Blade ring assembly and gas turbine provided with same

Abstract

A blade ring assembly according to the present disclosure is provided with: a turbine blade ring extending in a circumferential direction centered on an axis; a stationary blade disposed on the inner peripheral side of the turbine blade ring; and a deflector disposed on the outer peripheral side of at least a portion of the turbine blade ring. The turbine blade ring is provided with: a blade ring body; and a plurality of protruding parts which protrude from the blade ring body toward the upstream side of the axis from both sides in the axial direction in which the axis extends, and which are disposed at different positions in the circumferential direction at intervals from each other. Two circumferentially adjacent protrusions included in the plurality of protrusions together with the blade ring main body form a cooling medium intake port leading from the outer peripheral side to the inner peripheral side of the turbine blade ring, and the deflector is disposed so as to shield at least a portion of the cooling medium intake port when viewed from a radial direction centered on the axis.

Description

Technical Field

[0001] The present disclosure relates to a bling assembly and a gas turbine including the bling assembly.

[0002] This application claims priority to Japanese Patent Application No. 2022-165186, filed on October 14, 2022, the contents of which are incorporated herein by reference. Background Art

[0003] Patent Document 1 discloses a gas turbine having a mechanism for separating particles contained in cooling air. The gas turbine has a particle separation protection element disposed on the inner peripheral side (rotor side) of the stator blades, and the particle separation protection element makes it difficult for floating particles to flow into the intake opening.

[0004] Prior art literature

[0005] Patent Literature

[0006] Patent Document 1: Japanese Patent Application No. 2010-501764 Summary of the invention

[0007] Problems to be solved by the invention

[0008] However, the particle separation protection element described in Patent Document 1 does not prevent the cooling air supplied from the compressor into the casing from directly flowing into the air passage connected to the interior of the stator blade. Therefore, cooling air containing foreign matter sometimes flows into the interior of the stator blade, causing blockage in the cooling path inside the stator blade.

[0009] The present disclosure has been made to solve the above-mentioned problems, and an object of the present disclosure is to provide a blade ring assembly capable of suppressing the inflow of foreign matter into a stationary blade, and a gas turbine including the blade ring assembly.

[0010] Means for solving problems

[0011] In order to solve the above-mentioned problems, the blade ring assembly disclosed in the present invention comprises: a turbine blade ring, which extends in a circumferential direction centered on an axis; stationary blades, which are arranged on the inner circumferential side of the turbine blade ring; and a deflector, which is arranged on the outer circumferential side of at least a portion of the turbine blade ring, the turbine blade ring having: a blade ring body; and a plurality of protrusions, which protrude from the upstream side of the axis on both sides in the axial direction extending from the blade ring body toward the axis, and are arranged at different positions in the circumferential direction at intervals from each other, two protrusions adjacent to each other in the circumferential direction included in the plurality of protrusions together with the blade ring body form a cooling medium inlet leading from the outer circumferential side of the turbine blade ring to the inner circumferential side, and when observed from a radial direction centered on the axis, the deflector is configured to block at least a portion of the cooling medium inlet.

[0012] In order to solve the above-mentioned problems, the gas turbine disclosed in the present invention comprises: a rotor, which can rotate around the axis; a casing, which covers the rotor from the outer peripheral side; the above-mentioned blade ring assembly, which covers the rotor from the outer peripheral side in a state supported by the casing; and a combustor, which generates combustion gas by combustion of fuel and transports the combustion gas into the casing, and the stator blades included in the blade ring assembly are the first-stage turbine stator blades in the axial direction.

[0013] Effects of the Invention

[0014] The blade ring assembly and the gas turbine equipped with the blade ring assembly disclosed herein can suppress the inflow of foreign matter into the stator blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a cross-sectional view schematically showing the entire gas turbine according to the first embodiment of the present disclosure.

[0016] Figure 2 This is a cross-sectional view showing a part of the gas turbine according to the first embodiment of the present disclosure in an enlarged manner.

[0017] Figure 3 It is a cross-sectional view schematically showing a part of the bling assembly according to the first embodiment of the present disclosure.

[0018] Figure 4 This is a perspective view showing a part of the blade ring assembly according to the first embodiment of the present disclosure in an exploded manner.

[0019] Figure 5 yes Figure 3 A cross-sectional view of the bling assembly along line VV is shown.

[0020] Figure 6 It is a top view showing the deflector according to the first embodiment of the present disclosure.

[0021] Figure 7 It is a front view showing the deflector according to the first embodiment of the present disclosure.

[0022] Figure 8 It is a cross-sectional view showing the shielding cover according to the first embodiment of the present disclosure.

[0023] Fig. 9 It is a cross-sectional view showing the operation of the deflector according to the first embodiment of the present disclosure.

[0024] Fig.10 It is a perspective view showing a part of the bling assembly according to the second embodiment of the present disclosure.

[0025] Fig.11 It is a top view showing a deflector according to a second embodiment of the present disclosure.

[0026] Fig.12 It is a cross-sectional view showing the operation of the deflector according to the second embodiment of the present disclosure.

[0027] Fig.13 It is a perspective view showing a deflector according to another embodiment of the present disclosure. DETAILED DESCRIPTION

[0028] <First embodiment>

[0029] Hereinafter, a bale ring assembly according to a first embodiment of the present disclosure and a gas turbine equipped with the bale ring assembly will be described with reference to the accompanying drawings. In the following description, the same reference numerals are used for structures having the same or similar functions, and repeated descriptions of these structures may be omitted.

[0030] (Structure of gas turbine)

[0031] Figure 1 The gas turbine 10 is a cross-sectional view schematically showing the entirety of the gas turbine 10 in the present embodiment. The gas turbine 10 includes a compressor 20 for compressing air A, a combustor 30 for burning fuel F in the air A compressed by the compressor 20 to generate combustion gas G, and a turbine 40 driven by the combustion gas G.

[0032] The compressor 20 includes a compressor rotor 21 that rotates about the axis Ar, a compressor casing 25 that covers the outer circumference of the compressor rotor 21, and a plurality of stationary blade stages 26. The turbine 40 includes a turbine rotor 41 that rotates about the axis Ar, a turbine casing 45 that covers the outer circumference of the turbine rotor 41, and a plurality of stationary blade stages 46.

[0033] The compressor rotor 21 and the turbine rotor 41 are located on the same axis Ar and are connected to each other to form a gas turbine rotor 11. For example, a rotor of a generator GEN is connected to the gas turbine rotor 11. The compressor chamber 25 and the turbine chamber 45 are connected to each other to form a gas turbine chamber 15. The gas turbine chamber 15 is an example of a "casing". The combustor 30 is, for example, a can-type combustor.

[0034] Here, in the following description, the direction in which the axis Ar extends is defined as "axial direction Da", the circumferential direction centered on the axis Ar is defined as "circumferential direction Dc", and the direction centered on the axis Ar and perpendicular to the axis Ar is defined as "radial direction Dr". The side of the compressor 20 based on the turbine 40 on both sides in the axial direction Da is defined as "axial upstream side Dau", and the opposite side is defined as "axial downstream side Dad". In addition, the side close to the axis Ar on both sides in the radial direction Dr is defined as "radial inner side Dri", and the opposite side is defined as "radial outer side Dro". In addition, the side from the positive pressure surface of the blade body 110 of the stator 46a described later to the negative pressure surface on both sides in the circumferential direction Dc is defined as "circumferential direction Dcn", and the side from the negative pressure surface of the blade body 110 to the positive pressure surface is defined as "circumferential direction Dcp". The axial direction Da is the flow direction of the combustion gas G.

[0035] The compressor rotor 21 has a rotor shaft 22 extending along the axial direction Da with the axis Ar as the center, and a plurality of moving blade stages 23 mounted on the rotor shaft 22. The plurality of moving blade stages 23 are arranged at intervals in the axial direction Da. Each moving blade stage 23 is composed of a plurality of moving blades 23a arranged along the circumferential direction Dc. A stationary blade stage 26 is arranged on the axial downstream side Dad of each of the plurality of moving blade stages 23. Each stationary blade stage 26 is mounted on the inner side of the compressor casing 25. Each stationary blade stage 26 is composed of a plurality of stationary blades 26a arranged along the circumferential direction Dc.

[0036] The turbine rotor 41 has a rotor shaft 42 extending along the axial direction Da with the axis Ar as the center, and a plurality of moving blade stages 43 mounted on the rotor shaft 42. The plurality of moving blade stages 43 are arranged along the axial direction Da. Each moving blade stage 43 is composed of a plurality of moving blades 43a arranged along the circumferential direction Dc. A stationary blade stage 46 is arranged on the axial upstream side Dau of each of the plurality of moving blade stages 43. Each stationary blade stage 46 is mounted on the inner side of the turbine chamber 45. Each stationary blade stage 46 is composed of a plurality of gas turbine stationary blades 46a arranged along the circumferential direction Dc. Hereinafter, for the sake of convenience of explanation, the gas turbine stationary blades 46a are referred to as "stationary blades 46a".

[0037] Figure 2 FIG. 1 is a cross-sectional view showing a part of the gas turbine 10 according to the embodiment in an enlarged manner. Figure 2 Schematically shows Figure 3 The cross section of the blade ring assembly WS shown along the II-II line. The turbine chamber 45 has a cylindrical outer chamber 45a constituting the outer shell of the turbine chamber 45, an inner chamber 45b fixed to the inner side of the outer chamber 45a, and a plurality of segmented rings 45c fixed to the inner side of the inner chamber 45b. The plurality of segmented rings 45c are each arranged between two adjacent stationary blade stages 46 among the plurality of stationary blade stages 46. The moving blade stage 43 is arranged on the radial inner side Dri of each segmented ring 45c.

[0038] The space between the rotor shaft 42 and the turbine chamber 45 in the radial direction Dr and in which the stationary blades 46a and the moving blades 43a are arranged is a flow path for the combustion gas G from the combustor 30 to flow. Hereinafter, the above-mentioned flow path for the combustion gas G from the combustor 30 to flow is referred to as a "combustion gas flow path 49". The combustion gas flow path 49 is formed as an annular space centered on the axis Ar and is long in the axial direction Da.

[0039] The gas turbine 10 in this embodiment includes a cooling device 50 for supplying cooling air to the second-stage and subsequent stator blades 46a and the ring splitter 45c from the axial upstream side Dau. The cooling device 50 includes a foreign matter trap 51, a cooler 52, a supercharger 53, and a cooling air line 54.

