Patent Application
20170211421
The present invention relates to a vane, a gas turbine, a rim, segment, a remodeling method for a vane, and a remodeling method for a ring segment.
Priority is claimed on Japanese Patent Application No. 2014-158828, tiled on Aug. 4, 2014, the content of which is incorporated herein by reference.
A gas turbine vane is known that has shrouds formed on a radially inward side and a radially outward side of the airfoil section. The outer shroud located on the radially outward side is provided with a hook on the outer side. The outer shroud is usually supported by an insulating ring or casing through the hook.
Of the vane thus constructed, the airfoil section is arranged in a gas path through which a high-temperature working fluid flows. Cooling air flows on the side of the shroud of the vane opposite from the gas path. The outer shroud tries to deform so as to warp toward the radially outward side due to a large temperature difference between the high-temperature working fluid inside the gas path and the cooling air.
The hook provided on the shroud protrudes to a large extent in the radial direction of the shroud. Thus, the hook has a high moment of inertia of area relative to the warping deformation of the shroud. As a result, the hook restricts the deformation of the shroud body, causing high heat stress on the shroud.
Patent Document 1 shows a turbine vane in which a hook does not continuously extend in a circumferential direction, but instead a recessed part having a shape of scallop is formed in order to relax mechanical stress and heat stress. Patent Document 1 further discloses a sealing assembly having a sealing member which is arranged so as to at least partially overlap the recessed part to prevent a fluid from leaking through the recessed part.
Patent Document 1: JP4781744B
If the recessed part is formed in the hook in order to relax the stress and the sealing assembly is disposed so as to cover the recessed part as disclosed in Patent Document 1, cooling air is capable of leaking through gaps between parts around the recessed part. Therefore, the cooling air flowing into the gas path increases, which may degrade the performances of the gas turbine.
An object of the present invention is to provide a vane, a gas turbine, a ring segment, a remodeling method for a vane, and a remodeling method for a ring segment which can reduce heat stress and also restrict an increase in amount of air leakage.
According to a first aspect of the present invention, a vane includes an airfoil section extending in a radial direction and an outer shroud located on the radially outward side of the airfoil section, and is supported inside a casing by a sane support member. The outer shroud includes a hook section. The hook section has a shroud body, a radial protrusion, and an engaging part. The shroud body extends in an axial direction and a circumferential direction. The radial protrusion is provided on the radially outward side of the shroud body, protrudes toward the radially outward side, and extends in the circumferential direction. The engaging part protrudes in the axial direction from the radial protrusion and extends in the circumferential direction. The hook section includes a recessed part recessed in the axial direction or the radial direction in at least a part of the circumference. The engaging part has a sealing surface which contacts the vane support member in the radial direction continuously along the entire circumference of the engaging part.
The vane thus constructed is capable of reducing the stiffness of the hook section by the recessed part. Therefore, the hook section is capable of deforming following a deformation of the shroud body due to heating. The hook section has the recessed part recessed in the axial direction or the radial direction, and yet the sealing surface is not split by the recessed part in the circumferential direction. As a result, it is possible to limit an increase in the amount of air leakage and relax heat stress.
According to a second aspect of the present invention, the hook section of the vane according to the first aspect may have a front hook arranged on the upstream side in the axial direction. The engaging part of the front hook may have a sealing surface on the radially inward side.
The recessed part of the vane thus constructed is capable of reducing the stiffness of the front hook having the sealing surface on the radially inward side without splitting the sealing surface. As a result, it is possible to limit an increase the amount of air leakage and relax the heat stress acting on the front hook side of the shroud body.
According to a third aspect of the present invention, in the vane in the second aspect, an area in the circumferential direction, in which the recessed part is arranged, may include a position in the circumferential direction at which a leading edge of the airfoil section is arranged.
The vane thus constructed is capable of relaxing stress at a highly stressed area in the leading edge.
