JP2019044740A - Stationary blade, stationary blade group, and gas turbine - Google Patents

Abstract

To provide a stationary blade, a stationary blade group, and a gas turbine of the invention capable of absorbing the difference in thermal expansion coefficient between a ceramic group composite material and a metallic material after stabilizing the attitude of a stationary blade body.SOLUTION: A stationary blade comprises: first and second fastening members 75 and 76 for fastening an outer shroud 67, a stationary blade body 69, and an inner shroud 65 in a radial direction Dr; and a spring member 78 interposed between one end of the first and second fastening members 75 and 76 located inside the inner surface of the inner shroud 65 and the inner surface of the inner shroud 65, and between the other end of the first and second fastening members 75 and 76 located outside the outer surface of the outer shroud 67 and the outer surface of the outer shroud 67.SELECTED DRAWING: Figure 3

Description

  The present invention relates to a vane, a vane group, and a gas turbine.

  A stationary blade group used for a gas turbine is configured such that a plurality of stationary blades are annularly arranged. The vanes are exposed to the hot combustion gases. For this reason, the stator vanes are cooled by guiding the cooling air to the base end portion of the stator vanes and guiding the cooling air to a cooling air flow path formed in the stator vanes.

In a gas turbine, it is possible to improve turbine output and turbine efficiency by raising the temperature of combustion gas.
For this reason, in recent years, ceramic matrix composites (CMC; Ceramic Matrix Composites), which are more heat resistant than metal materials, are used as the material of the vanes (see, for example, Patent Document 1).

  In order to absorb the difference in thermal expansion coefficient between the ceramic matrix composite material and the metal, Patent Document 1 discloses between the inner flange portion and the inner metal ring which are disposed on the inner side of the stator blade made of the ceramic matrix composite material. A structure is disclosed in which an undulating wave spring is interposed and an undulating wave spring is interposed between an outer flange portion disposed on the outer side of the vane and an outer metal ring.

U.S. Pat. No. 7,824,152

By the way, in patent document 1, a part of convex part of a metal ring (an inner metal ring or an outer metal ring) is inserted in the recessed part which a flange part (an inner flange part and an outer flange part) divides. Since the position of the stationary blade with respect to the metal ring is regulated, the posture of the stationary vane main body (a portion of the stationary blade disposed between the inner flange portion and the outer flange portion) is unstable.
For this reason, it is difficult to absorb the difference in thermal expansion coefficient between the ceramic base composite material and the metal material after stabilizing the attitude of the stator main body at the time of start-up and steady operation of the gas turbine.

  Therefore, the present invention provides a vane, a vane group, and a gas turbine capable of absorbing the difference in thermal expansion coefficient between the ceramic base composite material and the metal material while stabilizing the attitude of the vane body. Intended to be provided.

  In order to solve the above-mentioned subject, a stator blade concerning one mode of the present invention is arranged on the outside of the inner shroud so that it may be opposite to the inner shroud and the inner shroud which were constituted by metal material, and is constituted by metal material. An outer shroud, a wing extending in a direction from the inner shroud toward the outer shroud, an inner plate portion disposed along an outer surface of the inner shroud and connected to one end of the wing, and the outer shroud A vane body having an outer plate portion disposed along the inner surface of the blade and connected to the other end of the wing, and made of a ceramic base composite material, and in a direction from the inner shroud toward the outer shroud A fastening member disposed through the vane main body, for fastening the outer shroud, the vane main body, and the inner shroud; Between one end of the fastening member located inside the plane and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud and the outer shroud And a spring member interposed between at least one of the outer surface and the outer surface.

  According to the present invention, in the direction from the inner shroud toward the outer shroud, the outer shroud, the vane body, a fastening member for fastening the inner shroud, and one end of the fastening member located inside the inner surface of the inner shroud A spring member interposed between the inner surface of the inner shroud and at least one of the other end of the fastening member located outside the outer surface of the outer shroud and the outer surface of the outer shroud; The thermal expansion can be absorbed by the spring member contracting when the metallic material and the ceramic base composite material having different thermal expansion coefficients thermally expand. Thereby, the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite can be absorbed.

In addition, by having the above-described fastening member, when the outer shroud, the vane main body, and the inner shroud are thermally expanded, the vane main body, the inner shroud, and the outer shroud can be displaced only in the direction along the fastening member. It becomes. Thereby, at the time of thermal expansion, it is possible to suppress the inclination of the stator vane main body with respect to the fastening member, so that the posture of the stator vane main body can be stabilized.
That is, according to the present invention, it is possible to absorb the difference in coefficient of thermal expansion between the ceramic base composite material and the metal material after stabilizing the attitude of the vane main body.

  In the stator blade according to one aspect of the present invention, the fastening member includes a bolt including a shaft portion passing through the outer shroud, the stator vane body, and the inner shroud, and a nut attached to the bolt. And the outer shroud has a first protrusion including a through hole into which the shaft of the bolt is inserted, and the inner shroud protrudes in the direction toward the inner shroud. The projection may have a second projection including a through hole which protrudes in a direction toward the first projection and engages with the first projection and into which the shaft of the bolt is inserted.

By having the first and second protrusions configured in this way, the outer shroud can be easily positioned with respect to the inner shroud, and the structure including the first and second protrusions can be reinforced. It can function as a member.
Further, by arranging the shaft portion of the bolt in the through holes formed in the first and second projecting portions, positioning of the shaft portion can be easily performed.

  In the stator blade according to one aspect of the present invention, the fastening member may be a first fastening member housed in the first and second protrusions, and an outer side of the first and second protrusions. And a second fastening member disposed on the

  Thus, by having two fastening members (first and second fastening members), the attitude of the vane main body can be further stabilized.

  In the stator blade according to one aspect of the present invention, the stator blade body has an inner plate portion connected to one end of the blade, and the inner shroud is the inner plate portion And a plurality of first convex portions for dividing the flow path of the cooling air by projecting toward the inner plate portion side from the outer surface of the plate portion opposed to the inner plate portion. The end portion of the inner plate portion disposed on the trailing edge side of the wing may be bent and disposed so as to contact the inner surface of the plate portion.

In this manner, the end of the inner shroud disposed on the trailing edge side of the wing is bent to be in contact with the inner surface of the plate so that the warp of the end of the inner shroud heated by the high temperature combustion gas is generated. It is possible to suppress the formation of a gap between the end of the inner shroud and the end of the inner plate by (warpage of the end in a direction away from the inner plate).
As a result, it is possible to suppress the leakage of the cooling air flowing through the flow path formed between the inner shroud and the inner plate portion, so that it is possible to suppress a decrease in the cooling efficiency.

  In the stator blade according to one aspect of the present invention, the stator blade body has an outer plate portion connected to the other end of the blade, and the outer shroud is the outer plate portion There is a plate portion facing the plurality, and a plurality of second convex portions defining a flow path through which the cooling air is allowed to pass by projecting from the inner surface of the plate portion facing the outer side plate portion toward the outer side plate portion. The end portion of the outer side plate portion disposed on the trailing edge side of the wing may be bent and arranged to be in contact with the outer surface of the plate portion.

Thus, by bending the end of the outer side plate portion disposed on the trailing edge side of the wing so as to be in contact with the outer surface of the plate portion, the warpage of the end portion of the outer shroud heated by the high temperature combustion gas It is possible to suppress the formation of a gap between the end of the outer shroud and the end of the outer plate by (warpage of the end in a direction away from the outer plate).
As a result, it is possible to suppress the leakage of the cooling air flowing through the flow path formed between the outer shroud and the outer plate portion, and therefore, it is possible to suppress a decrease in the cooling efficiency.

  Further, in the stator blade according to one aspect of the present invention, the stator blade further includes an insert disposed inside the blade and guiding the cooling air to the inside of the blade, and the blade, the inner plate portion, and the outer plate portion The blade or the inner plate portion and the outer plate portion are separately provided with a recess, and the other is accommodated in the recess and contacts the recess when the vane main body thermally expands. In the state where the stator main body is not thermally expanded, a gap may be formed between the recess and the housing portion.

  With such a configuration, when the stator main body is thermally expanded by being heated by the combustion gas, the wing, the inner side plate portion, and the outer side plate portion are thermally expanded to bring the concave portion and the convex portion into contact with each other. Is possible. Thereby, it can suppress that cooling air leaks out from the boundary part of a recessed part and a convex part.

  Also, in a state where the vane main body is not thermally expanded, by forming a gap between the wing and the inner and outer plate portions, the pressure at the contact portion between the wing and the inner and outer plate portions can be determined. Since the size can be reduced, it is possible to suppress the application of a strong force to the wing, the inner side plate portion, and the outer side plate portion.

  Further, in the stator blade according to one aspect of the present invention, the stator blade further includes an insert disposed inside the blade and guiding the cooling air to the inside of the blade, and the blade, the inner plate portion, and the outer plate portion A first reverse tapered surface is provided at an end of the blade located on the inner plate side and a first taper is provided on an end of the wing located on the outer plate side A second tapered surface in contact with the first reverse tapered surface when the vane main body thermally expands, in a portion facing the first reverse tapered surface of the inner plate portion. Providing a second reverse tapered surface in contact with the first tapered surface when the vane main body thermally expands, in a portion of the outer side plate portion facing the first tapered surface; In a state where the vane main body is not thermally expanded, the first reverse tapered surface and the second tapered surface During, and the between the first tapered surface and the second reverse tapered surfaces may be gaps respectively formed.

  With such a configuration, when the combustion gas is supplied, the wing, the inner plate portion, and the outer plate portion are thermally expanded to form the first reverse tapered surface, the second tapered surface, and the first tapered surface. It is possible to bring the tapered surface and the second reverse tapered surface into contact with each other. Accordingly, it is possible to suppress the leakage of the cooling air from the boundary portion between the first reverse tapered surface and the second tapered surface and the boundary portion between the first tapered surface and the second reverse tapered surface.

  Also, in a state where the vane main body is not thermally expanded, by forming a gap between the wing and the inner and outer plate portions, the pressure at the contact portion between the wing and the inner and outer plate portions can be determined. Since the size can be reduced, it is possible to suppress the application of a strong force to the wing, the inner side plate portion, and the outer side plate portion.