[0040] The foreign matter trap 51 is, for example, a filter having a plurality of fine pores, and separates foreign matter contained in the cooling air flowing in the cooling air line 54. The cooler 52 cools the cooling air flowing in the cooling air line 54. The booster compressor 53 boosts the pressure of the cooling air flowing in the cooling air line 54. The cooling air line 54 extracts the compressed air Ac in the gas turbine chamber 15 as cooling air, and supplies the extracted cooling air to the inside of the outer chamber 45a via the foreign matter trap 51, the cooler 52, and the booster compressor 53.

[0041] A cooling air passage 45p is formed in the inner chamber 45b of the turbine chamber 45, which passes from the radially outer side Dro to the radially inner side Dri. The cooling air supplied from the cooling air line 54 to the inner side of the outer chamber 45a is introduced into the second-stage and later stator blades 46a and the split ring 45c via the cooling air passage 45p of the inner chamber 45b, and is used for cooling these stator blades 46a and the split ring 45c. Here, by arranging the foreign matter trap 51 in the cooling air line 54, it is difficult for foreign matter to reach the second-stage and later stator blades 46a and the split ring 45c. It should be noted that the path for supplying cooling air to the stator blades 46a is not limited to the above.

[0042] (Gas turbine operation)

[0043] return Figure 1, the operation of the gas turbine 10 will be described. The compressor 20 compresses the air A to generate compressed air Ac. A portion (most of) of the compressed air Ac generated by the compressor 20 flows into the combustor 30. The fuel F is supplied to the combustor 30. In the combustor 30, the fuel F burns in the compressed air Ac to generate a high-temperature and high-pressure combustion gas G. The combustion gas G generated by the combustor 30 is transported from the combustor 30 to the combustion gas flow path 49 in the turbine 40. The combustion gas G rotates the turbine rotor 41 while flowing toward the axial downstream side Dad in the combustion gas flow path 49. Along with the rotation of the turbine rotor 41, the rotor of the generator GEN connected to the gas turbine rotor 11 rotates. As a result, the generator GEN generates electricity.

[0044] (Leaf ring assembly)

[0045] like Figure 2 As shown, the gas turbine 10 includes a bale assembly WS. The bale assembly WS is arranged on the inner peripheral side of the gas turbine casing 15. The bale assembly WS in the present embodiment is arranged on the most upstream side (most axial upstream side Dau) of the turbine 40 in the axial direction Da.

[0046] The blade ring assembly WS includes a turbine blade ring 70, a plurality of stator blades 46a1 that respectively form a plurality of stator blades 46a of the first stage in the axial direction Da, and an inducer 90. The compressed air Ac supplied from the compressor 20 to the gas turbine chamber 15 is directly supplied to the first-stage stator blades 46a1 in this embodiment as cooling air without passing through the foreign matter trap 51. Therefore, the turbine blade ring 70 in this embodiment is equipped with an inducer 90 for suppressing foreign matter contained in the compressed air Ac from reaching the stator blades 46a1. This content will be described in detail below. In the following, for the sake of convenience, compressed air Ac is sometimes referred to as "cooling air Ac".

[0047] (Structure around the leaf ring assembly)

[0048] The gas turbine casing 15 has a front wall 61, a peripheral wall 62, and a rear wall 63 as wall portions defining an accommodation chamber R for accommodating the combustor 30. The accommodation chamber R is a space in the gas turbine casing 15 through which the compressed air Ac flows, and the blade ring assembly WS is exposed.

[0049] The front wall 61 is located on the axial upstream side Dau relative to the accommodation chamber R. The front wall 61 includes: a cylinder 61a having an opening 61h; and a cylindrical cover 61b, which is mounted on the cylinder 61a and covers the opening 61h. A part of the burner 30 is arranged inside the cylinder 61a and the cylindrical cover 61b. For example, the air intake part 31 of the burner 30 is arranged inside the cylindrical cover 61b.

[0050] The peripheral wall 62 is located at the radially outer side Dro relative to the accommodation chamber R. The peripheral wall 62 extends between the front wall 61 and the rear wall 63, connecting the front wall 61 and the rear wall 63 in the axial direction Da. The peripheral wall 62 has a first peripheral wall 62a and a second peripheral wall 62b. The first peripheral wall 62a is a portion connected to the front wall 61 from the axial downstream side Dad. The first peripheral wall 62a extends along the axial direction Da. The second peripheral wall 62b is a portion that is located at a position closer to the axial downstream side Dad than the first peripheral wall 62a in a state of being integrated with the first peripheral wall 62a and connected to the rear wall 63. The second peripheral wall 62b is, for example, an inclined portion (reduced diameter portion) inclined in a manner that is located at the radially inner side Dri as it approaches the axial downstream side Dad. The second peripheral wall 62b includes, for example, an arc portion that is steeper in inclination relative to the axial direction Da as it approaches the axial downstream side Dad.

[0051] The rear wall 63 is located on the axial downstream side Dad relative to the containment chamber R. The rear wall 63 is connected to the second peripheral wall 62b from the axial downstream side Dad. The rear wall 63 extends along the radial direction Dr. The rear wall 63 is a partition wall that blocks the axial downstream side Dad of the containment chamber R. A blade ring fixing portion 71 of a turbine blade ring 70 described later is fixed to the rear wall 63. The rear wall 63 is located closer to the axial downstream side Dad than the air intake port 72 of the turbine blade ring 70 described later.

[0052] When viewed from the compressor 20, a guide portion 64 for guiding the compressed air Ac to the accommodation chamber R is arranged at the inlet portion of the accommodation chamber R. The guide portion 64 is, for example, a guide vane arranged in a state inclined with respect to the axis Ar. The guide portion 64 changes the flow direction (flow direction) of the compressed air Ac flowing in from the compressor 20 toward the peripheral wall 62 of the gas turbine chamber 15, for example. However, the guide portion 64 may be omitted as long as a part of the compressed air Ac flowing in from the compressor 20 is directed toward the peripheral wall 62 or the rear wall 63.

[0053] (Structure of the leaf ring assembly)

[0054] Figure 3 It is a perspective view showing a part of the blade ring assembly WS.

[0055] The blade ring assembly WS includes a turbine blade ring 70, a plurality of combustor connecting members 80, and a plurality of stationary blades 46a1 (in Figure 3 Not shown in the figure, Figure 5 Only one stationary blade 46a1 is shown in the figure), a plurality of deflectors 90, a plurality of sealing members 85, and a plurality of shielding covers 150 (in Figure 3 Not shown in the figure, Figure 5 Only one shielding cover 150 is shown in the figure).

[0056] (Turbine blade ring)

[0057] The turbine blade ring 70 extends along the circumferential direction Dc centered on the axis Ar and is formed into a circular ring shape. The turbine blade ring 70 has an outer peripheral surface 70o, an inner peripheral surface 70i, an upstream end surface 70u, and a downstream end surface 70d. The outer peripheral surface 70o faces the radial outer side Dro. The outer peripheral surface 70o is exposed to the storage chamber R of the gas turbine chamber 15. The inner peripheral surface 70i is located on the side opposite to the outer peripheral surface 70o and faces the radial inner side Dri. The inner peripheral surface 70i faces the plurality of stationary blades 46a1. The upstream end surface 70u faces the axial upstream side Dau. The downstream end surface 70d is located on the side opposite to the upstream end surface 70u and faces the axial downstream side Dad.

[0058] The turbine brim 70 includes a brim body 7, a brim fixing portion 71, and a plurality of protrusions 73. The brim body 7 is formed, for example, in a cylindrical shape. The brim fixing portion 71 fixes the brim body 7 to the gas turbine chamber 15. The brim fixing portion 71 is integrally arranged with the brim body 7 at the end portion of the brim body 7 on the axial downstream side Dad. The brim fixing portion 71 is, for example, a flange extending from the brim body 7 to the radially outer side Dro. The brim fixing portion 71 is located on the radially inner side Dri (refer to the FIG. 10 ) of the rear wall 63 of the gas turbine chamber 15. Figure 2 The blade ring fixing portion 71 is supported in a state of being fixed to the rear wall 63 of the gas turbine casing 15 .

[0059] like Figure 3 As shown, a plurality of air inlets 72 are formed in the turbine blade ring 70. The plurality of air inlets 72 are arranged at predetermined intervals in the circumferential direction Dc and are spaced apart on the entire circumference of the turbine blade ring 70. The air inlet 72 penetrates from the outer peripheral surface 70o to the inner peripheral surface 70i of the turbine blade ring 70. The air inlet 72 is located at a position Dau upstream of the blade ring fixing portion 71 along the axis.

[0060] Figure 4 : is a perspective view showing a part of the blade ring assembly WS by disassembling it. The air intake port 72 in this embodiment is a cutout portion (groove portion) formed at the end of the axial upstream side Dau of the turbine blade ring 70. That is, the air intake port 72 is open to the axial upstream side Dau in a state of penetrating from the outer peripheral surface 70o to the inner peripheral surface 70i of the turbine blade ring 70. It should be noted that, instead of this, the air intake port 72 may also be a through hole penetrating from the outer peripheral surface 70o to the inner peripheral surface 70i in the central part of the turbine blade ring 70 in the axial direction Da. The air intake port 72 guides a part of the cooling air Ac flowing in the accommodation chamber R of the gas turbine casing 15 from the outer peripheral side to the inner peripheral side of the turbine blade ring 70. The air intake port 72 is an example of a "cooling medium intake port", and the compressed air Ac compressed by the compressor 20 is an example of a "cooling medium".