According to a fourth aspect of the present invention, the hook section of the vane according to any one of the first to third aspects of the present invention may include a rear hook arranged on the downstream side in the axial direction. The engaging part of the rear hook may include a sealing surface on the radially outer circumferential side.
The recessed part of the hook section thus constructed is capable of relaxing the stress acting on the rear hook side of the shroud body by reducing the stiffness of the rear hook having the sealing surface on the radially outer circumferential side.
According to a fifth aspect of the present invention, in the vane of the fourth aspect, an area in the circumferential direction, in which the recessed part is formed, may include a position in the circumferential direction at which a trailing edge of the airfoil section is arranged.
The vane thus constructed is capable of relaxing stress at a highly stressed area in the trailing edge of the airfoil section.
According to a sixth aspect of the present invention, in the vane of any one of the first, second, and fourth aspects an area in the circumferential direction, in which the recessed part is formed, my include the center in the circumferential direction of the hook section.
The vane thus constructed is capable of effectively reducing the stiffness of the hook section relative to a bending deformation of the shroud.
According to a seventh aspect of the present invention, a ring segment of a gas turbine is supported in a casing of the gas turbine by a ring segment support member, and delimits an outer circumference of an annular high-temperature gas passage. This ring segment has a hook section. The hook section has a ring segment body, a radial protrusion, and an engaging part. The ring segment body extends in an axial direction and a circumferential direction. The radial protrusion is provided on the radially outward side of the ring segment body, protrudes toward the radially outward side, and extends in the circumferential direction. The engaging part protrudes in the axial direction from the radial protrusion and extends in the circumferential direction. The hook section has a recessed part recessed in the axial direction or the radial direction in at least a part of the circumference. The engaging part has a sealing surface which contacts the ring segment support member in the radial direction continuously along the entire circumference of the engaging part.
The recessed part of the ring segment thus constructed is capable of reducing the stiffness of the hook section thereof Therefore, the hook section is capable of deforming following a deformation of the heated ring segment body. The hook section has the recessed part recessed in the axial direction or the radial direction. The engaging part has the scaling surface extending continuously along the entire circumference of the engaging part. Therefore, the recessed part does not split the sealing surface in the circumferential direction. As a result, it is possible to limit an increase in amount of air leakage and relax heat stress.
According to an eighth aspect of the present invention, a gas turbine has at least one of the vane of any one of the first to sixth aspects of the present invention, and the ring segment of the seventh aspect of the present invention.
The gas turbine thus constructed is capable of limiting an increase in the amount of air leakage and limiting heat stress in the shroud body and the ring segment body. Thus, it is possible to improve the performance and the reliability of the gas turbine.
According to a ninth aspect of the present invention, a remodeling method is a method for remodeling a vane supported in a easing by a vane support member. The vane has an airfoil section extending in a radial direction, and an outer shroud arranged on the radially outward side of the airfoil section. The outer shroud has a hook section. The hook section has a shroud body, a radial protrusion, and, an engaging part. The shroud body extends in an axial direction and a circumferential direction. The radial protrusion is provided on the radially outward side of the shroud body, protrudes toward the radially outward side, and extends in the circumferential direction. The engaging part protrudes in the axial direction from the radial protrusion and extends in the circumferential direction. The remodeling method for the vane has a step of forming a recessed part recessed in the axial direction or the radial direction, in at least a part of the hook section in the circumferential direction, so as to form a sealing surface which contacts the vane support member in the radial direction along the entire circumference of the engaging part.
The method having the above step is capable of forming a recessed part in an existing vane, while the turbine is being maintained, so as to reduce the amount of air leakage and to relax heat stress.