  In order to solve the above problems, a vane according to an aspect of the present invention is disposed between an inner shroud and an outer shroud which are disposed to face each other and are made of a metal material, and between the inner shroud and the outer shroud. An oppositely extending wing in which the inner shroud and the outer shroud face each other, an inner plate portion disposed along the outer surface of the inner shroud, and an outer plate disposed along the inner surface of the outer shroud A stator body comprising a ceramic base composite material, and passing through the inside of the stator body in the opposite direction and passing through the outer shroud and the inner shroud; Fasteners for clamping the outer shroud, the stator vane body, and the inner shroud in a direction, and the inner surface of the inner shroud Between one end of the fastening member located on the inner side and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud and the outer surface of the outer shroud And the inner shroud is cooled by projecting from the plate to the side of the inner plate and the plate opposed to the inner plate. And an end portion of the inner plate portion disposed on the trailing edge side of the stationary vane main body has a plurality of first convex portions defining a flow path through which air passes. It is bend | folded and arrange | positioned at the inner surface of the said board part of the side in which the convex part is not formed.

  According to the present invention, the outer shroud, the vane main body, and the fastening member for fastening the inner shroud, and between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud By providing a spring member interposed between at least one of the other end of the fastening member located outside the outer surface of the shroud and the outer surface of the outer shroud, at startup and during steady operation, The thermal expansion can be absorbed by the spring member contracting when the metal material and the ceramic base composite material having different thermal expansion coefficients thermally expand. Thereby, the spring member can absorb the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite material.

In addition, by having the above-described fastening member, when the outer shroud, the vane main body, and the inner shroud are thermally expanded, the vane main body, the inner shroud, and the outer shroud can be displaced only in the direction along the fastening member. It becomes. Thereby, at the time of thermal expansion, it is possible to suppress the inclination of the stator vane main body with respect to the fastening member, so that the posture of the stator vane main body can be stabilized.
That is, according to the present invention, it is possible to absorb the difference in coefficient of thermal expansion between the ceramic base composite material and the metal material after stabilizing the attitude of the vane main body.

  In order to solve the above-mentioned subject, a stator blade concerning one mode of the present invention is arranged on the outside of the inner shroud so that it may be opposite to the inner shroud and the inner shroud which were constituted by metal material, and is constituted by metal material. An outer shroud, a wing extending in a direction from the inner shroud toward the outer shroud, an inner plate portion disposed along an outer surface of the inner shroud and connected to one end of the wing, and the outer shroud A vane body having an outer plate portion disposed along the inner surface of the blade and connected to the other end of the wing, and made of a ceramic base composite material, and in a direction from the inner shroud toward the outer shroud A fastening member disposed through the vane main body, for fastening the outer shroud, the vane main body, and the inner shroud; Between one end of the fastening member located inside the plane and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud and the outer shroud And a spring member interposed between at least one of the outer surface and the insert, the insert being disposed inside the wing and guiding the cooling air to the inside of the wing, the wing and the inner plate portion The outer plate portion is a separate body, and a recess is provided in one of the wing or the inner plate portion and the outer plate portion, and the other is accommodated in the recess and the vane main body is thermally expanded. In this case, a housing portion is provided in contact with the recessed portion, and a gap is formed between the recessed portion and the housing portion in a state where the stationary vane main body is not thermally expanded.

  According to the present invention, the outer shroud, the vane main body, and the fastening member for fastening the inner shroud, and between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud By providing a spring member interposed between at least one of the other end of the fastening member located outside the outer surface of the shroud and the outer surface of the outer shroud, at startup and during steady operation, The thermal expansion can be absorbed by the spring member contracting when the metal material and the ceramic base composite material having different thermal expansion coefficients thermally expand. Thereby, the spring member can absorb the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite material.

In addition, by having the above-described fastening member, when the outer shroud, the vane main body, and the inner shroud are thermally expanded, the vane main body, the inner shroud, and the outer shroud can be displaced only in the direction along the fastening member. It becomes. Thereby, at the time of thermal expansion, it is possible to suppress the inclination of the stator vane main body with respect to the fastening member, so that the posture of the stator vane main body can be stabilized.
That is, after stabilizing the attitude of the vane main body, it is possible to absorb the difference between the thermal expansion coefficients of the ceramic base composite material and the metal material.

  Moreover, when the vane main body thermally expands, it becomes possible to make a recessed part and a convex part contact, by having the wing | blade, the inner side plate part, and the outer side plate part which were set as the said structure. Accordingly, it is possible to suppress that the cooling air supplied to the inside of the vane main body leaks out from the boundary portion between the recess and the protrusion.

  Furthermore, in the state in which the vane main body is not thermally expanded, a gap is formed between the recess and the housing portion, thereby reducing the pressure applied to the portion where the wing contacts the inner and outer plate portions. It is possible to Thereby, it is possible to suppress application of a strong force to the wing, the inner side plate portion, and the outer side plate portion.

  In order to solve the above-mentioned subject, a stator blade concerning one mode of the present invention is arranged on the outside of the inner shroud so that it may be opposite to the inner shroud and the inner shroud which were constituted by metal material, and is constituted by metal material. An outer shroud, a wing extending in a direction from the inner shroud toward the outer shroud, an inner plate portion disposed along an outer surface of the inner shroud and connected to one end of the wing, and the outer shroud A vane body having an outer plate portion disposed along the inner surface of the blade and connected to the other end of the wing, and made of a ceramic base composite material, and in a direction from the inner shroud toward the outer shroud A fastening member disposed through the vane main body, for fastening the outer shroud, the vane main body, and the inner shroud; Between one end of the fastening member located inside the plane and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud and the outer shroud And a spring member interposed between at least one of the outer surface and the insert, the insert being disposed inside the wing and guiding the cooling air to the inside of the wing, the wing and the inner plate portion The outer plate portion is separate from the outer plate portion, and a first reverse tapered surface is provided at an end portion of the wing positioned on the inner plate portion side, and an end of the wing positioned on the outer plate portion side A first tapered surface is provided in the portion, and the portion of the inner plate portion facing the first reverse tapered surface contacts the first reverse tapered surface when the vane main body thermally expands. Providing a second tapered surface, wherein the outer plate portion A second reverse tapered surface which contacts the first tapered surface when the vane main body thermally expands, in a portion opposed to the tapered surface of the stator, in a state where the vane main body is not thermally expanded, A gap is formed between the first reverse tapered surface and the second tapered surface, and between the first tapered surface and the second reverse tapered surface.

  According to the present invention, the outer shroud, the vane main body, and the fastening member for fastening the inner shroud, and between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud By providing a spring member interposed between at least one of the other end of the fastening member located outside the outer surface of the shroud and the outer surface of the outer shroud, at startup and during steady operation, The thermal expansion can be absorbed by the spring member contracting when the metal material and the ceramic base composite material having different thermal expansion coefficients thermally expand. Thereby, the spring member can absorb the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite material.

In addition, by having the above-described fastening member, when the outer shroud, the vane main body, and the inner shroud are thermally expanded, the vane main body, the inner shroud, and the outer shroud can be displaced only in the direction along the fastening member. It becomes. Thereby, at the time of thermal expansion, it is possible to suppress the inclination of the stator vane main body with respect to the fastening member, so that the posture of the stator vane main body can be stabilized.
That is, after stabilizing the attitude of the vane main body, it is possible to absorb the difference between the thermal expansion coefficients of the ceramic base composite material and the metal material.

Further, by having the blade, the inner plate portion, and the outer plate portion configured as described above, it is possible to bring the first reverse tapered surface into contact with the second tapered surface when the vane main body thermally expands. As a result, the first tapered surface and the second reverse tapered surface can be brought into contact with each other.
Thereby, the cooling air supplied to the inside of the vane main body is a boundary between the first reverse taper surface and the second taper surface, and a boundary between the first taper surface and the second reverse taper surface. Can be controlled from leaking out.

  Furthermore, in the state where the vane main body is not thermally expanded, clearances are respectively provided between the first reverse tapered surface and the second tapered surface and between the first tapered surface and the second reverse tapered surface. By forming, it becomes possible to make small the pressure applied to the part which the wing | blade and the inner side plate part and the outer side plate part contacted. Thereby, it is possible to suppress application of a strong force to the wing, the inner side plate portion, and the outer side plate portion.

  In order to solve the above-mentioned subject, a stator blade group concerning one mode of the present invention is a stator blade group provided with a plurality of stator blades, and a plurality of the above-mentioned stator blades are annularly arranged, and the above-mentioned inner shroud separated In the state, they are disposed in the circumferential direction so as to be adjacent to each other, and the inner plate portions are respectively provided to the plurality of the inner shrouds disposed in the circumferential direction, and are adjacent to each other in the circumferential direction The first seal member is disposed in a space formed between the stator vanes to be fitted, and is formed of a ceramic matrix composite material, and the first seal members are two inner sides adjacent to each other in the circumferential direction. A first end portion disposed between the plate portions, and a second end portion capable of being in contact with the inner surfaces of the two inner shrouds which are adjacent to each other in a state of being opposed to and spaced apart from the first end portion; , Said first end and said A second end disposed between the first end and the second end and having a circumferential width smaller than that of the first and second ends; And a surface of the first end facing the second end can be in contact with a tapered surface formed at the end of the inner plate. The inner shroud projects cooling air from the outer surface of the plate facing the inner plate portion and the outer surface of the plate facing the inner plate portion toward the inner plate portion. And a first convex portion defining a flow passage to be passed through, and in a state where the vane main body is not thermally expanded, the first seal member, the inner shroud, and the inner plate portion. A gap is formed between the two.

  According to the present invention, by having the inner shroud, the inner plate portion, and the first seal member configured as described above, when the temperature of the inner shroud and the inner plate portion is increased by the combustion gas, the ceramic base composite material can be obtained. The inner shroud, which is made of a metallic material that is also easily thermally expanded, undergoes a large amount of thermal expansion.