[0061] In the present embodiment, the above-mentioned air intake port 72 formed by cutting off the end portion of the turbine blade ring 70 on the axial upstream side Dau is formed with a plurality of protrusions 73 protruding from the blade ring body 7 toward the axial upstream side Dau. The plurality of protrusions 73 are arranged at different positions in the circumferential direction Dc at intervals from each other, and respectively protrude from the end surface of the blade ring body 7 facing the axial upstream side Dau toward the axial upstream side Dau. Hereinafter, the end surface of the blade ring body 7 facing the axial upstream side Dau is referred to as the "upstream surface 7s". The end surfaces of the plurality of protrusions 73 on the axial upstream side Dau constitute the upstream side end surface 70u of the above-mentioned turbine blade ring 70. The plurality of protrusions 73 and the plurality of air intake ports 72 are alternately arranged in the circumferential direction Dc (refer to Figure 3 ). Therefore, if Figure 4 As shown, with one air inlet 72 in focus, the plurality of protrusions 73 include a first protrusion 73a located on the side of the air inlet 72 in the circumferential direction Dcn and a second protrusion 73b located on the side of the air inlet 72 in the circumferential direction Dcp. The first protrusion 73a and the second protrusion 73b together with the blade ring body 7 form the air inlet 72 that leads from the outer peripheral side to the inner peripheral side of the turbine blade ring 70. In other words, the air inlet 72 is located between the first protrusion 73a and the second protrusion 73b in the circumferential direction Dc. The air inlet 72 in this embodiment is formed in a manner that becomes narrower as it moves toward the radial inner side Dri (see Figure 7 ). Hereinafter, for convenience of explanation, the narrowest portion of the air inlet 72 located closest to the radial inner side Dri is sometimes referred to as the "narrow portion 72a". The narrow portion 72a is formed, for example, between the end of the radial inner side Dri of the first protrusion 73a and the end of the radial inner side Dri of the second protrusion 73b. The narrow portion 72a is an example of a "smallest portion".

[0062] like Figure 5 As shown, the blade ring body 7 in this embodiment has a deflector fixing portion 75 protruding from the upstream surface 7s between the first protrusion 73a and the second protrusion 73b. The deflector fixing portion 75 is, for example, arranged at a central position between the first protrusion 73a and the second protrusion 73b (see Figure 4 The deflector fixing portion 75 is disposed in the air intake port 72 at the first protrusion 73 a and the second protrusion 73 b with a gap therebetween in the circumferential direction Dc (see Figure 4 ).like Figure 5As shown, the deflector fixing portion 75 has a support surface 75b facing the radial outer side Dro and a fixing surface 75a perpendicular to the support surface 75b and facing the axial upstream side Dau. The deflector 90 described later is mounted on these support surfaces 75b and fixing surfaces 75a. A coupling hole 75h that can be coupled with a coupling member 93 such as a bolt is formed on the fixing surface 75a of the deflector fixing portion 75. A plurality of (for example, two) coupling holes 75h are arranged on the fixing surface 75a.

[0063] It should be noted that if Figure 3 As shown, a cooling medium circulation portion 100 is provided in the adjacent first protrusion 73a and the second protrusion 73b. The cooling medium circulation portion 100 connects these first protrusions 73a and the second protrusions 73b in a manner spanning the first protrusion 73a and the second protrusion 73b. The cooling medium circulation portion 100 allows the cooling medium to flow in a cooling flow path (not shown) formed in the blade ring body 7. In the present disclosure, steam, air, etc. are used as the cooling medium, but the cooling medium is not limited thereto, and a medium that has fluidity and can be used for cooling the blade ring body 7 is appropriately used. The cooling medium circulation portion 100 is provided on the radially outer side Dro of the turbine blade ring 70, and overlaps with the air inlet 72 when viewed in the radial direction Dr. The cooling medium circulation portion 100 is an example of a "forced cooling component".

[0064] (Burner connecting member)

[0065] Next, the burner connecting member 80 will be described. The burner connecting member 80 is a fixing member for fixing the tail pipe 32 of the burner 30. Figure 3 As shown, a plurality of combustor connection members 80 are provided at positions corresponding to the plurality of protrusions 73 of the turbine blade ring 70 in the circumferential direction Dc. Figure 3 and Figure 4 As shown, the burner connecting member 80 has a frame portion 81 and a flange 82 .

[0066] The frame portion 81 is a portion to which the tail cylinder 32 of the burner 30 is connected. The tail cylinder 32 of the burner 30 is fixed to the frame portion 81 by welding, for example. The flange 82 is a portion extending from the frame portion 81 to the radially outer side Dro. The flange 82 has a planar shape along the circumferential direction Dc and the radial direction Dr. The flange 82 faces the end surface 73u of the axial upstream side Dau of the protrusion 73 in the axial direction Da. A coupling hole 73h that can be coupled with a coupling member 83 such as a bolt is formed on the end surface 73u of the axial upstream side Dau of the protrusion 73.

[0067] The flange 82 is formed with an insertion hole 82h through which the coupling piece 83 is inserted. The coupling piece 83 inserted through the insertion hole 82h of the flange 82 is coupled to the coupling hole 73h of the protrusion 73, thereby fixing the flange 82 to the protrusion 73. The end surface 73u of the protrusion 73 including the coupling hole 73h is an example of a "connection portion" that can be connected to the burner connection member 80. In the present embodiment, the end surface 73u of each of the first protrusion 73a and the second protrusion 73b described above has a coupling hole 73h for mounting the burner connection member 80.

[0068] (Stationary leaf)

[0069] Next, the stationary blade 46a1 will be described.

[0070] Figure 5 yes Figure 3 The sectional view of the leaf ring assembly WS along the V-V line is shown. Figure 5 The stationary blades 46a1 are arranged on the inner circumference of the turbine blade ring 70 and arranged in a row along the circumferential direction Dc. The stationary blades 46a1 are held by a holding member 74 provided on the turbine blade ring 70. The stationary blades 46a1 include a blade body 110, an outer shroud 120, an inner shroud 130, and an air passage 140.

[0071] The cross section of the blade body 110 is blade-shaped and extends along the radial direction Dr. In other words, the blade height direction of the blade body 110 is the radial direction Dr. The blade body 110 is arranged in the combustion gas flow path 49 for the combustion gas G to pass through. On the surface of the blade body 110, the convex surface of the surface facing the circumferential direction Dc forms the dorsal side (negative pressure surface), and the concave surface forms the ventral side (positive pressure surface). A plurality of exhaust holes 110h are formed at the end of the upstream side Dau of the axis and the end of the downstream side Dad of the axis in the blade body 110.

[0072] The outer shroud 120 is provided at the end of the radially outer side Dro of the blade body 110, and defines the outer peripheral side position of the combustion gas flow path 49 which is an annular space. The outer shroud 120 includes a shroud body 121, a peripheral wall 122, a retainer 124, and a collision plate 123.

[0073] The shield body 121 is formed in a plate shape extending in the axial direction Da and the circumferential direction Dc. The shield body 121 has a gas passage surface 121a and an outer inner surface 121b. The gas passage surface 121a is a surface in contact with the combustion gas G (a surface facing the combustion gas flow path 49) and faces the radial inner side Dri. The outer inner surface 121b is a surface facing the opposite side of the gas passage surface 121a.

[0074] The peripheral wall 122 protrudes from the shield body 121 to the radially outer side Dro along the outer peripheral edge of the shield body 121. The peripheral wall 122 in the present embodiment is formed over the entire circumference of the outer peripheral edge of the shield body 121. The peripheral wall 122 has: a front wall portion 122a having a front wall facing the axial downstream side Dad; a rear wall portion 122b having a rear wall facing the axial upstream side Dau; a dorsal wall portion 122c having a dorsal wall facing the circumferential direction Dcp; and a ventral wall portion (not shown) having a ventral wall facing the circumferential direction Dcn. Therefore, the outer shield 120 has a space surrounded by the peripheral wall 122 from four directions, namely, a first space S1.

[0075] The retainer 124 is arranged on the radially outer side Dro of the front wall portion 122a in the peripheral wall 122. The retainer 124 extends from the front wall portion 122a to the radially outer side Dro integrally with the front wall portion 122a. The end of the radially outer side Dro of the retainer 124 is fixed to, for example, the deflector fixing portion 75 of the blade ring body 7. The retainer 124 has a front surface 124a facing the axial upstream side Dau.

[0076] The collision plate 123 is arranged in the first space S1 of the outer shroud 120, and divides the first space S1 into a region on the radially outer side Dro and a region on the radially inner side Dri, that is, a chamber CA. The collision plate 123 is formed with a plurality of air holes 123h that penetrate in the radial direction Dr. A portion of the cooling air Ac existing on the radially outer side Dro of the stationary blade 46a1 flows into the chamber CA through the plurality of air holes 123h formed in the collision plate 123. A portion of the air flowing into the chamber CA cools the outer shroud 120, and then is exhausted to the combustion gas flow path 49 from, for example, an exhaust hole (not shown) provided in the outer shroud 120.

[0077] The inner shroud 130 is provided at the end portion of the radially inner side Dri of the blade body 110 and defines the inner peripheral position of the combustion gas flow path 49 which is an annular space. The inner shroud 130 includes a shroud body 131 , a peripheral wall 132 , and a collision plate 133 .

[0078] The shield body 131 is formed in a plate shape extending in the axial direction Da and the circumferential direction Dc. The shield body 131 has a gas passage surface 131a and an inner inner surface 131b. The gas passage surface 131a is a surface in contact with the combustion gas G (a surface facing the combustion gas flow path 49) and faces the radial outer side Dro. The inner inner surface 131b is a surface facing the opposite side of the gas passage surface 131a. The shield body 131 has an exhaust hole 131h that connects the second space S2 described later with the combustion gas flow path 49.

[0079] The peripheral wall 132 protrudes from the shield body 131 to the radial inner side Dri along the outer peripheral edge of the shield body 131. The peripheral wall 132 in the present embodiment is formed over the entire circumference of the outer peripheral edge of the shield body 131. The peripheral wall 132 has: a front wall portion 133a having a front wall facing the axial downstream side Dad; a rear wall portion 133b having a rear wall facing the axial upstream side Dau; a dorsal wall portion 133c having a dorsal wall facing the circumferential direction Dcp; and a ventral wall portion (not shown) having a ventral wall facing the circumferential direction Dcn. The inner shield 130 has a second space S2, which is a space surrounded by the peripheral wall 132 from four directions.

[0080] The collision plate 133 is disposed in the second space S2 of the inner shield 130, and divides the second space S2 into a region on the radial inner side Dri and a region on the radial outer side Dro, namely, a chamber CA. The collision plate 133 is formed with a plurality of air holes 133h penetrating in the radial direction Dr. It should be noted that the collision plate 133 may also be omitted.