According to a tenth aspect of the present invention, a remodeling method is a method for a ring segment of a gas turbine which is supported in a casing by a ring segment support member and delimits an outer circumference of an annular high-temperature gas passage. The ring segment has a hook section. The hook section has a ring segment body, a radial protrusion, and an engaging part. The ring segment body extends in an axial direction and a circumferential direction. The radial protrusion is provided on the radially outward side of the ring segment body, protrudes toward the radially outward side, and extends in the circumferential direction. The engaging part protrudes in the axial direction from the radial protrusion and extends in the circumference direction. The remodeling method for the ring segment includes a step of forming a recessed part recessed in the axial direction or the radial direction, in at least a part of the hook section in the circumference direction, so as to form a sealing surface which contacts the ring segment support member in the radial direction continuously along the entire circumference of the engaging part.
The above-described vane, gas turbine, ring segment, remodeling method for a vane, and remodeling method for a ring segment are capable of limiting an increase in amount of air leakage and of relaxing heat stress.
Hereinafter, a vane, a gas turbine, a ring segment, a remodeling method for a vane, and a remodeling method for a ring segment according to a first embodiment of the present invention will be described.
As indicated in
The compressor 2 draws in air through an air inlet and compresses it into compressed air.
The combustor 3 is connected with an outlet of the compressor 2. The combustor 3 injects fuel to the compressed air exhausted from the compressor 2 and generates combustion gas G having a high temperature and high pressure.
The turbine section 4 is provided with a casing 6 and a rotor 7.
The casing 6 has a form of cylinder around a rotor axis Ar (shown in
The rotor 7 is supported by the casing 6 so as to be rotatable around the rotor axis Ar.
The turbine section 4 drives the rotor 7 to rotate by using the combustion gas sent from the combustor 3 as a working fluid. The driving force thus generated in the turbine section 4 is transferred to a generator (not shown in the figures) coupled to the rotor 7. In the following description, “upstream side” means the side of the rotor axis Ar of the turbine section 4 which is toward the compressor 2, and “downstream side” means the other side of the rotor axis Ar opposite to the upstream side. Further, “axial direction Da” means a direction in which the, rotor axis Ar extends, “circumferential direction Dc” means a direction of the circumference of the rotor axis Ar, and “radial direction Dr” means a direction radial to the rotor axis Ar. Further, “radially inward” means one side approaching the rotor a Ar in the radial direction Dr, and “radially outward” means the other side leaving from the rotor axis Ar.
As indicated in
The blade 12 is provided with a blade body 13, a platform 14 and a blade root 15. The blade body 13 extends in the radial direction Dr. The platform 14 is provided on the radially inward sick of the blade body 13. The blade root 15 is provided on the radially inward side of the platform 14. The blade 12 is fixed to the rotor body 10 by inserting the blade root 15 to the rotor body 10.
A vane stage 17 is arranged on the upstream side of each of the plurality of blade stages 11. Each of the vane stages 17 is provided with a plurality of vanes 18. The plurality of vanes 18 are aligned in the circumferential direction Dc. The vane 18 is provided with a vane body (airfoil section) 19, an outer shroud 20, and an inner shroud 21. The vane body 19 extends in the radial direction Dr. The outer shroud 20 is provided on the radially outward side of the vane body 19. The inner shroud 21 is provided on the radially inward side of the vane body 19.
A blade ring 23 is arranged on the radially outward side of the blade stage 11 and the vane stage 17 and radially inward side of the casing 6. The blade ring 23 has a cylindrical form around the rotor axis Ar. The blade ring 23 is fixed to the casing 6. The vane ring 23 is connected to the outer shroud 20 of the vane 18 by an insulation ring 24 serving as a vane support member.
A ring segment 25 is arranged between the outer shrouds 20 next to each other in the axial direction Da. The plurality of ring segments 25 are aligned in the circumferential direction Dc around the rotor axis Ar. The plurality of ring segments 25 aligned in the circumferential direction Dc form an annular shape. The blade stage 11 is arranged on the radially inward side of the ring segments 25. All the plurality of ring segments 25 aligned in the circumferential direction Dc are connected to the blade ring 23 by the insulation ring 24.