At this time, the thermal expansion of the inner shroud brings the protruding surface of the first convex portion into contact with the outer surface of the inner plate portion, thereby eliminating the gap formed between the first convex portion and the inner plate portion. Contact between the outer surface of the inner shroud and the second end eliminates the gap formed between the inner shroud and the second end.
As a result, it is possible to suppress the cooling air from leaking out of the flow path formed between the inner shroud and the inner plate portion, so it is possible to suppress a decrease in the cooling efficiency.

In addition, when the inner shroud thermally expands, the distance between the second end and the inner plate increases, so that the first end and the inner plate approach each other, and eventually the tapered surface of the inner plate And the reverse taper surface of the first end contact.
Thereby, a gap is eliminated between the inner side plate portion and the first end portion, so that the sealing performance between the inner side plate portion and the first end portion at the time of starting and operation can be improved.

  In order to solve the above-mentioned subject, a stator blade group concerning one mode of the present invention is a stator blade group provided with two or more of the above-mentioned stator blades, and a plurality of the above-mentioned stator blades are annularly arranged, Are arranged in the circumferential direction so as to be adjacent to each other, and the outer plate portions are respectively provided to the outer shrouds disposed in the circumferential direction, and are adjacent to each other in the circumferential direction. A second seal member is disposed in a space formed between the vanes, and the second seal member is disposed between two of the outer plate portions in the circumferential direction adjacent to each other. A fourth end facing the third end, and spaced apart from each other so as to be in contact with the outer surfaces of the two outer shrouds disposed adjacent to each other. An end, said third end and a front It is disposed between the fourth end and connects the third end and the fourth end, and the circumferential width is greater than the width of the third and fourth ends. And a surface of the third end portion facing the fourth end portion is a reverse tapered surface formed at the end portion of the outer plate portion. The outer shroud is cooled by projecting from the inner surface of the plate facing the outer plate and the inner surface of the plate facing the outer plate toward the outer plate. And a second convex portion that defines a flow path through which air passes, and in a state in which the vane main body is not thermally expanded, the second seal member, the outer shroud, and the outer plate portion. And a gap is formed between them.

According to the present invention, by having the outer shroud, the outer plate portion, and the second seal member configured as described above, when the temperature of the outer shroud and the outer plate portion is increased by the combustion gas, the ceramic base composite material can be obtained. The outer shroud, which is made of a metallic material that is also easily thermally expanded, undergoes a large amount of thermal expansion.
At this time, the protruding surface of the second convex portion and the outer surface of the outer side plate portion are in contact with each other, thereby eliminating the gap formed between the second convex portion and the outer side plate portion. The contact with the end of 4 eliminates the gap formed between the outer shroud and the fourth end.
As a result, it is possible to suppress the cooling air from leaking from the flow path formed between the outer shroud and the outer plate portion, so that it is possible to suppress a decrease in the cooling efficiency.

In addition, the outer shroud is thermally expanded to a large extent, and the distance between the fourth end and the outer plate increases, whereby the third end and the outer plate approach each other, and the reverse tapered surface of the outer plate is eventually obtained. And the tapered surface of the third end contact.
Thereby, a gap is eliminated between the outer side plate portion and the third end portion, so that the sealing property between the outer side plate portion and the third end portion at the time of starting and operation can be improved.

  In order to solve the above-mentioned subject, a stator blade group concerning one mode of the present invention is a stator blade group provided with a plurality of stator blades arranged annularly, and the stator blade is an inner side comprised by metal material. A shroud, an outer shroud disposed outside the inner shroud opposite to the inner shroud and made of a metallic material, a wing extending in a direction from the inner shroud toward the outer shroud, an outer surface of the inner shroud And an outer plate portion disposed along an inner surface of the outer shroud and connected to the other end portion of the wing. A stator body made of a ceramic matrix composite material, and disposed through the stator body in a direction from the inner shroud toward the outer shroud, the outer shroud, the stator body, and A fastening member for fastening the inner shroud, and between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud and outside the outer surface of the outer shroud A spring member interposed in at least one of the other end of the fastening member and the outer surface of the outer shroud, the inner shrouds being adjacent to each other in a separated state Are disposed circumferentially, and the inner plate portion is provided for each of the plurality of inner shrouds disposed in the circumferential direction, and between the vanes adjacent to each other in the circumferential direction. The first seal member is disposed in the formed space and is formed of a ceramic matrix composite material, and the first seal members are adjacent to each other in the circumferential direction. A first end disposed between the two mating inner plate portions, and a first end capable of being in contact with the inner surfaces of the two inner shrouds facing each other and spaced apart from each other; 2 and between the first end and the second end to connect the first end to the second end, and have a circumferential width And a first connecting portion smaller than a width of the first and second ends, and a surface of the first end facing the second end is the inner side. The inner shroud is a plate portion facing the inner plate portion, and the inner shroud protrudes from the plate portion toward the inner plate portion side. And a first convex portion that defines a flow path through which the cooling air is allowed to pass. A clearance is formed between the first seal member, the inner shroud, and the inner plate portion.

  According to the present invention, in the direction from the inner shroud toward the outer shroud, the outer shroud, the vane body, a fastening member for fastening the inner shroud, and one end of the fastening member located inside the inner surface of the inner shroud A spring member interposed between the inner surface of the inner shroud and at least one of the other end of the fastening member located outside the outer surface of the outer shroud and the outer surface of the outer shroud; The thermal expansion can be absorbed by the spring member contracting when the metallic material and the ceramic base composite material having different thermal expansion coefficients thermally expand. Thereby, the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite can be absorbed.

  In addition, by having the above-described fastening member, when the outer shroud, the vane main body, and the inner shroud are thermally expanded, the vane main body, the inner shroud, and the outer shroud can be displaced only in the direction along the fastening member. It becomes. Thereby, at the time of thermal expansion, it is possible to suppress the inclination of the stator vane main body with respect to the fastening member, so that the posture of the stator vane main body can be stabilized.

  By having the inner shroud, the inner plate portion, and the first seal member configured as described above, when the temperature of the inner shroud and the inner plate portion is increased by the combustion gas, the metal is more easily thermally expanded than the ceramic base composite material The inner shroud made of material undergoes a large thermal expansion.

At this time, the thermal expansion of the inner shroud brings the protruding surface of the first convex portion into contact with the outer surface of the inner plate portion, thereby eliminating the gap formed between the first convex portion and the inner plate portion. Contact between the outer surface of the inner shroud and the second end eliminates the gap formed between the inner shroud and the second end.
As a result, it is possible to suppress the cooling air from leaking out of the flow path formed between the inner shroud and the inner plate portion, so it is possible to suppress a decrease in the cooling efficiency.

In addition, when the inner shroud thermally expands, the distance between the second end and the inner plate increases, so that the first end and the inner plate approach each other, and eventually the tapered surface of the inner plate And the reverse taper surface of the first end contact.
Thereby, a gap is eliminated between the inner side plate portion and the first end portion, so that the sealing performance between the inner side plate portion and the first end portion at the time of starting and operation can be improved.

  In order to solve the above-mentioned subject, a gas turbine concerning one mode of the present invention is provided with the above-mentioned stator blade and a burner which generates combustion gas supplied to the outside of the stator blade.

  According to the gas turbine configured as described above, it is possible to absorb the difference in coefficient of thermal expansion between the ceramic base composite material and the metal material after stabilizing the attitude of the vane main body.

  In order to solve the above-mentioned subject, a gas turbine concerning one mode of the present invention is provided with the above-mentioned stator blade group, and a burner which generates combustion gas supplied to the outer side of the above-mentioned stator blade.

  According to the gas turbine configured as described above, it is possible to absorb the difference in coefficient of thermal expansion between the ceramic base composite material and the metal material after stabilizing the attitude of the vane main body.

  According to the present invention, it is possible to absorb the difference in thermal expansion coefficient between the ceramic matrix composite material and the metal material while stabilizing the attitude of the stationary blade.

BRIEF DESCRIPTION OF THE DRAWINGS It is sectional drawing which shows typically schematic structure of the gas turbine which concerns on the 1st Embodiment of this invention. It is the figure which looked at a part of stator vane group shown in FIG. 1 from radial direction outer side. It is the figure which looked at the stator blade shown in FIG. It is a cross-sectional view of the _H 1 -H ₂ along the line of the stationary blade shown in FIG. It is a figure which shows typically the state which removed the stator main body from the stator blade shown in FIG. It is a figure which shows typically the state which spaced apart the inner shroud and outer shroud which comprise the stator blade shown in FIG. 2 to radial direction. It is a figure which shows typically a part of stator vane group which concerns on the 2nd Embodiment of this invention. FIG. 8 is a cross-sectional view taken along line J ₁ -J _{2 of the} structural body shown in FIG. 7, schematically showing the inner plate portion, the inner shroud, and the first seal member in a state of not being thermally expanded. It is sectional drawing which shows typically the state which the structure shown in FIG. 8 thermally expanded. It is sectional drawing of the 2nd seal member arrange | positioned between the adjacent two stator vanes in the circumferential direction, the outer side plate part arrange | positioned on both sides of the 2nd seal member, and an outer shroud. It is the figure which looked at the structure shown in FIG. It is a figure showing a schematic structure of a stator blade concerning a 3rd embodiment of the present invention. It is a cross-sectional view of the _M 1 -M ₂ along the line of the stationary blade shown in FIG. 12. It is a cross-sectional view of _N 1 -N ₂ along the line of the structure shown in FIG. 13. FIG. 15 is a cross-sectional view of a portion of the outer plate portion and the outer shroud facing the N ₁ -N ₂ line shown in FIG. It is a figure showing a schematic structure of a stator blade concerning a 4th embodiment of the present invention. It is a sectional view for explaining an engagement part of an inner side board part corresponding to fields P and Q shown in Drawing 16, wings, and an outer side board part among stator blades of a 4th embodiment of the present invention, and an inner side It is a figure which shows typically the state which the board part, the wing | blade, and the outer side board part have not thermally expanded. FIG. 18 is a view schematically showing a state in which the structure shown in FIG. 17 is thermally expanded. It is a sectional view for explaining an engagement part of an inner side board part, a wing, and an outer side board part among stator blades concerning a modification of a 4th embodiment of the present invention, and an inner side board part, a wing, and an outer side. It is a figure which shows typically the state which the board part has not thermally expanded. It is a figure which shows typically the state which the structure shown in FIG. 19 thermally expanded.

