

[0059] [6] In some embodiments, in any of the configurations [1] to [5] above, The joint portion includes a weld portion that joins the plate-shaped member and the surface of the downstream portion facing the circumferential direction.

[0060] According to the configuration [6] above, the plate-shaped member and the circumferential surface of the downstream portion are joined via a weld, so that the plate-shaped member and the frame portion can be firmly joined together. Therefore, as described in [1] above, it is possible to effectively suppress wear of the radial groove (seal groove) while suppressing the detachment of the seal member.

[0061] [7] In some embodiments, in any of the configurations [1] to [6] above, The plate-shaped member is made of a cobalt-based alloy.

[0062] According to the above-mentioned configuration [7], the plate-shaped member is made of a cobalt-based alloy. That is, a small member relative to the frame is made of a cobalt-based alloy, which is a wear-resistant material. Therefore, wear of the seal groove can be effectively suppressed at low cost compared to when the entire frame is made of a cobalt-based alloy.

[0063] [8] At least one embodiment of the present invention provides a gas turbine combustor (4), a burner for burning fuel; a combustion liner (36) configured to guide combustion gas generated by the burner; Equipped with The combustion liner includes the transition piece according to any one of [1] to [7] above.

[0064] In the configuration [8] described above, a plate-shaped member is provided inside the radial groove in the circumferential side of the frame portion and is joined to the downstream portion of the circumferential side. Therefore, when the seal member is installed in the radial groove, the plate-shaped member is positioned between the seal member and the downstream portion. This effectively suppresses wear of the radial groove due to friction between the seal member and the downstream portion. Furthermore, a joint is provided that joins the downstream-facing surface of the plate-shaped member to the circumferential-facing surface of the downstream portion. This joint firmly joins the plate-shaped member to the frame portion. Furthermore, this joint can be provided in an area opposite the seal member across the plate-shaped member in the flow direction. Therefore, even if wear occurs in the plate-shaped member due to friction with the seal member, the joint is less affected, and therefore, the joint is less likely to break. Therefore, the configuration [8] described above effectively suppresses wear of the radial groove (seal groove) while suppressing detachment of the seal member.

[0065] [9] At least one embodiment of the gas turbine (1) of the present invention comprises: a compressor (2) for compressing air; A plurality of combustors (4) according to the above [8] configured to combust compressed air from the compressor and fuel; a turbine (6) configured to be driven by combustion gases from the combustor; radial seal members (74) provided to fit into the radial grooves of a pair of the transition pieces adjacent to each other in the circumferential direction; Equipped with.

[0066] In the configuration [9] described above, a plate-shaped member is provided inside the radial groove in the circumferential side of the frame portion and is joined to the downstream portion of the circumferential side. Therefore, when the seal member is installed in the radial groove, the plate-shaped member is positioned between the seal member and the downstream portion. This effectively suppresses wear of the radial groove due to friction between the seal member and the downstream portion. Furthermore, a joint is provided that joins the downstream-facing surface of the plate-shaped member to the circumferential-facing surface of the downstream portion. This joint firmly joins the plate-shaped member to the frame portion. Furthermore, this joint can be provided in an area opposite the seal member across the plate-shaped member in the flow direction. Therefore, even if wear occurs in the plate-shaped member due to friction with the seal member, the joint is less affected and therefore less likely to break. Therefore, the configuration [9] described above effectively suppresses wear of the radial groove (seal groove) while suppressing detachment of the seal member.

[0067]

[10] A method for manufacturing a transition piece according to at least one embodiment of the present invention includes: A method of manufacturing a transition piece (50) of a gas turbine combustor, comprising: The transition piece includes a frame portion (54) that forms an outlet portion of the transition piece, The circumferential side portion (60) of the frame portion is a radial groove (68) provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion (62) located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion (61) located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; a step of joining a surface (second surface 76b) of the plate-like member facing downstream in the flow direction to a surface of the downstream portion of the circumferential side portion facing the circumferential direction; Prepare.