The combustor 3 has a transition piece 27 and a fuel supplier 28. The transition piece 27 sends the high-pressure and high-temperature combustion gas G to the turbine section 4. The fuel supplier 28 supplies fuel and compressed air to the transition piece 27. An outlet flange 29 on the downstream side of the transition piece 27 is connected with the inner shroud 21 and the outer shroud 20 of vanes 18a composing a first vane stage 17a.
The compressed air A flows from the compressor 2 into the casing 6 of the turbine section 4 and further flows into the fuel supplier 28 of the combustor 3 through the circumferential area of the combustor 3. The fuel supplier 28 supplies the feel from the outside to the transition piece 27 together with the compressed air A. The fuel is burned in the transition piece 27 to generate the combustion gas G. The combustion gas G passes between the inner shrouds 21 and the outer shrouds 20 of the plurality of vanes 18 composing the vane stages 17, and between the platforms 14 of the plurality of blades 12 composing the blade stage 11 located on the downstream side of the vane stage 17, and the ring segments 25 arranged on the radially outward side of the blades 12. The combustion gas G rotates the rotor 7 around the rotor axis Ar by contacting the blade body 13 in the above passing process.
An annular combustion gas passage Pg through which the combustion gas G flows is delimited by the outer shroud 20 and the inner shroud 21 of the vane 18, the platform 14 of the blade 12, and the ring segment 25 facing the platform 14. The vane 18, the blade 12, and the ring segment 25 contact the combustion gas G haying high temperature and high pressure, and therefore, work as hot parts.
A part of the above compressed air A or compressed air. A bled from the compressor 2 flows into an area on the radially outward side of the outer shroud 20 and an area on the radially inward side of the inner shroud 21 so as to cool the outer shroud 20 and the inner shroud 21 of the vane 18. A pan of the above compressed air A flowing into the casing 6 from the compressor 2 or the compressed air A bled from the compressor 2 is also supplied to an area on the radially inward side of the casing 6 and radially outward side of the blade ring 23. The compressed air A flows into the radially outward side of the ring segment 25 through the blade ring 23 so as to cool the ring segment 25 arranged on the radially inward side of the blade ring 23.
As indicated in
The outer shroud 20 has a shroud body 31 and a hook section 32.
The shroud body 31 extends in the axial direction Da and the circumferential direction Dc. The shroud body 31 has a shape of board curving in the circumferential direction Dc. The shroud body 31 has the vane bodies 19 extending from the inner circumferential surface of the shroud body 31 to the radially inward side.
The hook section 32 is formed so as to engage the vane segment 30 with the insulation ring 24. The hook section 32 has a front hook 33 and a rear hook 34.
As indicated in
The front hook 33 has a protrusion 36 protruding to the downstream side in the axial direction Da. The protrusion 36 protrudes from a radially outer end of the front hook 33.
The rear hook 34 is arranged on the downstream side in the axial direction Da nearby a peripheral end 20b of the outer shroud 20. The rear hook 34 in the first embodiment is arranged at the peripheral end 20b on the downstream side of the outer shroud 20. The rear hook 34, like the front hook 33, protrudes to the radially outward side from the shroud body 31 of the outer shroud 20. The rear hook 34 is formed continuously over the entire width of the outer shroud 20 in the circumferential direction Dc. The rear hook 34 has a protrusion 37 protruding toward the upstream side in the axial direction Da.
As indicated in
Since the vane 18 is pressed by the combustion gas G flowing from the upstream to the downstream, a three trying to shift the front hook 33 to the radially inward side acts on the front hook 33. As a result, a radially inward face of the protrusion 36 in the front hook 33 is pressed against a radially outward face of the supporting section 41 in the insulation ring 24. By this action, a gap 42a between. the radially inward face of the protrusion 36 and the radially outward face of the supporting section 41 narrows.