[0081] A plurality of air passages 140 extend from the outer shroud 120 through the blade body 110 to the inner shroud 130. A portion of the adjacent air passages 140 in the plurality of air passages 140 may also be connected to each other at the radially outer side Dro portion or the radially inner side Dri portion. Any of the plurality of air passages 140 is connected to the first space S1 of the outer shroud 120. Any of the plurality of air passages 140 is connected to the second space S2 of the inner shroud 130. The air passage 140 is connected to the plurality of exhaust holes 110h of the blade body 110.

[0082] A portion of the cooling air Ac flowing into the inner peripheral side of the turbine blade ring 70 through the air intake port 72 of the turbine blade ring 70 flows into the air hole 123h of the collision plate 123 of the outer shroud 120, flows in the chamber CA of the outer shroud 120, and cools the outer shroud 120. Another portion of the cooling air Ac flowing into the inner peripheral side of the turbine blade ring 70 flows into the air passage 140, and cools the blade body 110 while passing through the air passage 140. A portion of the cooling air Ac flowing in the air passage 140 is discharged from a plurality of exhaust holes 110h provided in the blade body 110 to the combustion gas flow path 49. Another portion of the cooling air Ac flowing in the air passage 140 flows into the second space S2 of the inner shroud 130, and cools the inner shroud 130. The cooling air Ac flowing in the second space S2 of the inner shroud 130 is discharged from the exhaust holes 131h of the inner shroud 130 to the combustion gas flow path 49.

[0083] (Deflector)

[0084] Next, the deflector 90 will be described.

[0085] like Figure 3 As shown, a plurality of deflectors 90 are arranged on the outer peripheral side of at least a portion of the turbine blade ring 70. The plurality of deflectors 90 are arranged separately in the circumferential direction Dc and are located at positions corresponding to the plurality of air intake ports 72. The deflectors 90 and the turbine blade ring 70 are formed of a material of the same composition (e.g., stainless steel) and have the same thermal expansion coefficient. The "same composition" mentioned here means, for example, that the material used in manufacturing the turbine blade ring 70 and the material used in manufacturing the deflector 90 are the same material.

[0086] Figure 6 1 is a top view of the deflector 90 when the deflector 90 is viewed from the radially outer side Dro. Figure 7 This is a front view of the deflector 90 when the deflector 90 is viewed from the upstream side Dau of the axis. Figure 6 As shown, the deflector 90 is configured to shield at least a portion of the air intake port 72 when viewed from the radially outer side Dro. Figures 3 to 7 As shown, the deflector 90 has a fixing platform portion 91 and a plate portion 92 .

[0087] (Fixed table)

[0088] The fixing platform 91 is arranged between two protrusions 73 (the first protrusion 73a and the second protrusion 73b) adjacent to each other in the circumferential direction Dc, and is mounted on the turbine blade ring 70. The fixing platform 91 in this embodiment can be fixed to the deflector fixing portion 75 of the blade ring body 7 in a detachable manner. The fixing platform 91 has a first portion 91a that abuts against the fixing surface 75a of the deflector fixing portion 75 from the axial upstream side Dau and a second portion 91b that abuts against the support surface 75b of the deflector fixing portion 75 from the radially outer side Dro. The first portion 91a and the second portion 91b are each in the shape of a plate having a predetermined thickness, and are integrated in a state where the ends are connected to each other. The fixing platform 91 is L-shaped when viewed from the circumferential direction Dc.

[0089] The first portion 91a of the fixing platform 91 is formed with an insertion hole 93h through which the coupling piece 93 is inserted. The coupling piece 93 inserted through the insertion hole 93h of the first portion 91a is coupled to the coupling hole 75h of the deflector fixing portion 75, so that the first portion 91a and the second portion 91b integral with the first portion 91a are fixed to the deflector fixing portion 75. In other words, the fixing platform 91 can be attached to and detached from the deflector fixing portion 75 by the coupling piece 93.

[0090] In addition, the first portion 91a is provided with a coupling hole 91h through which a coupling member 95 such as a bolt passes. The first portion 91a including the coupling hole 91h is an example of a "fixing portion" capable of fixing the sealing member 85. In the present embodiment, the first portion 91a has the coupling hole 91h for mounting the sealing member 85. Therefore, the first portion 91a including the coupling hole 91h for fixing the deflector 90 to the turbine blade ring 70 is arranged between the two protrusions 73 in the circumferential direction Dc.

[0091] In addition, a coupling hole 94h is provided on the surface of the second portion 91b facing the radially outer side Dro, through which a coupling member 94 such as a bolt can be coupled. A plurality of (eg, two) coupling holes 94h are arranged on the end surface of the second portion 91b facing the radially outer side Dro.

[0092] (Board)

[0093] The plate portion 92 is mounted on the fixed platform portion 91. The plate portion 92 is mounted on the end of the radially outer side Dro in the fixed platform portion 91 and is supported by the fixed platform portion 91. The plate portion 92 is, for example, in the shape of a plate along a direction intersecting (for example, orthogonal to) the radial direction Dr. The plate portion 92, for example, has a main surface 92a extending in a direction intersecting (for example, orthogonal to) the radial direction Dr. In the present embodiment, the plate portion 92 has a pair of main surfaces 92a that are located toward the radially outer side Dro and the radially inner side Dri when mounted on the fixed platform portion 91. The main surface 92a facing the radially inner side Dri of the pair of main surfaces 92a of the plate portion 92 abuts against the surface of the second portion 91b of the fixed platform portion 91 that faces the radially outer side Dro.

[0094] The plate portion 92 is formed with an insertion hole 92h through which the coupling member 94 is inserted. The insertion hole 92h penetrates through a pair of main surfaces 92a in the plate thickness direction of the plate portion 92. The coupling member 94 inserted through the insertion hole 92h of the plate portion 92 is coupled to the coupling hole 94h of the second portion 91b, thereby fixing the plate portion 92 to the second portion 91b of the fixing platform portion 91. In other words, the plate portion 92 can be attached and detached relative to the fixing platform portion 91 by the coupling member 94. Therefore, the fixing platform portion 91 can be removed from the turbine blade ring 70 in a state where the plate portion 92 and the fixing platform portion 91 are integrated.

[0095] like Figure 6As shown, when viewed from the radially outer side Dro, the plate portion 92 is configured to overlap at least a portion of each of the two protrusions 73 (the first protrusion 73a and the second protrusion 73b) adjacent to each other in the circumferential direction Dc. In addition, when viewed from the radially outer side Dro, the plate portion 92 is configured to be separated from the upstream surface 7s of the blade ring body 7 by a gap (gap). Hereinafter, the gap separated between the plate portion 92 and the upstream surface 7s of the blade ring body 7 when viewed from the radially outer side Dro is referred to as the "gap G1". Here, the plate portion 92 has an end portion on the downstream side Dad of the axis, i.e., a first end portion 92e1, a first direction ( Figure 6 and Figure 7 The first end 92e1 is configured to have a gap G1 between it and the upstream surface 7s of the turbine blade ring 70. The first end 92e1 and the third end 92e3 extend in the first direction. The second end 92e2 extends in the axial direction Da.

[0096] In addition, if Figure 7 As shown, the plate portion 92 is arranged with a gap (gap) between the two protrusions 73 in the radial direction Dr. Hereinafter, the gap between the plate portion 92 on the radially outer side Dro and the two protrusions 73 is referred to as "gap G2". That is, the second end portion 92e2 is arranged with a gap G2 between the two protrusions 73. Furthermore, when viewed from the radial direction, the width L1 of the plate portion 92 in the first direction adjacent to the two protrusions 73 is larger than the width L2 of the narrow portion 72a of the air intake port 72 in the first direction. It should be noted that the width L1 of the plate portion 92 is the separation distance between the pair of second end portions 92e2 in the first direction.

[0097] In addition, if Figure 6 As shown in FIG. 1 , the ratio of the deflector 90 to block the air intake port 72 when viewed from the radially outer side Dro is as follows: Figure 7 As shown, the deflector 90 blocks the air inlet 72 at a higher ratio when viewed from the axial upstream side Dau. In other words, the fixed platform 91 and the plate 92 block the air inlet 72 in the radial direction Dr when viewed from the radially outer side Dro than the fixed platform 91 and the plate 92 block the air inlet 72 in the axial direction Da when viewed from the axially upstream side Dau.

[0098] In addition, if Figure 5As shown, the third end 92e3 of the plate portion 92 is located closer to the axis downstream side Dad than the front surface 124a of the retainer 124 included in the stationary blade 46a1. In addition, the third end 92e3 is located closer to the axis downstream side Dad than the surface of the fixed platform portion 91 facing the axis upstream side Dau. In addition, the third end 92e3 is located closer to the axis downstream side Dad than the end surface 73u of the protrusion 73 facing the axis upstream side Dau.

[0099] In addition, if Figure 3 As shown, the deflector 90 is disposed on the inner peripheral side of the cooling medium flow portion 100. In addition, the plate portion 92 is located between the cooling medium flow portion 100 and the air intake port 72 in the radial direction Dr.

[0100] (Sealing member)

[0101] like Figures 3 to 7 As shown in FIG. 1 , the sealing member 85 is disposed between the tail pipes 32 of two combustors 30 adjacent to each other in the circumferential direction Dc, and the gap between the tail pipes 32 of the two combustors 30 is sealed airtightly. The sealing member 85 is, for example, a spring seal. The sealing member 85 is disposed on the inner circumference side of the turbine blade ring 70 (see FIG. 1 ). Figure 5 The sealing member 85 is arranged at a position overlapping with the air intake port 72 in the radial direction Dr (see Figure 5 and Figure 6 The sealing member 85 can be removed toward the outer peripheral side of the turbine blade ring 70 through the air intake port 72 in a state where the tail cylinder 32 of the combustor 30 is removed from the combustor connecting member 80 .

[0102] The sealing member 85 is provided with an insertion hole 95h through which the coupling piece 95 is inserted. The coupling piece 95 inserted through the insertion hole 95h of the sealing member 85 is coupled to the coupling hole 91h of the first portion 91a of the fixing platform 91, so that the sealing member 85 is fixed to the first portion 91a. In other words, the sealing member 85 can be attached and detached relative to the fixing platform 91 by the coupling piece 95.