  Hereinafter, embodiments to which the present invention is applied will be described in detail with reference to the drawings.

First Embodiment
The schematic configuration of the gas turbine 10 according to the first embodiment will be described with reference to FIG. In FIG. 1, A is open air (hereinafter referred to as “open air A”), Acom is compressed air (hereinafter referred to as “compressed air Acom”), Ar is an axis (hereinafter referred to as “axis Ar”), and Da is an axial direction Hereinafter, "the axial direction Da" is shown respectively.
In FIG. 1, Dau is an axial upstream side (hereinafter referred to as “axial upstream Dau”) that is one side of the axial direction Da, and Dad is an axial downstream side that is the other side of the axial direction Da (hereinafter, “Axial downstream side Dad” and Dc indicate circumferential directions (hereinafter referred to as “circumferential direction Dc”).

  Further, in FIG. 1, Dr represents a radial direction with respect to the axis Ar (hereinafter, referred to as “radial direction Dr”), and Dro represents a radially outer side which is a side away from the axis Ar in the radial direction Dr (hereinafter referred to as “radial outer side Dro” And Dri indicate radial inner sides (hereinafter referred to as “radial inner side Dri”) which are sides closer to the axis Ar in the radial direction Dr.

  In the first embodiment, the radial direction Dr is also the direction in which the inner shroud 65 and the outer shroud 67 face each other. Further, in the first embodiment, the inner surface of the component constituting the turbine 13 refers to a surface disposed on the rotor shaft 47 side, and the outer surface is a surface disposed on the turbine casing 41 side. It means that.

  The gas turbine 10 includes a compressor 11, a turbine 13, an intermediate casing 15, a combustor 17, and an exhaust chamber 19.

  The compressor 11 compresses the outside air A to generate a compressed air Acom. The compressor 11 has a compressor casing 21 and a compressor rotor 23.

The compressor casing 21 is cylindrical and covers the compressor rotor 23. On the upstream side of the compressor casing 21, an air intake port 21A for the compressor 11 to take in the outside air A from the outside is provided.
A plurality of stator blade groups 25 are fixed to the radially inner side Dri of the compressor casing 21. The plurality of stator blade groups 25 are arranged at intervals in the axial direction Da. The plurality of stator blade groups 25 is configured of a plurality of stator blades 29 arranged in the circumferential direction Dc with respect to the axis Ar.

The compressor rotor 23 extends in the direction of the axis Ar and rotates around the axis Ar. The compressor rotor 23 has a rotor shaft 32 and a plurality of moving blade rows 34. The rotor shaft 32 extends in the axial direction Da around the axis Ar. The plurality of moving blade arrays 34 are fixed to the outer periphery of the rotor shaft 32.
Each moving blade row 34 is disposed on the upstream side Dau in the axial direction of any one of the vane groups 25. The plurality of moving blade rows 34 are configured by a plurality of moving blades 36 arranged in line in the circumferential direction Dc.

  The turbine 13 is disposed on the axially downstream side Dad of the compressor 11. The turbine 13 has a turbine rotor 38 and a turbine casing 41.

The turbine rotor 38 extends in the direction of the axis Ar and rotates around the axis Ar.
The turbine rotor 38 has a rotor shaft 47 and a plurality of moving blade arrays 49.
The rotor shaft 47 extends in the axial direction Da around the axis Ar. The rotor shaft 47 is formed with a cooling air passage (not shown) through which the cooling air passes. The cooling air having passed through the cooling air passage is introduced into the moving blades 51 and is used to cool the moving blades 51.

  The turbine casing 41 is cylindrical and covers the turbine rotor 38. A plurality of vane groups 44 are fixed to the radially inner side Dri of the turbine casing 41. The plurality of stator blade groups 44 are arranged at intervals in the axial direction Da. Each stationary blade group 44 is configured of a plurality of stationary blades 45 arranged in the circumferential direction Dc.

  The specific configuration of the stationary blade 45 according to the first embodiment will be described later with reference to FIGS.

  The turbine casing 41 is formed with a cooling air passage through which the cooling air passes. The cooling air that has passed through the cooling air passage is introduced into the stator vanes 45 and used to cool the stator vanes 45.

  Depending on the configuration of the vane group 44, the air in the intermediate vehicle chamber 15 may be used as cooling air and supplied to the vanes 45 of the vane group 44 without passing through the cooling air passage of the compartment. is there.

  Between the radially outer side Dro of the rotor shaft 47 and the radially inner side Dri of the turbine casing 41, a combustion gas flow path 50 which is an annular space is formed. The high temperature combustion gas G generated by the combustor 17 is supplied to the combustion gas passage 50.

  The plurality of moving blade arrays 49 are fixed to the outer periphery of the rotor shaft 47. Each moving blade row 49 is disposed on the axially downstream side Dad of the stator blade group 44. Each moving blade row 49 is composed of a plurality of moving blades 51 arranged side by side in the circumferential direction Dc.

The turbine rotor 38 rotates integrally with the compressor rotor 23 about the same axis Ar. The turbine rotor 38 and the compressor rotor 23 constitute a gas turbine rotor 57.
Both ends of the gas turbine rotor 57 in the axial direction Da are supported by bearings (not shown). The rotor of the generator 61 is connected to the gas turbine rotor 57.

  The intermediate casing 15 is disposed between the compressor casing 21 and the turbine casing 41 in the axial direction Da. The compressed air Acom, which is the outside air A compressed by the compressor 11, is introduced into the intermediate vehicle compartment 15.

  The combustor 17 is fixed to the intermediate vehicle chamber 15. A fuel line 55 for supplying the fuel F to the combustor 17 is connected to the combustor 17. The fuel line 55 is provided with a fuel control valve 56 for adjusting the fuel flow rate. The combustor 17 generates a high temperature combustion gas G by burning the fuel F from the fuel supply source in the compressed air Acom.

The exhaust chamber 19 is disposed on the axially downstream side Dad of the turbine casing 41.
The compressor casing 21, the intermediate casing 15, the turbine casing 41, and the exhaust chamber 19 constitute a gas turbine casing 58 by being mutually connected.

Next, with reference to FIG. 1 to FIG. 6, the stator blades 45 constituting the stator blade group 44 housed in the turbine casing 41 will be described.
In FIG. 2, B indicates the direction in which the combustion gas flows (hereinafter referred to as the “B direction”). In FIG. 2, the same components as in the structure shown in FIG. In FIG. 3, the same components as those of the structure shown in FIG. In FIG. 4, the same components as those shown in FIGS. 2 and 3 are denoted by the same reference numerals. In FIG. 5, the same components as those of the structure shown in FIGS. In FIG. 6, the same components as those of the structure shown in FIGS.

  The vane 45 includes an inner shroud 65, an outer shroud 67, a vane body 69, inserts 71 and 73, a first fastening member 75, a second fastening member 76, and a spring member 78. .

  The inner shroud 65 is provided closer to the rotor shaft 47 than the outer shroud 67. The inner shrouds 65 are arranged at intervals in the circumferential direction Dc.

The inner shroud 65 has a shroud body 81 and a second protrusion 82.
The shroud main body 81 is a plate-like member. The shroud main body 81 is bent toward the rotor shaft 47 so that an end portion located on the upstream side Dau in the axial direction is L-shaped. A flow path (flow path 109 shown in FIG. 14) in which the cooling air flows is partitioned inside the shroud main body 81.

Through holes 65A and 65B are formed in the shroud main body 81.
The through hole 65 </ b> A is formed to penetrate a portion of the shroud main body 81 facing the central portion of the wing 86.
The shaft portion 75AB of the bolt 75A constituting the first fastening member 75 is inserted into the through hole 65A. One end of the shaft portion 75AB protrudes from the shroud main body 81 to the rotor shaft 47 side.

The through hole 65 </ b> B is formed to pass through the front edge 86 </ b> A side of the central portion of the wing 86 in the shroud main body 81.
The shaft portion 76AB of the bolt 76A constituting the second fastening member 76 is inserted into the through hole 65B. One end of the shaft portion 76AB protrudes from the shroud main body 81 to the rotor shaft 47 side.

The second protrusion 82 protrudes from the shroud main body 81 corresponding to the formation area of the through hole 65A in the direction toward the outer shroud 67 (specifically, the first protrusion 88).
The second protrusion 82 has a through hole 82A and an insertion space 82B.
The through hole 82A communicates with the through hole 65A. The shaft portion 75AB of the bolt 75A is inserted into the through hole 82A.

The insertion space 82B is formed on the outer shroud 67 side and communicates with the through hole 82A. The insertion space 82B is larger in diameter than the through hole 82A.
The inner shroud 65 configured as described above is configured of a metal material.

  The outer shroud 67 is provided outside the inner shroud 65 in a state of being separated from the inner shroud 65 in the radial direction Dr. The outer shroud 67 faces the inner shroud 65 in the radial direction Dr.

The outer shroud 67 has a shroud body 87 and a first projection 88.
The shroud body 87 is a plate-like member. The shroud body 87 is bent toward the rotor shaft 47 so that an end portion located on the upstream side Dau in the axial direction is L-shaped. Inside the shroud main body 87, a flow path (flow path 115 shown in FIG. 15 described later) through which the cooling air flows is partitioned.

Through holes 67A and 67B are formed in the shroud body 87.
The through hole 67 </ b> A is formed to penetrate a portion of the shroud main body 87 that faces the central portion of the wing 86. The shaft portion 75AB of the bolt 75A that constitutes the first fastening member 75 is inserted into the through hole 67A.

  The through hole 67 </ b> B is formed to penetrate the front edge 86 </ b> A side of the central portion of the wing 86 in the shroud main body 87. The shaft portion 76AB of the bolt 76A constituting the second fastening member 76 is inserted into the through hole 67B.

The first protrusion 88 protrudes from the shroud body 87 corresponding to the formation area of the through hole 67A in the direction toward the second protrusion 82 of the inner shroud 65.
The first protrusion 88 has a through hole 88A and an engaging portion 88B. The through hole 88A communicates with the through hole 67A. The shaft portion 75AB of the bolt 75A is inserted into the through hole 88A.
The engagement portion 88 </ b> B is inserted into an insertion space 82 </ b> B formed at the end of the second protrusion 82. Thereby, the first projection 88 is engaged with the second projection 82.