The cross-sectional area of the gap 42a is the narrowest in a passage between the insulation ring 24 and the front hook 33 through which cooling air leaks to the combustion gas passage Pg (shown in
The insulation ring 24 has a rear engaging part 40 which engages with the rear hook 34. The rear engaging part 40 extends to the radially inward side so as to be located next to the upstream side of the rear hook 34. The rear engaging part 40 has a supporting section 43 supporting the protrusion 37 of the rear hook 34 from the radially inward side. The supporting section 43 extends from the upstream side to the downstream side in the axial direction Da. The supporting section 34 is formed continuously in the circumferential direction Dc in the same way as the rear hook 34.
When the combustion gas G flowing from the upstream to the downstream presses the vane 18, a force trying to shin the rear hook 34 toward the radially outward side acts on the rear hook 34. By the action of the three, a radially outward face of the protrusion 37 in the rear hook 34 is pressed against a surface of a radially inward face 24a of the insulation ring 24. By this action, a gap 45a between the radially outward face of the protrusion 37 and the radially inward the 24a of the insulation dug 24 narrows. The cross-sectional area of the gap 45a is the narrowest in a passage between the insulation ring 24 and the rear hook 34 through which cooling air leaks to the combustion gas passage Pg (shown in
The rear hook 34 has the sealing surface 45 that is the face directed to the radially outward side, i.e., both of the face directed to the radially outward side of a hook body 44 which rises toward the radially outward side, and the face directed to the radially outward side of the protrusion 37. In the first embodiment, the face directed toward the radially outward side of the hook body 44 and the thee directed toward the radially outward side of the protrusion 37 form the unitary sealing surface 45 which continues in the circumferential direction Dc.
Each of the sealing surfaces 42, 45 limits leakage of the cooling air, which is supplied to the radially outward side of the outer shroud 20, to the combustion gas passage Pa on the radially inward side of the outer shroud 20.
As indicated in
The recessed part 50 in the first embodiment is formed in a central part in the circumferential direction Da of the vane segment 30. In other words, the recessed part 50 is formed in a part including the center in the circumferential direction Dc of the hook section 32. The recessed part 50 in the first embodiment is formed in the rear hook 34 so as to be recessed from the upstream side to the downstream side in the axial direction Da. More specifically, when seen along the axial direction Da, the recessed part 50 extends from the side of the protrusion 37 to the hook body 44 and is recessed to such an extent as not to penetrate to the downstream side of the hook body 44 in the axial direction Da. A face 51 of the recessed part 50 directed to the downstream side is located between a central part C1 (shown in
The recessed part 50 has the face 51 directed to the downstream side, a face 52 directed to the radially inward side, and faces 53 located on both sides of the recessed part 50 in the circumferential direction Dc. The face 51 directed to the downstream side extends in the radial direction Dr and also in the circumferential direction Dc. The face 52 directed to the radially inward side extends in the axial direction Da and also in the circumferential direction Dc. The faces 53 directed to both sides in the circumferential direction Dc extend in the radial direction Dr and also in the axial direction Da. Corners where the face 51 directed to the downstream side, the face 52 directed to the radially inward side, and the faces 53 arranged on both sides in the circumferential direction Dc are connected to one another have a curved surface.
Next, a remodeling method far the vane 18 in the gas turbine 1 or the first embodiment will be described with reference to the figures. The method of the first embodiment is a remodeling method for a gas turbine which is an existing gas turbine. A remodeling method for the ring segment 25 described later is similar to the following remodeling method for the vane. Therefore, a specific description of the remodeling method for the ring segment 25 will be omitted.
Firstly, as a preparing process, the vane 18 is removed from the insulation ring 24.
Secondly, as indicated in
Next, as a finishing process, the vane 18 is assembled to the insulation ring 24 in reversed processing order of removing the hook section 32 from the insulation ring 24. The remodeling method for the vane 18 is completed by the above processing.
In the first embodiment, the stiffness of the rear hook 34 in the hook section 32 can be reduced by the recessed part 50. Therefore, the rear hook 34 can deform following a deformation of the shroud body 31 by heating. The hook section 32 has the recessed part 50 recessed in the axial direction or the radial direction, and yet the sealing surface 45 of the protrusion 37 is not split by the recessed part 50 in the circumferential direction Dc. Thus, the vane in the first embodiment can limit an increase in the amount of air leakage and extend the lifetime of the vane 18 by relaxing the heat stress acting on the vane 18.