[0103] (mask)

[0104] Figure 8: is a cross-sectional view showing the shield cover 150. The shield cover 150 is mounted on the inner shroud 130 and fixed to the inner shroud 130 by welding or the like. The shield cover 150 covers at least a portion of the second space S2 of the inner shroud 130 from the radial inner side Dri. The shield cover 150 in the present embodiment is mounted on the peripheral wall 132 of the inner shroud 130 and covers the entire second space S2 of the inner shroud 130. By mounting the shield cover 150 on the inner shroud 130, the compressed air Ac is not supplied from the radial inner side Dri to the second space S2 of the inner shroud 130. The compressed air Ac that flows in from the air inlet 72 of the turbine blade ring 70 and flows in the air passage 140 of the outer shroud 120 and the blade body 110 is supplied to the second space S2 of the inner shroud 130.

[0105] (Function / Effect)

[0106] Next, the functions and effects achieved by the configuration of this embodiment will be described.

[0107] like Figure 2 As shown, the compressed air Ac compressed by the compressor 20 is supplied from the compressor 20 to the accommodation chamber R in which the burner 30 is arranged. A part of the compressed air Ac supplied to the accommodation chamber R changes the flow direction angle through the guide portion 64 and flows toward the peripheral wall 62 of the gas turbine chamber 15. And, the compressed air Ac that collides with the peripheral wall 62 (first peripheral wall 62a) is divided into two paths, for example. That is, a part (for example, most of) of the compressed air Ac changes the flow direction so as to flow toward the intake portion 31 of the burner 30, and then flows toward the intake portion 31 of the burner 30 (see Figure 2 On the other hand, another part of the compressed air Ac changes its flow direction in a manner of flowing from the peripheral wall 62 along the rear wall 63 after colliding with the peripheral wall 62 of the gas turbine chamber 15 (see arrow A1 in FIG. 1 ). Figure 2 As a result, inside the accommodation chamber R, a flow of compressed air Ac from the radially outer side Dro toward the radially inner side Dri is generated in the space located radially outward Dro relative to the turbine blade ring 70 (see Figure 2 Middle and Fig. 9 In addition, a part of the flow of the compressed air Ac is taken into the inner peripheral side of the turbine blade ring 70 from the air intake port 72 of the turbine blade ring 70 .

[0108] In addition, if Figure 2 and Figure 4 As shown, a part of the compressed air Ac supplied to the storage chamber R changes the flow direction angle by the guide portion 64, and generates a flow of compressed air directly from the axial upstream side Dau toward the air intake port 72 (see Figure 2 Middle and Figure 4At the same time, the compressed air collides with the sealing member 85 that seals the gap between the two tail pipes 32 of the combustor 30 in an airtight manner, and a flow of the compressed air Ac from the radial inner side Dri to the radial outer side Dro is generated along the sealing member 85 (refer to Figure 2 Middle and Figure 4 arrow A4 in the figure).

[0109] Fig. 9 It is a cross-sectional view showing the function of the deflector 90 .

[0110] In the present embodiment, the deflector 90 is attached to the turbine blade ring 70. The deflector 90 includes a plate portion 92 arranged so as to shield at least a portion of the air intake port 72 when viewed in the radial direction Dr. Therefore, most of the compressed air Ac flowing along the rear wall 63 of the gas turbine casing 15 does not directly flow into the air intake port 72, but collides with the plate portion 92 of the deflector 90 and rebounds (see Fig. 9 In this process, foreign matter M (such as rust and garbage) contained in the compressed air Ac flows toward the axial upstream side Dau in a manner separated from the air intake port 72. Therefore, it is difficult for foreign matter M contained in the compressed air Ac to enter the air intake port 72 from the radially outer side Dro. As a result, the foreign matter M is prevented from clogging the cooling structure of the stationary blade 46a1 (for example, the exhaust hole 110h of the blade body 110 and the exhaust hole 131h of the inner shroud 130).

[0111] The foreign matter M that is rebounded by the compressed air Ac and flows toward the axial upstream side Dau in a manner separated from the air intake port 72 is taken into the combustor 30 from, for example, the air intake portion 31 of the combustor 30, is included in the combustion gas G, and is discharged to the outside of the gas turbine 10. The combustion gas flow path 49 has fewer or no small holes clogged with foreign matter than the stator 46a1, so that the inconvenience caused by the foreign matter M is less likely to occur.

[0112] Furthermore, according to the structure described in this embodiment, the above-mentioned effects can be achieved with a simple structure such as the plate portion 92. Therefore, for example, an increase in the manufacturing cost of the deflector 90 can be suppressed.

[0113] In addition, if Figure 7 As shown, when viewed from the radial direction Dr, the width L1 of the plate portion 92 in the first direction where the two protrusions 73 are adjacent is larger than the width L2 of the narrow portion 72a of the cooling medium inlet 72 in the first direction. Therefore, for example, compared with a case where the width L1 of the plate portion 92 is the same as or smaller than the width L2 of the narrow portion 72a, it is difficult for the compressed air Ac to flow into the inner peripheral side of the turbine impeller 70 from the radially outer side Dro through the air inlet 72.

[0114] In addition, if Figure 6 As shown, when viewed from the radially outer side Dro, the first end portion 92e1 of the plate portion 92 is arranged with a gap G1 between it and the upstream surface 7s of the blade ring body 7. Figure 7 As shown, the pair of second end portions 92e2 of the plate portion 92 are arranged with a gap G2 between the two protrusions 73 when viewed from the axial upstream side Dau. Therefore, even if tolerances occur in dimensions such as length, width, and thickness during the manufacturing process of the plate portion 92, the presence of the gaps G1 and G2 can suppress interference of the plate portion 92 with the turbine blade ring 70. As a result, for example, the number of man-hours required for assembling the blade ring assembly WS can be reduced.

[0115] In addition, if Figure 5 As shown in FIG. 1 , the third end portion 92e3 of the plate portion 92 is located at a position closer to the axial downstream side Dad than the front surface 124a of the retainer 124 included in the stationary blade 46a1. Therefore, for example, compared with the case where the third end portion 92e3 is located at the same position as the front surface 124a of the retainer 124 in the axial direction Da, or is located closer to the axial upstream side Dau than the front surface 124a, the compressed air Ac (see FIG. 1 ) flowing from the axial upstream side Dau is Figure 2 middle, Figure 4 Middle and Fig. 9 The foreign matter M contained in the arrow A3 in the figure is unlikely to collide with the main surface 92a of the plate portion 92 facing the radial inner side Dri and bounce back. As a result, the foreign matter M is unlikely to be taken into the air intake port 72. In addition, the compressed air Ac (refer to Figure 2 middle, Figure 4 Middle and Fig. 9 The foreign matter M included in the arrow A4 in FIG. 1 is unlikely to collide with and bounce off the main surface 92 a of the plate portion 92 that faces the radially inner side Dri. As a result, the foreign matter M is unlikely to be taken into the air intake port 72.

[0116] In addition, according to the structure described in this embodiment, the fixed platform 91 of the deflector 90 is arranged between the two protrusions 73 in the circumferential direction Dc and is attached to the turbine blade ring 70, and the plate portion 92 is attached to the outer end of the radial direction Dr in the fixed platform 91. As a result, the fixed platform 91 in the cooling medium intake port can support the plate portion 92 from the radial inner side Dri. Therefore, when the compressed air Ac collides with the plate portion 92 from the radial outer side Dro, it is possible to suppress the displacement of the plate portion 92 to the radial inner side Dri.

[0117] In addition, according to the structure described in the present embodiment, the third end 92e3 of the plate portion 92 is located at a position closer to the axial downstream side Dad than the surface of the fixed platform portion 91 facing the axial upstream side Dau. Therefore, compared with the case where the third end 92e3 is located at the same position as the surface of the fixed platform portion 91 facing the axial upstream side Dau in the axial direction Da or is located closer to the axial upstream side Dau than the surface, the foreign matter M contained in the compressed air Ac flowing from the radially outer side Dro of the fixed platform portion 91 is less likely to collide with the main surface 92a of the plate portion 92 facing the radially inner side Dri and rebound. As a result, the foreign matter M is less likely to be taken into the air intake port 72.

[0118] In addition, according to the structure described in this embodiment, the fixing platform 91 can be removed from the turbine blade ring 70 in a state where the plate portion 92 and the fixing platform 91 are integrated. Therefore, for example, even if a forced cooling component such as the cooling medium flow portion 100 exists as an interfering object at a position closer to the radial outer side Dro than the plate portion 92, the fixing platform 91 can be removed toward the axial upstream side Dau in a state where it is integrated with the plate portion 92. As a result, for example, compared with a case where the fixing platform 91 and the plate portion 92 are not integrated, it is easier to perform maintenance such as repair on these fixing platforms 91 and the plate portion 92.

[0119] In addition, according to the structure described in the present embodiment, the fixing platform 91 has a first portion 91a to which the sealing member 85 is fixed, and the sealing member 85 airtightly closes the gap between the two tail pipes 32 of the combustor 30 adjacent in the circumferential direction Dc. In other words, the fixing platform 91 is a member that supports the plate portion 92 from the radial inner side Dri, and also serves as a member for fixing the sealing member 85. Therefore, it is not necessary to provide a member other than the fixing platform 91 in order to fix the sealing member 85. As a result, it is possible to suppress an increase in the number of components of the turbine blade ring 70.

[0120] In addition, according to the structure described in the present embodiment, each of the plurality of protrusions 73 has an end surface 73u including a coupling hole 73h that can be connected to the combustor connecting member 80 to which the tail cylinder 32 of the combustor 30 is fixed. Therefore, by using the protrusions 73, the length of the plate portion 92 in the axial direction Da can be made relatively long. Therefore, foreign matter M contained in the compressed air Ac flowing toward the deflector 90 from the radially outer side Dro is suppressed from flowing into the air intake 72.

[0121] In addition, according to the structure described in this embodiment, the turbine blade ring 70 and the inducer 90 are formed of the same material, so that, for example, the influence of thermal expansion of the turbine blade ring 70 acting between the turbine blade ring 70 and the inducer 90 can be suppressed to be small. Therefore, for example, it is possible to suppress the occurrence of a malfunction between the turbine blade ring 70 and the first portion 91a of the fixing platform 91. As a result, the life of the blade ring assembly WS can be extended.