[0068] In the method

[10] described above, a plate-shaped member is provided inside the radial groove in the circumferential side of the frame portion and is joined to the downstream portion of the circumferential side. Therefore, when the seal member is installed in the radial groove, the plate-shaped member is positioned between the seal member and the downstream portion. This effectively suppresses wear of the radial groove due to friction between the seal member and the downstream portion. Furthermore, a joint is provided that joins the downstream-facing surface of the plate-shaped member to the circumferential-facing surface of the downstream portion. This joint firmly joins the plate-shaped member and the frame portion. Furthermore, this joint can be provided in an area opposite the seal member across the plate-shaped member in the flow direction. Therefore, even if wear occurs in the plate-shaped member due to friction with the seal member, the joint is less affected, and therefore, the joint is less likely to break. Therefore, the method

[10] described above effectively suppresses wear of the radial groove (seal groove) while suppressing detachment of the seal member.

[0069]

[11] In some embodiments, in the method of

[10] above, The method for manufacturing the transition piece includes: processing the circumferential side portion of the frame portion so that the circumferential end surface of the downstream portion is located closer to a combustion gas passage formed by the transition piece in the circumferential direction than the circumferential end surface of the upstream portion, The joining step joins the plate-like member to the surface of the downstream portion facing the circumferential direction after the processing step.

[0070] According to the method

[11] above, the circumferential end face of the downstream portion of the circumferential side of the frame portion is located closer to the combustion gas passage than the circumferential end face of the upstream portion, so it is easy to position the plate-like member so that it protrudes circumferentially beyond the circumferential end face of the downstream portion. This makes it easy to properly join the plate-like member to the frame portion.

[0071]

[12] A method for modifying a transition piece according to at least one embodiment of the present invention includes: A method for modifying a transition piece (50) of a gas turbine combustor, comprising: The transition piece includes a frame portion (54) that forms an outlet portion of the transition piece, The circumferential side portion (60) of the frame portion is a radial groove (68) provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion (62) located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion (61) located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; a step of joining a surface (second surface 76b) of the plate-like member facing downstream in the flow direction to a surface of the downstream portion of the circumferential side portion facing the circumferential direction; Equipped with.

[0072] In the method

[12] described above, a plate-shaped member is provided inside the radial groove in the circumferential side of the frame portion and is joined to the downstream portion of the circumferential side. Therefore, when the seal member is provided in the radial groove, the plate-shaped member is positioned between the seal member and the downstream portion. This effectively suppresses wear of the radial groove due to friction between the seal member and the downstream portion. Furthermore, a joint is provided between the downstream surface of the plate-shaped member and the circumferential surface of the downstream portion, thereby firmly joining the plate-shaped member and the frame portion. Furthermore, this joint can be provided in an area opposite the seal member across the plate-shaped member in the flow direction. Therefore, even if wear occurs in the plate-shaped member due to friction with the seal member, the joint is less affected, and therefore, the joint is less likely to be damaged. Therefore, the method

[12] described above effectively suppresses wear of the radial groove (seal groove) while suppressing detachment of the seal member.

[0073]

[13] In some embodiments, in the method of

[12] above, The method for modifying the tailpipe includes: processing the circumferential side portion of the frame portion so that the circumferential end surface of the downstream portion is located closer to a combustion gas passage formed by the transition piece in the circumferential direction than the circumferential end surface of the upstream portion, The joining step joins the plate-like member to the surface of the downstream portion facing the circumferential direction after the processing step.

[0074] According to the method

[13] , the circumferential end face of the downstream portion of the circumferential side of the frame is located closer to the combustion gas passage than the circumferential end face of the upstream portion, so it is easy to position the plate-like member so that it protrudes circumferentially beyond the circumferential end face of the downstream portion. This makes it easy to properly join the plate-like member to the frame.

[0075] The above describes an embodiment of the present invention, but the present invention is not limited to the above-described embodiment, and also includes forms in which the above-described embodiment is modified, or forms in which these forms are appropriately combined.