  By having the first protrusion 88 constituting the outer shroud 67 described above, and the second protrusion 82 constituting the inner shroud 65 and engaged with the first protrusion 88, the inner shroud 65 can be obtained. It is possible to easily position the outer shroud 67 with respect to the above, and to allow the structure composed of the first protrusion 88 and the second protrusion 82 to function as a reinforcing member.

  Further, by arranging the shaft portion 75AB of the bolt 75A in the through holes 82A and 88A formed in the first projecting portion 88 and the second projecting portion 82, positioning of the shaft portion 75AB can be easily performed.

The first fastening member 75 has a bolt 75A and a nut 75B.
The bolt 75A has a head 75AA and a shaft 75AB. The head 75AA is provided at the other end of the shaft 75AB. The head 75 AA is disposed on the outer surface side of the shroud main body 87 (the outer surface of the outer shroud 67).

The shaft portion 75AB is provided with a through hole 67A, a through hole 88A, an insertion space 82B, a through hole 82A and a through hole 65A from the outer surface side of the shroud main body 87 via a plurality of spring members 78 arranged on the outer surface of the shroud main body 87. It is inserted in order.
Thus, the shaft portion 75AB penetrates the outer shroud 67, the vane main body 69, and the inner shroud 65 in the radial direction Dr, and a portion thereof is inside the first protrusion 88 and the second protrusion 82. Is located in

  One end (the end opposite to the side on which the head 75AA is provided) of the shaft 75AB protrudes from the inner surface of the shroud main body 81 (the inner surface of the inner shroud 65) toward the rotor shaft 47.

The nut 75 </ b> B is tightened to one end of the shaft portion 75 </ b> AB protruding from the inner surface of the shroud main body 81 via a plurality of spring members 78 disposed on the inner surface of the shroud main body 81.
The first fastening member 75 configured as described above clamps the outer shroud 67, the vane main body 69, and the inner shroud 65 in the radial direction Dr.

The second fastening member 76 has a bolt 76A and a nut 76B.
The bolt 76A has a head 76AA and a shaft 76AB. The head 76AA is provided at the other end of the shaft 76AB. The head 76AA is disposed on the outer surface side of the shroud body 87.

  The shaft portion 76AB is inserted in the order of the through hole 67B, the vane main body 69, and the through hole 65B from the outer surface side of the shroud main body 87 via a plurality of spring members 78 disposed on the outer surface of the shroud main body 87.

Thus, the shaft portion 76AB passes through the vane main body 69 and the outer shroud 67 and the inner shroud 65 in the radial direction Dr.
One end (the end opposite to the side on which the head 76AA is provided) of the shaft 76AB protrudes from the inner surface of the shroud main body 81 toward the rotor shaft 47.

The nut 76 </ b> B is tightened to one end of the shaft portion 76 </ b> AB protruding from the inner surface of the shroud main body 81 via a plurality of spring members 78 disposed on the inner surface of the shroud main body 81.
The second fastening member 76 configured as described above clamps the outer shroud 67, the vane main body 69, and the inner shroud 65 in the radial direction Dr.

  By having two fastening members (first and second fastening members 75 and 76) configured as described above, the attitude of the vane main body 69 that thermally expands compared to the case where only one fastening member is provided. Can be further stabilized.

  A plurality of spring members 78 are disposed between the heads 75AA and 76AA and the shroud main body 87, and between the nuts 75B and 76B and the shroud main body 81, respectively.

  The spring member 78 is extended when the inner shroud 65, the outer shroud 67, and the vane main body 69 are not thermally expanded (in other words, the high temperature combustion gas is not supplied to the combustion gas passage 50). In the state.

Under this condition, when the inner shroud 65 and the outer shroud 67 made of metal material and the vane main body 69 made of the ceramic matrix composite expand, they have different coefficients of thermal expansion. The difference can be absorbed.
As the spring member 78, for example, a disc spring or a coil spring can be used.

  According to the vane 45 of the first embodiment, the first and second fastening members 75 and 76 described above and the first and second fastening members 75 and 76 located inside the inner surface of the inner shroud 65 are provided. Between the other end of the first and second fastening members 75 and 76 located outside the outer surface of the outer shroud 67, and the outer surface of the outer shroud 67, And the spring member 78 is interposed between the metal members and the ceramic matrix composite material having different thermal expansion coefficients so that the spring member 78 can be contracted when the thermal expansion is absorbed. Become. Thereby, the difference in thermal expansion coefficient between the metal material and the ceramic matrix composite can be absorbed.

In addition, when the outer shroud 67, the vane main body 69, and the inner shroud 65 are thermally expanded by having the first and second fastening members 75 and 76 described above, the first and second fastening members 75 and 76 can be used. It is possible to displace the vane main body 69, the inner shroud 65, and the outer shroud 67 only in the direction along.
Thus, the inclination of the vane main body 69 with respect to the first and second fastening members 75 and 76 can be suppressed at the time of thermal expansion, so that the posture of the vane main body 69 can be stabilized.
That is, after the attitude of the vane main body 69 is stabilized, it is possible to absorb the difference between the thermal expansion coefficients of the ceramic base composite material and the metal material.

  Further, the gas turbine 10 of the first embodiment provided with the stator blade 45 can obtain the same effect as the stator blade 45 of the first embodiment.

  In the first embodiment, the case where two fastening members (first and second fastening members 75 and 76) are provided has been described as an example, but the number of fastening members may be one or more. There is no limitation to two.

  Also, the spring member 78 is located between one end of the first fastening member 75 (or the second fastening member 76) located inside the inner surface of the inner shroud 65 and the inner surface of the inner shroud 65, and It may be provided on at least one of the other end of the first fastening member 75 (the second fastening member 76) located outside the outer surface of the outer shroud 67 and the outer surface of the outer shroud 67, It is not limited to the structure shown in FIG.

  Furthermore, in the first embodiment, between the end of one of the first and second fastening members 75 and 76 located inside the inner surface of the inner shroud 65 and the inner surface of the inner shroud 65, and the outer shroud 67 Taking as an example the case where a plurality of spring members 78 are respectively disposed between the other end of the first and second fastening members 75 and 76 located outside the outer surface of the outer surface and the outer surface of the outer shroud 67 Although the number of the spring members 78 may be one or more, the number of the spring members 78 may be appropriately selected as needed.

Second Embodiment
A stator vane group 100 according to a second embodiment of the present invention will be described with reference to FIGS. 7 to 11. In FIG. 7, for convenience of explanation, the outer shroud 67 shown in FIGS. 10 and 11 is not shown, and the vane main body 69 located between the outer shroud 67 and the inner shroud 65 is shown in cross section. In FIG. 7, the same components as those of the structure shown in FIGS.

  In FIG. 8, the same components as those shown in FIGS. 3 and 7 are designated by the same reference numerals. In FIG. 9, the same components as in the structure shown in FIG. In FIG. 10, the same components as those of the structure shown in FIG. In FIG. 11, the same components as in the structure shown in FIG.

  The stator blade group 100 according to the second embodiment constitutes the stator blade group 44 according to the first embodiment, and in the space formed between the stator blades 45 adjacent to each other in the circumferential direction Dc, the first and second While arranging the seal members 101 and 102, the shapes of the end portions of the inner side plate portion 83 and the outer side plate portion 85 in the circumferential direction Dc are the end portions of the inner side plate portion 83 and the outer side plate portion 85 of the first embodiment. The configuration is the same as that of the vane group 44 except that the shape is different.

  Here, before describing the shapes of the end portions of the inner plate portion 83 and the outer plate portion 85 and the configurations of the first and second seal members 101 and 102, the configurations of the inner shroud 65 and the outer shroud 67 will be sequentially described. explain.

  The inner shroud 65 has a plate portion 105 and a first convex portion 107. The plate portion 105 is disposed to face the inner plate portion 83 in a state of being separated from the inner plate portion 83. The plate portion 105 has an outer surface 105 a facing the inner plate portion 83 and an inner surface 105 b disposed on the opposite side of the outer surface 105 a. The inner surface 105 b is a surface corresponding to the inner surface of the inner shroud 65.

  The first convex portion 107 protrudes from the outer surface 105 a of the plate portion 105 to the inner plate portion 83 side. In FIGS. 8 and 9, only one first convex portion 107 disposed at the end in the circumferential direction Dc is illustrated, but the outer surface 105 a of the plate portion 105 has a plurality of first convex portions. 107 are provided. The plurality of first convex portions 107 define a flow path 109 for passing the cooling air. The plurality of first convex portions 107 have flat projecting surfaces 107 a facing the inner side plate portion 83.

  The outer shroud 67 has a plate portion 111 and a second convex portion 112. The plate portion 111 is disposed to face the outer side plate portion 85 in a state of being separated from the outer side plate portion 85. The plate portion 111 has an inner surface 111a opposed to the outer plate portion 85, and an outer surface 111b disposed on the opposite side of the inner surface 111a.

  The second convex portion 112 protrudes from the inner surface 111 a of the plate portion 105 to the outer plate portion 85 side. In FIGS. 10 and 11, only one second convex portion 112 disposed at the end in the circumferential direction Dc is illustrated, but a plurality of second convex portions are formed on the inner surface 111a of the plate portion 105. 112 are provided. The plurality of second protrusions 112 define a flow passage 109 for passing the cooling air. The plurality of second protrusions 112 have flat projecting surfaces 112 a facing the outer side plate portion 85.

Next, the shape of the end of the inner side plate portion 83 disposed in the circumferential direction Dc will be described.
The end portion of the inner side plate portion 83 is a taper inclined in a direction from the surface 83 a of the inner side plate portion 83 disposed on the wing 86 side to the surface 83 b (the surface of the inner plate portion 83 disposed on the opposite side of the surface 83 a) It has a face 83c.

Next, the shape of the end portion of the outer side plate portion 85 disposed in the circumferential direction Dc will be described.
The end of the outer side plate portion 85 is inclined in a direction from the surface 85 b of the outer side plate portion 85 disposed on the outer shroud 67 side toward the surface 85 a (the surface of the outer side plate portion 85 disposed on the opposite side of the surface 85 b) It has a reverse tapered surface 85c.