[0122] In addition, if Figure 6 and Figure 7 As shown, the ratio of the deflector 90 observed from the radial outer side Dro to block the air inlet 72 in the radial direction Dr is higher than the ratio of the deflector 90 observed from the axial upstream side Dau to block the air inlet 72. Therefore, the amount of cooling air Ac taken into the air inlet 72 from the axial upstream side Dau is greater than the amount of compressed air Ac taken into the air inlet 72 from the radial outer side Dro. The inventors analyzed the size of the foreign matter M contained in the compressed air Ac in the containment chamber R. As a result, it was found that the size of the foreign matter M contained in the compressed air Ac flowing around the deflector 90 from the radial outer side Dro toward the deflector 90 is larger than the foreign matter M contained in the compressed air Ac flowing from the axial upstream side Dau toward the deflector 90. Therefore, through the above-mentioned structure, while preventing foreign matter M contained in the compressed air Ac flowing from the radial outer side Dro from being taken into the air inlet 72, by allowing cooling air Ac to be taken into the air inlet 72 from the axial upstream side Dau, it is possible to prevent foreign matter M from clogging the cooling structure of the stator 46a1.

[0123] In addition, if Figure 6 and Figure 7As shown, when viewed from the radially outer side Dro, the plate portion 92 is arranged so as to overlap at least a portion of each of the two protrusions 73 adjacent to each other in the circumferential direction Dc and to be spaced apart from the two protrusions 73 in the radial direction Dr by a gap G2. A portion of the compressed air Ac flowing from the radially outer side Dro toward the plate portion 92 collides with the main surface 92a of the plate portion 92 toward the radially outer side Dro, and after flowing along the circumferential direction Dc, turns at an angle exceeding 90° (e.g., about 180°) and flows into the air intake port 72 from the above-mentioned gap G2 spaced apart in the radial direction Dr. In this process, the foreign matter M contained in the compressed air Ac cannot turn due to the inertial force of the foreign matter M, and is hardly taken into the air intake port 72. In other words, it is possible to suppress the foreign matter M flying from the radially outer side Dro from being taken into the air intake port 72, and a part of the compressed air Ac from which the foreign matter M is separated by the plate portion 92 can be taken into the air intake port 72 from the gap G2 between the plate portion 92 and the protrusion 73. Therefore, compared with the case where the plate portion 92 abuts against the protrusion 73 without separating the gap G2 in the radial direction Dr, for example, the amount of the compressed air Ac from which the foreign matter M is separated and taken into the air intake port 72 can be increased.

[0124] <Second embodiment>

[0125] Below, refer to Figures 10 to 12 A bale ring assembly according to a second embodiment of the present disclosure will be described. It should be noted that in the following description, components having the same or similar functions as those of the first embodiment are denoted by the same reference numerals and their descriptions are omitted.

[0126] Fig.10 This is a perspective view showing a portion of the leaf ring assembly WS in an exploded manner. Fig.11 97 is a top view when the deflector 97 is viewed from the radially outer side Dro. In the present embodiment, a cooling hole 76 formed in the radial direction Dr is formed in the deflector fixing portion 75. The cooling hole 76 penetrates the deflector fixing portion 75, and one end of the cooling hole 76 on the radially outer side Dro opens at the support surface 75b adjacent to the upstream surface 7s of the blade ring body 7, and the other end on the radially inner side Dri opens at the first space S1 of the outer shroud 120. In the present embodiment, three cooling holes 76 are formed in one deflector fixing portion 75 separated from each other in the circumferential direction Dc, but the number of cooling holes 76 is not limited to three, and can be appropriately selected according to the cooling performance required of the blade ring assembly WS.

[0127] The deflector 97 of this embodiment has a fixed platform 98 and a plate portion 99. The fixed platform 98 is fixed to the deflector fixing portion 75 by a coupling 93 in a detachable manner, and has a first portion 98a that abuts against the fixing surface 75a of the deflector fixing portion 75 from the axial upstream side Dau and a pair of second portions 98b and 98c provided on the upper surface of the radial outer side Dro of the first portion 98a. The first portion 98a and the second portions 98b and 98c are a single component formed integrally. The second portions 98b and 98c are separated in the circumferential direction Dc and do not hinder the flow of the cooling medium therebetween. The fixed platform 98 is L-shaped when viewed from the circumferential direction Dc, but unlike the fixed platform 91 of the first embodiment described above, the second portions 98b and 98c do not abut against the support surface 75b of the deflector fixing portion 75. By providing the second parts 98b and 98c on the upper surface of the radially outer side Dro of the first part 98a, a groove 98d having the upper surface of the first part 98a as the bottom is formed between the second part 98b on one side and the second part 98c on the other side. The groove 98d is formed along the axial direction Da and is coplanarly continuous with the support surface 75b of the deflector fixing part 75. The groove 98d and the support surface 75b define a cooling medium intake passage 97a between the plate part 99 fixed to the second parts 98b and 98c.

[0128] like Fig.11 As shown, the plate portion 99 is in the shape of a plate extending in a direction intersecting the radial direction Dr, and has two main surfaces 99a facing the radial outer side Dro and the radial inner side Dri. The main surface 99a facing the radial inner side Dri abuts against the surface of the second part 98b, 98c of the fixed platform 98 facing the radial outer side Dro. Insertion holes for passing two coupling members 94 are formed separately in the plate portion 99 along the circumferential direction Dc. On the other hand, two coupling holes corresponding to the insertion holes of the plate portion 99 are formed on the surface of the second part 98b, 98c facing the radial outer side Dro. The coupling member 94 passing through the insertion hole of the plate portion 99 is coupled to the coupling hole of the second part 98b, 98c, whereby the plate portion 99 is fixed to the second part 98b, 98c of the fixed platform 98 in a manner that allows loading and unloading.

[0129] The plate portion 99 has a first end portion 99c which is an end portion on the downstream side Dad of the axis, two second end portions 99d and 99e which are both ends of the plate portion 99 in the longitudinal direction, a third end portion 99f which is an end portion on the upstream side Dau of the axis, and a rectangular extension portion 99g which extends from the third end portion 99f to the upstream side Dau of the axis. When viewed from the radially outer side Dro, the first end portion 99c is arranged so as to be separated from the upstream surface 7s of the blade ring body 7 by a gap G1. The first end portion 99c and the third end portion 99f extend in the first direction similarly to the plate portion 92 of the first embodiment. The second end portions 99d and 99e both extend in the axial direction Da, and the two are parallel. The leading edge 99h of the extension portion 99g is parallel to the first end portion 99c, and the distance between the two side edges 99i and 99j of the extension portion 99g separated in the first direction is substantially equal to the length of the fixing platform portion 98 in the circumferential direction Dc.

[0130] The second end 99d of the plate portion 99 extends in the circumferential direction Dcn, and the second end 99e extends in the circumferential direction Dcp. The plate portion 99 is configured such that, when viewed from the radially outer side Dro, the second end 99d overlaps with the first protrusion 73a of the two protrusions adjacent in the circumferential direction Dc, and the second end 99e overlaps with the second protrusion 73b. In addition, the second end portions 99d and 99e are configured with gaps between the protrusions 73a and 73b in the radial direction Dr.

[0131] When the extension 99g is viewed from the radially outer side Dro, the front edge 99h of the extension 99g coincides with the surface of the axial upstream side Dau of the first portion 98a of the fixed platform 98, and the two side edges 99i and 99j of the extension 99g coincide with the two side surfaces separated in the circumferential direction Dc of the fixed platform 98. Thus, the extension 99g is arranged so as to overlap with the groove 98d of the fixed platform 98, so that when viewed from the radially outer side Dro, the groove 98d is blocked by the extension 99g.

[0132] Fig.12: is a cross-sectional view showing the function of the guide 97. Compressed air Ac (A3) as a cooling medium that flows from the axial upstream side Dau by changing the flow direction angle by the guide portion (the guide vane of the compressor) flows into the intake passage 97a of the guide 97. The compressed air Ac that has flowed into the intake passage 97a flows toward the axial downstream side Dad along the groove 98d and the support surface 75b between the second portions 98b and 98c, and collides with the upstream surface 7s of the blade ring body 7. A portion of the compressed air Ac that has collided with the upstream surface 7s changes direction toward the radial inner side Dri, and flows into the first space S1 of the outer shroud 120 through the cooling hole 76. The cooling air Ac that flows into the inner peripheral side of the turbine blade ring 70 through the cooling hole 76 cools the blade body 110, the outer shroud 120, and the inner shroud 130 in the same manner as in the above-mentioned first embodiment. In this embodiment, the fixing platform 98 of the deflector 97 is provided with a cooling medium intake passage 97a, so that the amount of compressed air Ac flowing into the outer shroud 120 and the inner shroud 130 can be increased compared with the deflector 90 of the first embodiment. This can enhance the effect of the cooling structure of the stationary vane 46a1.

[0133] Unlike the compressed air Ac (A3), the compressed air Ac (A2) flowing along the rear wall 63 of the gas turbine chamber 15 does not flow into the air intake port 72, but collides with the plate portion 99 of the deflector 97. At this time, the foreign matter M contained in the compressed air Ac hits the plate portion 99 and rebounds, and flows toward the axial upstream side Dau in a manner separated from the air intake port 72. In the present embodiment, the plate portion 99 of the deflector 97 is formed with a protruding portion 99g that protrudes toward the axial upstream side Dau and blocks the groove 98d, so that the foreign matter M hits the plate portion 99 and rebounds, and does not contact the groove 98d of the fixed platform portion 98. In other words, even if the fixed platform portion 98 of the deflector 97 is formed with the groove 98d constituting a part of the intake passage 97a for compressed air, the protruding portion 99g can prevent the foreign matter M from flowing from the intake passage 97a to the outer shroud 120 and the inner shroud 130. As a result, the foreign matter M is suppressed from clogging the cooling structure of the vane 46a1.

[0134] (Other Implementations)

[0135] Although the embodiments of the present disclosure have been described in detail above with reference to the drawings, the specific structure is not limited to the structure of the embodiments, and addition, omission, replacement, and other changes in structure are possible within the scope not departing from the gist of the present disclosure.

[0136] It should be noted that if Fig.13As shown, the plate portion 92' of the deflector 90 may be formed integrally with the fixing platform portion 91'. In this case, a through hole 91c is formed in the fixing platform portion 91' for passing a fastener 96 such as a bolt. A plurality of (for example, two) through holes 91c are formed in the fixing platform portion 91'. The fixing platform portion 91' is fixed to the blade ring body 7 by being coupled to the coupling hole 7a pre-formed in the blade ring body 7, with the fastener 96 passing through the through hole 91c. Thus, there is no need to separately install the fixing platform portion 91' and the plate portion 92', so that, for example, the operation of mounting the deflector 90 on the turbine blade ring 70 becomes easy.