[0076] In this specification, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement strictly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. Furthermore, in this specification, expressions representing shapes such as a rectangular shape or a cylindrical shape not only represent rectangular shapes or cylindrical shapes in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. Furthermore, in this specification, the expressions "comprise," "include," or "have" a component are not exclusive expressions that exclude the presence of other components. [Explanation of symbols]

[0077] 1. Gas turbine 2 Compressor 4 Combustor 6 Turbine 8 rotors 10 Compressor compartment 12 Air intake 16 Stator blade 18 Moving blade 20 Casing 22 Turbine casing 23 1st stage stator vane 24 Stator blade 26 Moving blade 28 Combustion gas passage 30 Exhaust chamber 32 Combustor casing 36 Combustion tube 38 First combustion burner 40 Second combustion burner 41 Cabin entrance 42 fuel port 44 fuel port 48 Inner cylinder 49 Combustion gas passage 50 Tailpiece 51 Exit opening 52 Exit section 54 Frame section 56 Outer part 58 Inner part 60 Circumferential side 60a Circumferential end face 61 Upstream part 61a Circumferential end face 62 Downstream part 62a Circumferential end face 62b Upstream end face 62c Downstream end face 63 Seal groove 64 Circumferential groove 66 Circumferential groove 68 Radial groove 70 Circumferential seal member 71 Circumferential seal member 72 Downstream part 74 Radial seal member 76 Plate-shaped members 76a 1st page 76b 2nd side 80 Joint 82 Through opening 82a Inner wall L1 Thermal expansion limit position O center axis

Claims

1. A transition piece for a gas turbine combustor, comprising: a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, a plate-like member at least partially received in the radial groove; a joint portion that joins a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; A tailpipe equipped with a tailpipe.

2. The plate-shaped member protrudes in the circumferential direction beyond the circumferential end surface of the downstream portion. The transition piece according to claim 1.

3. a portion of the plate-like member that protrudes beyond the circumferential end surface of the downstream portion and the circumferential end surface of the downstream portion are joined at the joint portion; The transition piece according to claim 2.

4. the downstream portion of the frame portion has through-openings that open to an upstream end surface and a downstream end surface of the downstream portion in the flow direction, The plate-like member and the inner wall surface of the through opening are joined at the joint. The transition piece according to claim 1 or 2.

5. The circumferential end surface of the downstream portion is located closer to the combustion gas passage formed by the transition piece in the circumferential direction than the circumferential end surface of the upstream portion. A transition piece according to any one of claims 1 to 3.

6. The joint portion includes a weld portion that joins the plate-shaped member and the surface of the downstream portion facing the circumferential direction. A transition piece according to any one of claims 1 to 3.

7. The plate-shaped member is made of a cobalt-based alloy. A transition piece according to any one of claims 1 to 3.

8. a burner for burning fuel; a combustion liner configured to guide combustion gas generated by the burner; Equipped with The combustion liner includes a transition piece according to any one of claims 1 to 3. Combustor for gas turbine.

9. a compressor for compressing air; a plurality of combustors as recited in claim 8 configured to combust compressed air from the compressor with fuel; a turbine configured to be driven by combustion gases from the combustor; radial seal members provided to fit into the radial grooves of a pair of the transition pieces adjacent to each other in the circumferential direction; A gas turbine comprising:

10. A method for manufacturing a transition piece of a gas turbine combustor, comprising: The transition piece includes a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; joining a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; Equipped with Manufacturing method of tail pipe

11. processing the circumferential side portion of the frame portion so that the circumferential end surface of the downstream portion is located closer to a combustion gas passage formed by the transition piece in the circumferential direction than the circumferential end surface of the upstream portion, The joining step includes joining the plate-like member and the surface of the downstream portion facing the circumferential direction after the processing step. A method for manufacturing the transition piece according to claim 10.

12. A method for modifying a transition piece of a gas turbine combustor, comprising: The transition piece includes a frame portion that forms an outlet portion of the transition piece, The circumferential side portion of the frame portion is a radial groove provided on a circumferential end surface of the frame portion and extending along a radial direction; a downstream portion located downstream of the radial groove in the flow direction of combustion gas in the transition piece; an upstream portion located upstream of the radial groove in the flow direction; Including, placing a plate-like member in the radial groove; joining a surface of the plate-like member facing a downstream side in the flow direction to a surface of the downstream portion of the circumferential side portion facing a circumferential direction; Equipped with How to modify the tailpipe.

13. processing the circumferential side portion of the frame portion so that the circumferential end surface of the downstream portion is located closer to a combustion gas passage formed by the transition piece in the circumferential direction than the circumferential end surface of the upstream portion, The joining step includes joining the plate-like member and the surface of the downstream portion facing the circumferential direction after the processing step. The method for modifying a transition piece according to claim 12.

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