Next, the first seal member 101 will be described.
The first seal member 101 has a first end 121, a second end 122, and a first connecting portion 123.
The first end 121 is disposed between two inner plate portions 83 adjacent to each other in the circumferential direction Dc. The first end 121 has reverse tapered surfaces 121a and 121b arranged in the circumferential direction Dc.

  The reverse tapered surface 121 a is formed at the end of one of the inner plate portions 83. The reverse taper surface 121a is opposed to the second end 122 (specifically, a protrusion 122A described later) in the radial direction Dr. The shape of the reverse tapered surface 121 a is a shape that can be in contact with the tapered surface 83 c formed at the end of the one inner plate portion 83.

  The reverse tapered surface 121 b is formed at the end of the other inner plate portion 83. The reverse tapered surface 121b is opposed to the second end 122 (specifically, a protrusion 122B described later) in the radial direction Dr. The shape of the reverse tapered surface 121 b is a shape that can contact the tapered surface 83 c formed at the end of the other inner plate portion 83.

  The second end 122 is disposed on the inner surface 105 b side of the plate portion 105 so as to face the first end 121 in the circumferential direction Dc. The width of the second end 122 in the circumferential direction Dc is configured to be wider than the width of the first connecting portion 123.

  The second end portion 122 has a pair of projecting portions 122A and 122B which project from the first connecting portion 123 in the circumferential direction Dc. The protrusion 122 </ b> A has a surface 122 a in contact with the end of the inner surface 105 b of one plate 105 (the inner surface of the inner shroud 65). The protrusion 122B has a surface 122b in contact with the end of the outer surface 111b of the other plate portion 105 (the outer surface of the outer shroud 67).

The first coupling portion 123 is provided between the first end 121 and the second end 122. The first coupling portion 123 extends in the radial direction Dr.
One end of the first connecting portion 123 is connected to the first end 121, and the other end is connected to the second end 122.

Thus, the first connecting portion 123 connects the first end 121 and the second end 122. The first connecting portion 123 is configured such that the width in the circumferential direction Dc is smaller than the widths of the first and second end portions 121 and 122.
The first seal member 101 configured as described above is made of a ceramic matrix composite material that is less likely to thermally expand than a metal material.

In a state where the first seal member 101, the inner shroud 65, the vane main body 69, and the inner plate portion 83 are not thermally expanded (in other words, a state where combustion gas is not supplied to the vane main body 69) A gap is formed between the seal member 101, the inner shroud 65, and the inner plate portion 83 (see FIG. 8).
As a result, the first seal member 101, the inner shroud 65, and the inner plate portion 83 are not in contact (are separated).

  At this time, a gap 125 is formed between one tapered surface 83c and the reverse tapered surface 121a, and a gap 126 is formed between the other tapered surface 83c and the reverse tapered surface 121b. .

  Further, a gap 128 is formed between the projecting surface 107 a and the surface 83 b. Furthermore, a gap 131 is formed between one inner surface 105b and the surface 122a, and a gap 132 is formed between the other inner surface 105b and the surface 122b.

  On the other hand, when the temperature of the first seal member 101, the inner shroud 65, and the inner plate portion 83 rises due to the supply of combustion gas to the vane main body 69, the inner shroud 65 made of metal material is made of ceramic base composite material. It thermally expands more than the inner side plate part 83 and the 1st sealing member 101 (refer FIG. 9).

  Due to this thermal expansion, the protruding surface 107 a and the surface 83 b come into contact with each other, and the gap 128 disappears. Moreover, while the one inner surface 105b and the surface 122a contact, and the other inner surface 105b and the surface 122b contact, the clearance gaps 131 and 132 are lose | eliminated.

  Further, the thermal expansion of the inner shroud 65 increases the distance between the inner plate 83 and the second end 122 in the radial direction Dr. As a result, one tapered surface 83c comes into contact with the reverse tapered surface 121a, and the other tapered surface 83c comes into contact with the reverse tapered surface 121b, and the gaps 125 and 126 disappear.

By having the inner shroud 65, the inner plate portion 83, and the first seal member 101 configured as described above, when the inner shroud 65 is thermally expanded by the supply of combustion gas to the vane main body 69, the first convex is obtained. The protruding surface 107a of the portion 107 and the surface 83b of the inner plate portion 83 (the inner surface of the inner plate portion 83) are in contact with each other.
As a result, it is possible to suppress the cooling air from leaking from the flow path 109 formed between the inner shroud 65 and the inner plate portion 83, so it is possible to suppress a decrease in cooling efficiency.

  Further, when the inner shroud 65 is further thermally expanded from the state in which the protruding surface 107a of the first convex portion 107 and the surface 83a of the inner plate portion 83 are in contact and the second end 122 and the inner shroud 65 are in contact. The second end 122 is separated from the inner plate 83 in the radial direction Dr.

Then, the tapered surface 83c and the reverse tapered surfaces 121a and 121b come into contact with each other, and the gaps 125 and 126 formed between the inner plate portion 83 and the first end portion 121 disappear.
As a result, it is possible to suppress the combustion gas from leaking out through the gaps 125 and 126, so that the sealability between the inner side plate portion 83 and the first end portion 121 at the time of startup and operation is ensured. Can be improved.

Next, the second seal member 102 will be described.
The second seal member 102 has a third end 141, a fourth end 142, and a second connecting portion 143.
The third end portion 141 is disposed between two outer plate portions 85 adjacent to each other in the circumferential direction Dc. The third end portion 141 has tapered surfaces 141a and 141b arranged in the circumferential direction Dc.

  The tapered surface 141 a is formed at the end of one outer plate portion 85. The tapered surface 141 a faces the fourth end 142 (specifically, a protrusion 142 A described later) in the radial direction Dr. The shape of the tapered surface 141 a is a shape that can be in contact with the reverse tapered surface 85 c formed at the end of the one outer plate portion 85.

  The tapered surface 141 b is formed at the end of the other outer plate portion 85. The tapered surface 141 b faces the fourth end 142 (specifically, a protrusion 142 B described later) in the radial direction Dr. The tapered surface 141 b is shaped so as to be in contact with the reverse tapered surface 85 c formed at the end of the other outer plate portion 85.

  The fourth end portion 142 is disposed on the outer surface 111 b side of the plate portion 105 so as to face the third end portion 141 in the circumferential direction Dc. The width of the fourth end portion 142 in the circumferential direction Dc is configured to be wider than the width of the second connection portion 143.

  The fourth end portion 142 has a pair of projecting portions 142A and 142B which project from the second connection portion 143 in the circumferential direction Dc. The protrusion 142A has a surface 142a in contact with the end of the outer surface 111b of one plate portion 105 (the outer surface of the outer shroud 67). The protrusion 142 B has a surface 142 b in contact with the end of the outer surface 111 b (the outer surface of the outer shroud 67) of the other plate portion 105.

The second coupling portion 143 is provided between the third end 141 and the fourth end 142. The second coupling portion 143 extends in the radial direction Dr. One end of the second connecting portion 143 is connected to the third end 141, and the other end is connected to the fourth end 142.
Thus, the second connecting portion 143 connects the third end 141 and the fourth end 142. The second connection portion 143 is configured such that the width in the circumferential direction Dc is smaller than the widths of the first and second end portions 121 and 122.
The second seal member 102 configured as described above is made of a ceramic matrix composite material that is less likely to thermally expand than a metal material.

In a state where the second seal member 102, the outer shroud 67, and the outer plate portion 85 are not thermally expanded (in other words, a state where combustion gas is not supplied to the vane main body 69), A gap is formed between the outer shroud 67 and the outer plate portion 85 (see FIGS. 10 and 11).
As a result, the second seal member 102, the outer shroud 67, and the outer plate portion 85 are in a non-contacting state (spaced state).

  At this time, a gap 145 is formed between one reverse tapered surface 85c and the tapered surface 141a, and a gap 146 is formed between the other reverse tapered surface 85c and the tapered surface 141b. .

  Further, a gap 148 is formed between the projecting surface 112 a and the surface 85 b. Furthermore, a gap 151 is formed between one outer surface 111b and the surface 142a, and a gap 152 is formed between the other outer surface 111b and the surface 142b.

On the other hand, when the second seal member 102, the outer shroud 67, and the outer plate portion 85 are heated by the supply of combustion gas to the vane main body 69, the outer shroud 67 made of a metal material is made of ceramic base composite material. The thermal expansion is larger than that of the outer plate portion 85 and the second seal member 102.
Due to this thermal expansion, the protruding surface 112 a and the surface 85 b come into contact with each other, and the gap 148 disappears. Moreover, while the one outer surface 111b contacts the surface 142a and the other outer surface 111b contacts the surface 142b, the gaps 151 and 152 disappear.

  Further, as the outer shroud 67 thermally expands, the outer side plate portion 85 and the fourth end portion 142 are separated, so the distance between the outer side plate portion 85 and the fourth end portion 142 becomes large. Thereby, one reverse tapered surface 85c and the tapered surface 141a come into contact with each other, and the other reverse tapered surface 85c and the tapered surface 141b come into contact, and the gaps 145 and 146 disappear.

By having the outer shroud 67, the outer plate portion 85, and the second seal member 102 configured as described above, when the outer shroud 67 is thermally expanded by the supply of combustion gas to the vane main body 69, the second convex The protruding surface 112 a of the portion 112 and the surface 85 b of the outer side plate portion 85 (the outer surface of the outer side plate portion 85) are in contact with each other.
As a result, it is possible to suppress the cooling air from leaking from the flow path 115 formed between the outer shroud 67 and the outer plate portion 85, so it is possible to suppress a decrease in cooling efficiency.

  Further, when the outer shroud 67 is further thermally expanded from the state in which the fourth end portion 142 and the outer shroud 67 are in contact with each other while the protruding surface 112 a of the second convex portion 112 contacts the surface 85 b of the outer side plate portion 85. Since the outer plate portion 85 and the fourth end portion 142 are separated in the radial direction Dr, the distance between the outer plate portion 85 and the fourth end portion 142 is increased.