[0137] In addition, the plate portion 92 described in the above embodiment is not limited to the above arrangement, and may be arranged in the air intake port 72 , for example.

[0138] <Note>

[0139] The blade ring assembly described in the embodiment and the gas turbine including the blade ring assembly are understood as follows, for example.

[0140] (1) A first embodiment of the bale assembly WS includes: a turbine bale 70 extending in a circumferential direction Dc with the axis Ar as the center; a stationary blade 46a arranged on the inner circumference side of the turbine bale 70; and an inducer 90, 97 arranged on the outer circumference side of at least a portion of the turbine bale 70, wherein the turbine bale 70 includes: a bale body 7; and a plurality of protrusions 73 protruding from the bale body 7 on the axial upstream side Dau of both sides in an axial direction Da extending toward the axis Ar, and arranged at different positions in the circumferential direction Dc at intervals from each other, wherein two protrusions 73 included in the plurality of protrusions 73 adjacent to each other in the circumferential direction Dc form a cooling medium inlet (air inlet 72) leading from the outer circumference side of the turbine bale 70 to the inner circumference side, and when viewed in a radial direction Dr with the axis Ar as the center, the inducers 90, 97 are arranged so as to shield at least a portion of the cooling medium inlet.

[0141] As a result, most of the compressed air Ac flowing from the outer side in the radial direction Dr to the blade ring assembly WS in the gas turbine casing 15 does not flow directly into the cooling medium inlet, but collides with the inducers 90, 97 and rebounds. In this process, foreign matter M (such as rust and garbage) contained in the compressed air Ac flows toward the axial upstream side Dau in a manner separated from the cooling medium inlet. Therefore, it is difficult for foreign matter M contained in the compressed air Ac to enter the cooling medium inlet from the outer side in the radial direction Dr.

[0142] (2) The second embodiment of the bling assembly WS is based on the first embodiment of the bling assembly WS. In addition, the deflector 90 , 97 may include a plate portion 92 , 92 ′, 99 having a main surface 92 a , 99 a extending in a direction intersecting the radial direction Dr.

[0143] Thus, the above-mentioned effect (1) can be achieved by a simple structure such as the plate parts 92 , 92 ′, and 99 .

[0144] (3) The third embodiment of the blade ring assembly WS is based on the second embodiment of the blade ring assembly WS, wherein the cooling medium inlet has a minimum portion (narrow portion 72a) where the cooling medium inlet is narrowest between the ends of the inner circumferential side of the two protrusions 73, and a width L1 of the plate portions 92, 92' in the first direction adjacent to the two protrusions 73 is larger than a width L2 of the minimum portion of the cooling medium inlet in the first direction.

[0145] Therefore, compared with the case where the width L1 of the plate portions 92, 92' is the same as or smaller than the width L2 of the initial portion of the cooling medium inlet, it is difficult for the compressed air Ac to flow from the outer side in the radial direction Dr through the cooling medium inlet to the inner peripheral side of the turbine impeller 70.

[0146] (4) The fourth embodiment of the blade ring assembly WS is based on the blade ring assembly WS of the second or third embodiment. In this embodiment, the plate portion 92, 92' has an end portion on the downstream side Dad of the axis on both sides in the axial direction Da, i.e., a first end portion 92e1, and two ends in the first direction adjacent to the two protrusions 73, i.e., a pair of second end portions 92e2, and the first end portion 92e1 and the pair of second end portions 92e2 are arranged with gaps G1 and G2 between them and the turbine blade ring 70.

[0147] Thus, due to the presence of the gaps G1 and G2, even if tolerances occur in the length, width, thickness and other dimensions of the plate portions 92 and 92' during the manufacturing process, interference of the plate portions 92 and 92' with the turbine blade ring 70 can be suppressed. As a result, for example, the number of man-hours required for assembling the blade ring assembly WS can be reduced.

[0148] (5) The blade ring assembly WS of the fifth scheme is based on the blade ring assembly WS of any one of the second to fourth schemes, and it is possible that the plate portion 92, 92' has a third end portion 92e3 as an end portion of the axial upstream side Dau, and the third end portion 92e3 is located on the axial downstream side Dad on both sides in the axial direction Da compared to the surface (front surface 124a) of the retaining member 124 included in the stationary blade 46a facing the axial upstream side Dau.

[0149] Thus, compared with the case where the third end portion 92e3 is located at the same position as the surface of the retainer 124 facing the axial upstream side Dau in the axial direction Da, or located closer to the axial upstream side Dau than the surface, it is difficult for foreign matter M contained in the compressed air Ac flowing from the axial upstream side Dau to collide with and rebound against the main surface 92a of the plate portion 92, 92' facing the inner side of the radial direction Dr. In addition, it is difficult for foreign matter M contained in the compressed air Ac flowing from the outer side of the radial direction Dr to collide with and rebound against the main surface 92a of the plate portion 92 facing the inner side of the radial direction Dr.

[0150] (6) The blade ring assembly WS of the sixth scheme is based on the blade ring assembly of any one of the second to fifth schemes, and it is possible that the deflector 90 also includes a fixed platform 91, 91', 98, which is arranged between the two protrusions 73 in the circumferential direction Dc and installed on the turbine blade ring 70, and the plate portion 92, 92', 99 is installed on the outer end of the radial direction Dr in the fixed platform 91, 91', 98.

[0151] Thus, the fixing base portions 91 and 91 ′ in the cooling medium inlet port can support the plate portions 92 and 92 ′ from the inner side in the radial direction Dr.

[0152] (7) The blade ring assembly WS of the seventh scheme is based on the blade ring assembly WS of the sixth scheme. It can be that the plate portion 92 has a third end portion 92e3 as an end portion of the upstream side Dau of the axis, and the third end portion 92e3 is located on the downstream side Dad of the axis on both sides in the axial direction Da compared to the surface of the fixed platform portion 91 facing the upstream side Dau of the axis.

[0153] Therefore, compared with the case where the third end portion 92e3 is located at the same position as the surface of the fixed platform portion 91 facing the axial upstream side Dau in the axial direction Da, or is located closer to the axial upstream side Dau than this surface, the foreign matter M contained in the compressed air Ac flowing from the inner side of the radial direction Dr of the fixed platform portion 91 is less likely to collide with the main surface 92a on the inner side of the radial direction Dr of the plate portion 92 and rebound.

[0154] (8) The bale ring assembly WS according to an eighth aspect is the bale ring assembly WS according to the sixth or seventh aspect, wherein the fixing base portion 91 may be detachable from the turbine bale ring 70 in a state where the plate portion 92 and the fixing base portion 91 are integrated.

[0155] Thus, for example, maintenance such as repair of the fixing base portion 91 and the plate portion 92 can be easily performed compared to a case where the fixing base portion 91 and the plate portion 92 are not integrally formed.

[0156] (9) The blade ring assembly WS of the ninth embodiment is based on the blade ring assembly WS of any one of the sixth to eighth embodiments, and it is possible that the fixing platform 91 has a fixing portion (including the first portion 91a of the coupling hole 91h), which is capable of fixing the sealing member 85 that blocks the gap between the two tail cylinders 32 of the combustor 30 adjacent to each other in the circumferential direction Dc.

[0157] Thus, the fixing base 91 is a member that supports the plate portion 92 from the inner side in the radial direction Dr, and also serves as a member that fixes the sealing member 85. Therefore, for example, it is not necessary to provide a member other than the fixing base 91 for fixing the sealing member 85.

[0158] (10) The blade ring assembly WS of the tenth scheme is based on the blade ring assembly WS of any one of the sixth to ninth schemes, and it can be that the fixed platform portion 98 has a groove 98d, which is formed along the axial direction Da at a position closer to the radial inside than the plate portion 99, and divides the cooling medium intake passage 97a between the plate portion 99.

[0159] As a result, the amount of cooling medium flowing into the cooling structure of the stationary blade increases, and thus the cooling effect of the stationary blade can be improved.

[0160] (11) The eleventh embodiment of the bling assembly WS is the bling assembly WS of the tenth embodiment, wherein the plate portion 99 has a projection 99g formed to project toward the axial upstream side Dau and overlap the groove 98d when viewed from the outside in the radial direction Dr.

[0161] Thus, even when the deflector 97 in which the compressed air intake passage 97 a is formed is used, the extension portion 99 g can prevent the foreign matter M from flowing into the cooling structure from the stationary blade 46 a 1 .

[0162] (12) The blade ring assembly WS of the tenth embodiment is based on the blade ring assembly WS of any one of the first to eleventh embodiments, and it is possible that the two protrusions 73 each have a connecting portion (including an end surface 73u of the coupling hole 73h) that can be connected to a fixing component (combustor connecting member 80) for fixing the tail cylinder 32 of the combustor 30.

[0163] Thus, by using the two protruding portions 73 , the lengths of the plate portions 92 , 92 ′, and 99 can be made longer in the axial direction Da.

[0164] (13) The bale ring assembly WS of the thirteenth aspect is the bale ring assembly WS of any one of the first to twelfth aspects, wherein the turbine bale ring 70 and the inducer 90 may be formed of a material having the same composition.

[0165] As a result, the influence of the thermal expansion of the turbine blade ring 70 acting between the turbine blade ring 70 and the inducer 90 can be suppressed to be small. Therefore, the occurrence of a malfunction between the turbine blade ring 70 and the inducer 90 can be suppressed.

[0166] (14) The blade ring assembly WS of the fourteenth scheme is based on the blade ring assembly WS of any one of the first to thirteenth schemes. It can be that the proportion of the guide 90 covering the cooling medium inlet when observed from the outer side of the radial direction Dr is higher than the proportion of the guide 90 covering the cooling medium inlet when observed from the upstream side Dau of the axis.

[0167] Thus, the amount of cooling air Ac taken into the cooling medium inlet from the axial upstream side Dau is greater than the amount of compressed air Ac taken into the cooling medium inlet from the outer side in the radial direction Dr.