Further, since the vanes 18 comprise the plurality of vane segments 30, the recessed part 50 can be easily formed at each of the plurality of vane segments 30. As a result, the stiffness of the rear hook 34 can be easily reduced.
Further, the vane in the first embodiment can limit the heat stress on the shroud body 31 while limiting an increase in the amount of air leakage. Therefore, the performance and the reliability of the gas turbine can be improved.
Next, a vane in a second embodiment of the present invention will be described. The vane of the second embodiment has a further recessed part in the front hook 33 of the vane in the first embodiment. Therefore, the same reference numbers are used for the components of the following second embodiment which are equivalent to those of the first embodiment, and repeated description for the equivalent components are omitted.
The front hook 33 has a recessed part 60. The recessed part 60 is formed in at least a part of the front hook 33 in the circumferential direction Dc. The recessed part 60 has the sealing surface 42 over at least a part thereof in the axial direction Da. The recessed part 60 is formed in the front hook 33 so as to be recessed in the axial direction Da.
More specifically, the recessed part 60 has a shape curved from a part 60a an the downstream side of the sealing surface 42 in the protrusion 36 in the axial direction Da, via a part 60b the radially outward side of the hook body 61, to a part 60c on the upstream side of the hook body 61 in the axial direction Da. In other words, the recessed part 60 is arranged in the axial direction Da relative to the sealing surface 42 at the part 60a on the downstream side of the sealing surface 42 in the axial direction Da and also at the part 60c on the upstream side of the hook body 61 in the axial direction Da. The part 60c on the upstream side of the recessed part 60 is located further upstream in the axial direction Da than an end face 36a of the protrusion 36 across the seating surface 42.
According to the second embodiment, the stiffness of the front hook 33 can be reduced by the recessed part 60. Thus, the recessed part 60 is capable of reducing the heat stress on the upstream side in the axial direction Da of the shroud body 31.
Since the sealing surface 42 is formed continuously in the circumferential direction Dc over the entire width of the front hook 33, the performance of sealing between the front engaging part 39 and the front hook 33 is secured. As a result, reduction of the stiffness of the front hook 33 thus performed does not cause an increase in the amount of air leakage.
The recessed parts 60 formed on both of the upstream side and the downstream side of the sealing surface 42 in the axial direction Da are capable of sufficiently reducing the stiffness of the front hook 33. As a result, the heat stress acting on the upstream side in the axial direction Da of the shroud body 31 can be sufficiently reduced.
In the above embodiments, an example of forming the recessed part 50 on the upstream side in the axial direction Da of the sealing surface 45 in the rear hook 34 has been described. However, the sealing surface 45 can be arranged in various areas in the axial direction Da relative to the recessed part 50. For instance, as indicated in
In the above second embodiment, an example of forming the recessed part 60 on the upstream side and also on the downstream side in the axial direction Da of the sealing surface 42 in the front hook 33 has been described. Alternatively, however, the recessed part 60 can be formed on one of the upstream side and the downstream side of the sealing surface 42. For instance, as indicated in
The outer shroud 20 of the vane segment 30 in each of the first and second embodiments has only one recessed pan 50 at the central part in the circumference direction Dc. However, the number and location of the recessed part 50 is not limited to those in the first and second embodiments. For instance, as indicated in the third variation in
The outer shroud 20 of the vane segment 30 in each of the first and second embodiments has the recessed part 50 in a part of the rear hook 34 in the circumferential direction Dc. However, the construction of the recessed part 50 is not limited to that in the first and second embodiments. For instance, as indicated in the fourth variation in
The present invention is not limited to the embodiments and the variations, but includes various changes to the above embodiments and variations unless such changes depart from the scope of the present invention. In other words, the specific shapes, configurations, etc. described in the embodiments and the variations are just examples and can be modified as appropriate.