  As a result, the reverse tapered surface 85 c of the outer side plate portion 85 and the tapered surfaces 141 a and 141 b of the third end portion 141 come into contact with each other to form a gap formed between the outer side plate portion 85 and the third end portion 141. 145 and 146 disappear. Therefore, it is possible to suppress the combustion gas from leaking out through the gaps 145 and 146, so that the sealing performance between the outer side plate portion 85 and the third end portion 141 at high temperature can be improved.

According to the vane group 100 of the second embodiment, the first and second seal members 101 and 102 are provided between the vanes 45 disposed in the circumferential direction Dc, so that the inner plate portion 83 and the inner shroud 65 are provided. It is possible to prevent the cooling air flowing in the flow paths 109 and 115 from leaking from the boundary portion between the two and the boundary portion between the outer plate portion 85 and the outer shroud 67 to the outside.
In addition, during startup and operation, combustion gas is prevented from leaking from the boundary between the first end 121 and the inner plate 83 and from the boundary between the third end 141 and the outer plate 85. can do.

  In the second embodiment, although the case where both the first seal member 101 and the second seal member 102 are provided is described as an example, the first and second seal members 101 and 102 are provided. Only one of them may be provided.

Third Embodiment
A vane 160 according to a third embodiment of the present invention will be described with reference to FIGS. 12 to 15. In FIG. 12, the same components as those of the structure shown in FIG. In FIG. 13, the same components as those of the structure shown in FIG. In FIG. 14, the same components as those shown in FIGS. 2 and 8 are denoted by the same reference numerals. In FIG. 15, the same components as those shown in FIGS. 12 and 10 are designated by the same reference numerals.

  The stationary blade 160 has an end portion of the inner side plate portion 83 disposed on the rear edge 86B side of the wing 86 on the inner surface 105b of the plate portion 105 (on the side of the plate portion 105 on which the plurality of first convex portions 107 are not formed Face of the outer plate portion 85 disposed on the rear edge 86B side of the wing 86 on the outer surface 111b of the plate portion 105 (on the side where the plurality of second convex portions 112 are not formed). The configuration is the same as that of the vane 45 of the first embodiment except that the plate is bent and disposed at the surface of the plate portion 111.

According to the stator blade 160 of the third embodiment, the end portion of the inner side plate portion 83 disposed on the rear edge 86B side of the blade 86 is bent to be disposed on the inner surface 105b of the plate portion 105, so that the high temperature is caused by the combustion gas. A gap is formed between the end of the inner shroud 65 and the end of the inner plate 83 due to the warpage of the end of the inner shroud 65 (warpage of the end in the direction away from the inner plate 83). Can be suppressed.
As a result, it is possible to suppress the cooling air from leaking from the flow path 109 formed between the inner shroud 65 and the inner plate portion 83, so it is possible to suppress a decrease in cooling efficiency.

Further, by bending the end of the outer side plate portion 85 disposed on the rear edge 86B side of the wing 86 to the outer surface 111b of the plate portion 105, the warpage of the end of the outer shroud 67 made high by combustion gas is obtained. It is possible to suppress the formation of a gap between the end of the outer shroud 67 and the end of the outer plate 85 by (warpage of the end in the direction of separating from the outer plate 85).
As a result, it is possible to suppress the cooling air from leaking from the flow path 115 formed between the outer shroud 67 and the outer plate portion 85, so it is possible to suppress a decrease in the cooling efficiency.

  In the third embodiment, as an example, the case where both the end portion of the inner side plate portion 83 and the end portion of the outer side plate portion 85 are bent is described as an example, but the end portion of the inner side plate portion 83 Alternatively, only one of the end portions of the outer side plate portion 85 may be bent and disposed.

Fourth Embodiment
A vane 170 according to a fourth embodiment of the present invention will be described with reference to FIGS. In FIG. 16, P and Q indicate regions (hereinafter referred to as “region P” and “region Q”, respectively). In FIG. 16, the same components as in the structure shown in FIG. In FIG. 17, the same components as those of the structure shown in FIG. In FIG. 18, S1, S2, T1, and T2 are regions where the vane 172 and the inner plate portion 173 contact with each other due to thermal expansion of the vane main body 171 (hereinafter, “region S1”, region T1, and “ Region S2 "and" region T2 "are shown. In FIG. 18, the same components as in the structure shown in FIG.

  The stationary blade 170 is configured in the same manner as the stationary blade 45 except that a stationary blade main body 171 is provided instead of the stationary blade main body 69 configuring the stationary blade 45 of the first embodiment.

  The vane main body 171 has a wing 172, an inner plate portion 173, and an outer plate portion 174. The vane main body 171 differs from the vane main body 69 in that the wings 172, the inner plate portion 173, and the outer plate portion 174 are separated.

  The wing 172 has, of both end portions in the radial direction, a concave portion 178 disposed on the inner plate portion 173 side and a concave portion 179 disposed on the outer plate portion 174 side. Recesses 178 and 179 are recesses in which the depth direction is the radial direction Dr.

The inner plate portion 173 has a housing portion 181 housed in the recess 178. The housing portion 181 extends in the radial direction Dr. When the stator body 171 is not thermally expanded (that is, when high temperature combustion gas is not supplied to the stator body 171), the housing portion 181 is in contact with the wing 172 defining the recess 178. Not (see FIG. 17).
On the other hand, when the high temperature combustion gas is supplied to the stationary vane main body 171 and the stationary vane main body 171 thermally expands, the vanes 172 and the inner plate portion 173 contact in the regions S1 and T1.

  As a result, there is no path between the inner plate portion 173 and the wing 172 for connecting the outer side and the inner side of the vane main body 171, so the combustion gas flowing on the outer side of the vane body 171 flows to the inner side of the vane main body 171. Leakage can be suppressed, and cooling air flowing inside the vane main body 171 can be prevented from leaking out of the vane main body 171.

The outer side plate part 174 has the accommodating part 182 accommodated in the recessed part 179. As shown in FIG. The housing portion 182 extends in the radial direction Dr. When the stator main body 171 is not thermally expanded, the housing portion 182 is not in contact with the wing 172 that defines the recess 179 (see FIG. 17).
On the other hand, when the high temperature combustion gas is supplied to the stationary vane main body 171 and the stationary vane main body 171 thermally expands, the vanes 172 and the outer side plate portion 174 contact in the regions S2 and T2.

  As a result, there is no path between the outer side plate portion 174 and the wing 172 for connecting the outer side and the inner side of the vane main body 171, so the combustion gas flowing on the outer side of the vane main body 171 is Leakage can be suppressed, and cooling air flowing inside the vane main body 171 can be prevented from leaking out of the vane main body 171.

  According to the stator vane 170 of the fourth embodiment, the combustion gas flowing outside the stator vane main body 171 is the stator vane main body by having the vane 172, the inner side plate portion 173, and the outer side plate portion 174 configured as described above. Leakage to the inside of the blade 171 can be suppressed, and leakage of cooling air flowing inside the vane body 171 to the outside of the vane body 171 can be suppressed.

  In the fourth embodiment, as an example, the case where the concave portions 178 and 179 are provided in the wing 172, the housing portion 181 is provided in the inner plate portion 173, and the housing portion 182 is provided in the outer plate portion 174 is exemplified. As described above, the housing portions 181 and 182 may be provided in the wing 172, the recess 178 may be provided in the inner plate portion 173, and the recess 179 may be provided in the outer plate portion 174. Also in this case, the same effect as that of the stationary blade 170 of the fourth embodiment can be obtained.

  Alternatively, the wing 172 and the inner plate portion 173 may be separate bodies, and the wing 172 and the outer plate portion 174 may be integrated, or the wing 172 and the outer plate portion 174 may be separate bodies, the wing 172 and the inner side. You may comprise the board part 173 integrally.

  Next, with reference to FIGS. 19 and 20, a vane main body 190 according to a modification of the fourth embodiment of the present invention will be described. In FIG. 20, U1 is a region (hereinafter referred to as “region U1”) where the vanes 191 and the inner plate portion 192 contact when the vane main body 190 thermally expands, and U2 is a thermal expansion of the vane main body 190. The area | region (henceforth "the area | region U2") which the wing | blade 191 and the outer side plate part 193 contact is each shown.

The vane main body 190 has a wing 191, an inner plate portion 192, and an outer plate portion 193. The wing 191, the inner plate portion 192, and the outer plate portion 193 are separately provided.
The wing 191 has a first reverse tapered surface 191 a disposed at an end located on the inner plate 192 side and a first tapered surface 191 b disposed at an end located on the outer plate 193 side. Have.

The inner plate portion 192 has a second tapered surface 192a in contact with the first reverse tapered surface 191a when the vane main body 190 is thermally expanded in a portion (end portion) facing the first reverse tapered surface 191a. Have.
In the state where the vane main body 190 is not thermally expanded, a gap 195 is formed between the first reverse tapered surface 191 a and the second tapered surface 192 a.

The outer side plate portion 193 has, at a portion facing the first tapered surface 191b, a second reverse tapered surface 193a that comes in contact with the first tapered surface 191b when the vane main body 190 thermally expands.
In a state where the vane main body 190 is not thermally expanded, a gap 196 is formed between the first tapered surface 191 b and the second reverse tapered surface 193 a.

  The vane main body 190 according to the modification of the fourth embodiment configured as described above can obtain the same effect as the vane 170 described in the fourth embodiment.

  Although the preferred embodiments of the present invention have been described above in detail, the present invention is not limited to such specific embodiments, and is within the scope of the present invention as described in the claims. Various modifications and changes are possible.