[0168] (15) The blade ring assembly WS of the fifteenth embodiment is based on the blade ring assembly WS of any one of the first to fourteenth embodiments, and it is possible to fix the deflector 90 to the fixing portion of the turbine blade ring 70 (including the first portion 91a of the insertion hole 93h) between the two protrusions 73 in the circumferential direction Dc.

[0169] Thereby, for example, compared with a case where the fixing portion of the inducer 90 is arranged on the outer peripheral side or the inner peripheral side of the turbine blade ring 70 , space saving can be achieved.

[0170] (16) The blade ring assembly WS of the sixteenth embodiment may be further provided with a forced cooling component (cooling medium circulation portion 100) based on the blade ring assembly WS of any one of the first to fifteenth embodiments. The forced cooling component is arranged on the outer peripheral side of the turbine blade ring 70 and is arranged at a position overlapping with the cooling medium inlet when viewed from the radial direction Dr for steam flow. The deflector 90 is arranged on the inner peripheral side of the forced cooling component.

[0171] (17) The gas turbine 10 of the seventeenth embodiment comprises: a rotor (gas turbine rotor 11) which is rotatable about the axis Ar; a casing (gas turbine chamber 15) which covers the rotor from the outer peripheral side; a blade ring assembly WS of any one of the first to sixteenth embodiments, which covers the rotor from the outer peripheral side in a state supported by the casing; and a combustor 30 which generates combustion gas G by combustion of fuel F and conveys the combustion gas G into the casing, wherein the stator blade 46a included in the blade ring assembly WS is a first-stage turbine stator blade (stator blade 46a1) in the axial direction Da.

[0172] Description of reference numerals:

[0173] 7…Leaf ring body

[0174] 7a, 73h, 75h, 91h, 94h…combination hole

[0175] 7s…upstream

[0176] 10…Gas turbine

[0177] 11…Gas turbine rotor

[0178] 15…Gas turbine room

[0179] 20…Compressor

[0180] 21…Compressor rotor

[0181] 22, 42…Rotor shaft

[0182] 23, 43…Motor stage

[0183] 23a, 43a…moving blades

[0184] 25…Compressor room

[0185] 26, 46…Stator stage

[0186] 26a…Station blade

[0187] 30…Burners

[0188] 31…Inhalation

[0189] 32…Tail tube

[0190] 40…Turbine

[0191] 41…Turbine rotor

[0192] 45…Turbine room

[0193] 45a…Outside engine room

[0194] 45b…Inner engine room

[0195] 45c…Split ring

[0196] 45p...Cooling air passage

[0197] 46a…Gas turbine stator blades

[0198] 46a1…Station blade

[0199] 49…Combustion gas flow path

[0200] 50…Cooling device

[0201] 51…Foreign matter trap

[0202] 52…Cooler

[0203] 53… Booster compressor

[0204] 54…Cooling air line

[0205] 61…front wall

[0206] 61a…Cylinder

[0207] 61b…Cylindrical cover

[0208] 61h…Open

[0209] 62…Wall

[0210] 62a…First perimeter wall

[0211] 62b…Second peripheral wall

[0212] 63…Back wall

[0213] 64…Guide

[0214] 70…Turbine blade ring

[0215] 70o…Outer Surface

[0216] 70i…Inner Surface

[0217] 70d…Downstream end face

[0218] 70u…Upstream side end face

[0219] 71…Blade ring fixing part

[0220] 72…Air intake

[0221] 72a…Narrow part

[0222] 73…Protrusion

[0223] 73a ... first protrusion

[0224] 73b ... second protrusion

[0225] 73u…end face

[0226] 75…Deflector fixing part

[0227] 75a…Fixed surface

[0228] 75b…Bearing surface

[0229] 76…Cooling holes

[0230] 80…Burner connecting components

[0231] 81…Frame

[0232] 82…Flange

[0233] 82h, 91c, 92h, 93h, 95h…through hole

[0234] 83, 93, 94, 95, 96…Joints

[0235] 85…Sealing components

[0236] 90, 97…Deflector

[0237] 91, 91', 98...Fixed table

[0238] 91a…Part 1

[0239] 91b…Part 2

[0240] 92, 92', 99... board

[0241] 92a, 99a…main surface

[0242] 92e1…first end

[0243] 92e2…Second end

[0244] 92e3…third end

[0245] 98d...slot

[0246] 99g…Extension

[0247] 100…Cooling medium circulation part

[0248] 110…Blade body

[0249] 110h…Exhaust hole

[0250] 120…Outer shroud

[0251] 121, 131…Shield body

[0252] 121a, 131a…gas passage surface

[0253] 121b…Outer inner surface

[0254] 122, 132…Surrounding wall

[0255] 122a, 132a ... front wall portion

[0256] 122b, 132b…rear wall portion

[0257] 122c, 132c ... back side wall

[0258] 123, 133…collision plate

[0259] 123h…Air hole

[0260] 124…Retaining parts

[0261] 124a…Front surface

[0262] 130…Inner shroud

[0263] 131b…Inside inner surface

[0264] 140…Air passage

[0265] 150...Shield

[0266] A…Air

[0267] A1, A2, A2', A3, A4...arrow

[0268] Ac…Compressed air

[0269] Ar…axis

[0270] CA…Chamber

[0271] Da…axis direction

[0272] Dad…Downstream side of axis

[0273] Dau…Axis upstream side

[0274] Dc, Dcn, Dcp…circumferential

[0275] Dr… Radial

[0276] Dri…Radial Inboard

[0277] Dro…Radial Outer

[0278] F…Fuel

[0279] G…Combustion gas

[0280] G1, G2…Gap

[0281] GEN…Generator

[0282] L1: Width of the plate portion in the first direction

[0283] L2: width of the narrow portion in the first direction

[0284] R…Containment Chamber

[0285] S1…First Space

[0286] S2…Second Space

[0287] WS…leaf ring assembly.

Claims

1. A leaf ring assembly, wherein: The leaf ring assembly comprises: a turbine blade ring extending in a circumferential direction centered on the axis; a stationary blade disposed on the inner circumference of the turbine blade ring; and a flow guide arranged on the outer peripheral side of at least a portion of the turbine blade ring, The turbine blade ring has: The main body of the leaf ring; as well as a plurality of protrusions which protrude from the upstream side of the axis of the blade ring body on both sides in the axis direction extending toward the axis and are arranged at different positions in the circumferential direction at intervals from each other, Two protrusions adjacent to each other in the circumferential direction included in the plurality of protrusions form a cooling medium inlet opening extending from the outer peripheral side of the turbine blade ring to the inner peripheral side together with the blade ring body. The deflector is configured to shield at least a portion of the cooling medium inlet when viewed in a radial direction centered on the axis.

2. The leaf ring assembly according to claim 1, wherein: The deflector includes a plate portion having a main surface extending in a direction intersecting the radial direction.

3. The leaf ring assembly according to claim 2, wherein: The cooling medium inlet has a smallest portion where the cooling medium inlet is narrowest between the inner peripheral ends of the two protruding portions. The width of the plate portion in the first direction in which the two protrusions are adjacent is larger than the width of the smallest portion of the cooling medium intake port in the first direction.

4. The leaf ring assembly according to claim 2, wherein: The plate portion has a first end portion and a pair of second end portions, wherein the first end portion is an end portion on the downstream side of the axis of the two sides in the axial direction, and the pair of second end portions are two end portions in the first direction adjacent to the two protrusions. The first end portion and the pair of second end portions are arranged with a gap therebetween from the turbine blade ring.

5. The leaf ring assembly according to claim 2, wherein: The plate portion has a third end portion, and the third end portion is an end portion on the upstream side of the axis. The third end portion is located on the axial downstream side of both sides in the axial direction relative to a surface of a retainer included in the stationary blade that faces the axial upstream side.

6. The leaf ring assembly according to claim 2, wherein: The deflector further includes a fixing platform, which is arranged between the two protruding portions in the circumferential direction and mounted on the turbine blade ring. The plate portion is attached to an outer end portion in the radial direction of the fixing platform portion.

7. The leaf ring assembly according to claim 6, wherein: The plate portion has a third end portion, and the third end portion is an end portion on the upstream side of the axis. The third end portion is located on the axial downstream side of both sides in the axial direction relative to the surface of the fixing table portion facing the axial upstream side.

8. The leaf ring assembly according to claim 6, wherein: The fixing base portion is detachable from the turbine blade ring in a state where the plate portion and the fixing base portion are integrated.

9. The leaf ring assembly according to claim 6, wherein: The fixing stage has a fixing portion capable of fixing a sealing member that closes a gap between two transition pieces of the combustors adjacent to each other in the circumferential direction.

10. The leaf ring assembly according to claim 6, wherein: The fixing table portion has a groove, the groove being formed along the axial direction at a position radially inward of the plate portion and defining a cooling medium intake passage between the fixing table portion and the plate portion.

11. The leaf ring assembly according to claim 10, wherein: The plate portion has a protruding portion that is formed to protrude toward the upstream side of the axis and overlaps with the groove when viewed from the outside in the radial direction.

12. The bling assembly according to claim 1, wherein: The two protrusions respectively have connection portions that can be connected to a fixing member for fixing a tail pipe of the combustor.

13. The bling assembly according to claim 1, wherein: The turbine blade ring and the inducer are formed of a material of the same composition.

14. The bling assembly according to claim 1, wherein: The ratio at which the air guide blocks the coolant intake port when viewed from the outer side in the radial direction is higher than the ratio at which the air guide blocks the coolant intake port when viewed from the upstream side in the axial direction.

15. The bling assembly according to claim 1, wherein: A fixing portion that fixes the deflector to the turbine blade ring is arranged between the two protruding portions in the circumferential direction.

16. The bling assembly according to claim 1, wherein: The blade ring assembly further includes a forced cooling member, which is provided on the outer peripheral side of the turbine blade ring and is arranged at a position overlapping with the cooling medium inlet when viewed from the radial direction, so that the cooling medium flows. The deflector is arranged on the inner peripheral side of the forced cooling member.

17. A gas turbine, wherein: The gas turbine comprises: a rotor rotatable about the axis; a housing covering the rotor from an outer peripheral side; The blade ring assembly according to any one of claims 1 to 16, which covers the rotor from the outer peripheral side in a state supported by the housing; and a burner that generates combustion gas by burning fuel and delivers the combustion gas into the housing, The stationary blades included in the blade ring assembly are first-stage turbine stationary blades in the axial direction.

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