For instance, the shape of the recessed part 50 is not limited to the shape described in the first embodiment as far as the shape is effective in reducing the stiffness of the hook section 32.
In the first and second embodiments, the structure in which the recessed part 50 is formed in the rear hook 34 so as to be recessed from the upstream side to the downstream side in the axial direction Da has been described. However, the shape of the recessed part 50 is not limited to that in the embodiments. For instance, a recessed part 50 may be formed so as to be recessed in the radial direction Dr as in the fifth variation shown in
In the above embodiments, the recessed part 50 has the shape of an angular groove when seen in a cross-section perpendicular to the axial direction Da. However, the shape of the recessed part 50 is not limited to this shape, and other shapes which can reduce the stiffness of the hook section 32 can be adopted for the recessed part 50. For instance, as in the sixth variation indicated in
As shown in
A connection area where the shroud body 31 is connected with the leading edge 19a of the vane body 19 and a connection area where the shroud body 31 is connected with the trailing edge 19b each undergoes a deformation of the vane body 19 in addition to deformation of the shroud body 31. Heat stress in these connection areas thus tends to be high. It is possible to efficiently relax the heat stress in these highly-stressed areas by arranging the recessed part 50 in an area where the trailing edge 19b of the vane body 19 is located and arranging the recessed part 60 in an area where the leading edge 19a of a vane body 19 is located when seen in the circumferential direction Dc. In
In the above embodiments, the structures in, which the protrusion 37 in the rear hook 34 protrudes toward the upstream side in the axial direction Da have been described. However, the direction in which the protrusion 37 protrudes is not limited to the direction toward the upstream side in the axial direction Da. For instance, as in the tenth variation indicated in
In the second embodiment, the recessed part 60 is formed in the front hook 33 and the recessed part 50 is formed in the rear hook 34. However, for instance, a structure in which a recessed part 60 is formed in a front hook 33 and a recessed part 50 is not provided in a rear hook 34 is also conceivable.
In the first and second embodiments, the recessed parts 50 and 60 are formed in the outer shroud 20 of the vane 18. However, recessed parts 50 and 60 can also be employed in the ring segments 25.
As indicated in
The hook section 71 has a radial protrusion 72 and an engaging part 73. The radial protrusion 72 is arranged on the outward side of the ring segment body 70 in a radial direction Dr. The radial protrusion 72 protrudes toward the outward side in the radial direction Dr and extends in the circumferential direction Dc. The engaging part 73 protrudes from the radial protrusion 72 toward the downstream side in the axial direction Da and extends in the circumferential direction Dc. The hook section 71 has a recessed part 74, recessed in the axial direction Da or the radial direction Dr, in at least a part of the hook section 71 in the circumferential direction Dc.
In the ring segment 25 thus constructed, the recessed part 74 is capable of reducing the stiffness of the hook section 71 in the same manner as the outer shroud 20 in the embodiments. Therefore, the hook section 71 is capable of deforming following a deformation of the ring-segment body 70 due to heating. The recessed part 74 does not split the sealing surface 75 of the radial protrusion 72 in the circumferential direction Dc. Therefore, the scaling surface 75 can be formed continuously in the circumferential direction Dc. As a result, it is possible to limit an increase in the amount of air leakage and relax the heat stress acing on the ring segment body 70 so as to extend the lifetime of the ring segment 25. A variety of shapes and layouts may be adopted for the recessed part 74 of the ring segment 25 as with the recessed parts 50 in the vanes 18 in the above embodiments and variations.
The present invention can be utilized for a vane, a gas turbine, a ring segment, a remodeling method for a vane, and a remodeling method for a ring segment. The present invention is capable of limiting an increase in the amount of air leakage and relaxing heat stress.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2014-158828 | Aug 2014 | JP | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2015/068623 | 6/29/2015 | WO | 00 |