  DESCRIPTION OF SYMBOLS 10 ... Gas turbine, 11 ... Compressor, 13 ... Turbine, 15 ... Intermediate compartment, 17 ... Combustor, 19 ... Exhaust chamber, 21 ... Compressor compartment, 21A ... Air intake, 23 ... Compressor rotor, 25 , 44, 100 ... stationary blade group, 29, 45, 160, 170 ... stationary blade, 32, 47 ... rotor shaft, 34, 49 ... moving blade row, 36, 51 ... moving blade, 38 ... turbine rotor, 41 ... turbine Vehicle compartment, 50: combustion gas flow channel, 55: fuel line, 56: fuel control valve, 57: gas turbine rotor, 58: gas turbine casing, 61: generator, 65: inner shroud, 65A, 65B, 67A, 67B, 82A, 88A: through hole, 67: outer shroud, 69, 171, 190: stator vane body, 71, 73: insert, 75: first fastening member, 75A, 76A: bolt, 75AA, 76AA: head , 7 AB, 76 AB shaft portion, 75 B, 76 B: nut, 76: second fastening member, 78: spring member, 81, 87: shroud body, 82: second projection, 82 B: insertion space, 83, 173, 192 ... inner plate portion, 83a, 83b, 85a, 85b, 122a, 122b, 142a, 142b ... surface, 83c, 141a, 141b ... taper surface, 85, 174, 193 ... outer plate portion, 85c, 121a, 121b ... reverse Tapered surface 86, 172, 191: wing, 86A: leading edge, 86B: trailing edge, 86a: ventral side, 86b: dorsal side, 88: first protrusion, 88B: engaging portion, 91: first Space 92: second space 93: third space 101: first seal member 102: second seal member 105, 111 plate portion 105b, 111a inner surface 105a, 111b Surface 107: first convex portion 107a, 112a: protruding surface 109, 115: flow path 112: second convex portion 121: first end 122: second end 122A, 122B, 142A, 142B ... Protrusion, 123 ... 1st connection part, 125, 126, 128, 129, 131, 132, 145, 146, 148, 151, 152, 195, 196 ... Gap, 141 ... 3rd End portion 142: fourth end portion 178, 179: recessed portion 181, 182: housing portion 191a: first reverse tapered surface 191b: first tapered surface 192a: second tapered surface 193a ... second reverse tapered surface, A: outside air, Acom: compressed air, Ar: axial line, B: direction, Da: axial direction, Dau: axial direction upstream side, Dad: axial direction downstream side, Dc: circumferential direction, Dr ... radial direction, Dro ... radial direction outer side, Dri ... radially inside, F ... fuel, G ... combustion gas, P, Q, S1, S2, T1, T2, U1, U2 ... area

Claims (15)

An inner shroud made of metal material,
An outer shroud disposed on the outside of the inner shroud and made of a metallic material so as to face the inner shroud;
A wing extending in a direction from the inner shroud toward the outer shroud, an inner plate disposed along the outer surface of the inner shroud and connected to one end of the wing, and disposed along the inner surface of the outer shroud A vane body having an outer side plate portion connected to the other end of the wing and made of a ceramic base composite material;
A fastening member disposed through the stator vane body in a direction from the inner shroud toward the outer shroud and clamping the outer shroud, the stator vane body, and the inner shroud;
Between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud A spring member interposed between at least one of the outer shroud and the outer surface of the outer shroud;
Stator equipped with The fastening member includes a bolt including a shaft portion passing through the outer shroud, the vane main body, and the inner shroud, and a nut attached to the bolt.
The outer shroud has a first protrusion including a through hole which protrudes in a direction toward the inner shroud and into which a shaft portion of the bolt is inserted.
The inner shroud has a second protrusion including a through hole that protrudes in a direction toward the first protrusion and engages with the first protrusion and into which the shaft portion of the bolt is inserted. The vane according to Item 1.   The fastening member includes a first fastening member accommodated in the first and second protrusions, and a second fastening member disposed outside the first and second protrusions. The vane according to Item 2. The vane body has an inner plate connected to one end of the wing,
The inner shroud projects a plurality of cooling air flow paths by projecting toward the inner plate portion from a plate portion facing the inner plate portion and an outer surface of the plate portion facing the inner plate portion. It has 1 convex part, and
The stator blade according to any one of claims 1 to 3, wherein an end portion of the inner plate portion disposed on the rear edge side of the wing is bent to be in contact with the inner surface of the plate portion. . The stator body has an outer plate connected to the other end of the wing,
The outer shroud is divided into a plate portion facing the outer plate portion, and a plurality of flow paths which allow the cooling air to pass by projecting from the inner surface of the plate portion facing the outer plate portion toward the outer plate portion. And the second convex portion of the
The static according to any one of claims 1 to 4, wherein an end of the outer side plate portion disposed on the rear edge side of the wing is bent and disposed so as to be in contact with the outer surface of the plate portion. Wings. And an insert disposed inside the wing and directing cooling air to the inside of the wing,
The wing, the inner plate portion and the outer plate portion are separated from each other,
A recess is provided in one of the wing or the inner plate portion and the outer plate portion, and an accommodating portion which is accommodated in the recess in the other and which contacts the recess when the vane main body thermally expands is provided.
The stator blade according to any one of claims 1 to 5, wherein a gap is formed between the recess and the housing portion in a state where the stator main body is not thermally expanded. And an insert disposed inside the wing and directing cooling air to the inside of the wing,
The wing, the inner plate portion and the outer plate portion are separated from each other,
A first reverse tapered surface is provided at an end of the wing located on the inner plate side, and a first tapered surface is provided at an end of the wing located on the outer side plate,
In the portion of the inner side plate portion facing the first reverse tapered surface, a second tapered surface is provided which comes into contact with the first reverse tapered surface when the vane main body thermally expands.
In the portion of the outer side plate portion facing the first tapered surface, a second reverse tapered surface is provided which comes into contact with the first tapered surface when the vane main body thermally expands.
In a state where the vane main body is not thermally expanded, between the first reverse tapered surface and the second tapered surface, and between the first tapered surface and the second reverse tapered surface The vane according to any one of claims 1 to 6, wherein a gap is formed in each of the two. An inner shroud made of metal material,
An outer shroud disposed on the outside of the inner shroud and made of a metallic material so as to face the inner shroud;
A wing extending in a direction from the inner shroud toward the outer shroud, an inner plate disposed along the outer surface of the inner shroud and connected to one end of the wing, and disposed along the inner surface of the outer shroud A vane body having an outer side plate portion connected to the other end of the wing and made of a ceramic base composite material;
A fastening member disposed through the stator vane body in a direction from the inner shroud toward the outer shroud and clamping the outer shroud, the stator vane body, and the inner shroud;
Between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud A spring member interposed between at least one of the outer shroud and the outer surface of the outer shroud;
Equipped with
The inner shroud projects a plurality of cooling air flow paths by projecting toward the inner plate portion from a plate portion facing the inner plate portion and an outer surface of the plate portion facing the inner plate portion. It has 1 convex part, and
An end portion of the inner side plate portion disposed on the rear edge side of the wing is bent so as to be in contact with an inner surface of the plate portion. An inner shroud made of metal material,
An outer shroud disposed on the outside of the inner shroud and made of a metallic material so as to face the inner shroud;
A wing extending in a direction from the inner shroud toward the outer shroud, an inner plate disposed along the outer surface of the inner shroud and connected to one end of the wing, and disposed along the inner surface of the outer shroud A vane body having an outer side plate portion connected to the other end of the wing and made of a ceramic base composite material;
A fastening member disposed through the stator vane body in a direction from the inner shroud toward the outer shroud and clamping the outer shroud, the stator vane body, and the inner shroud;
Between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud A spring member interposed between at least one of the outer shroud and the outer surface of the outer shroud;
Equipped with
And an insert disposed inside the wing and directing cooling air to the inside of the wing,
The wing, the inner plate portion and the outer plate portion are separated from each other,
A recess is provided in one of the wing or the inner plate portion and the outer plate portion, and an accommodating portion which is accommodated in the recess in the other and which contacts the recess when the vane main body thermally expands is provided.
The stator blade in which the crevice is formed between the crevice and the seat part in the state where the stator blade body is not thermally expanded. An inner shroud made of metal material,
An outer shroud disposed on the outside of the inner shroud and made of a metallic material so as to face the inner shroud;
A wing extending in a direction from the inner shroud toward the outer shroud, an inner plate disposed along the outer surface of the inner shroud and connected to one end of the wing, and disposed along the inner surface of the outer shroud A vane body having an outer side plate portion connected to the other end of the wing and made of a ceramic base composite material;
A fastening member disposed through the stator vane body in a direction from the inner shroud toward the outer shroud and clamping the outer shroud, the stator vane body, and the inner shroud;
Between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud A spring member interposed between at least one of the outer shroud and the outer surface of the outer shroud;
Equipped with
And an insert disposed inside the wing and directing cooling air to the inside of the wing,
The wing, the inner plate portion and the outer plate portion are separated from each other,
A first reverse tapered surface is provided at an end of the wing located on the inner plate side, and a first tapered surface is provided at an end of the wing located on the outer side plate,
In the portion of the inner side plate portion facing the first reverse tapered surface, a second tapered surface is provided which comes into contact with the first reverse tapered surface when the vane main body thermally expands.
In the portion of the outer side plate portion facing the first tapered surface, a second reverse tapered surface is provided which comes into contact with the first tapered surface when the vane main body thermally expands.
In a state where the vane main body is not thermally expanded, between the first reverse tapered surface and the second tapered surface, and between the first tapered surface and the second reverse tapered surface Are the vanes in which each gap is formed. A stator blade group including a plurality of the stator blades according to any one of claims 1 to 3, wherein the plurality of stator blades are annularly arranged,
The inner shrouds are circumferentially arranged adjacent to one another in a spaced apart condition,
The inner plate portion is provided to each of the plurality of inner shrouds arranged in the circumferential direction,
The first seal member is disposed in a space formed between the stator vanes adjacent to each other in the circumferential direction, and is formed of a ceramic base composite material.
The first seal member faces a first end portion disposed between the two inner plate portions adjacent to each other in the circumferential direction and the first end portion, and is separated from each other. Disposed between the first end and the second end, the second end capable of being in contact with the inner surfaces of the two adjacent inner shrouds, and the first end and the second end; And a first connecting portion having a circumferential width smaller than the widths of the first and second ends.
Of the first end, a surface facing the second end is a reverse tapered surface capable of being in contact with the tapered surface formed at the end of the inner plate portion,
The inner shroud divides a flow passage for passing cooling air by projecting from the outer surface of the plate portion facing the inner plate portion to the inner plate portion side from the outer surface of the plate portion facing the inner plate portion. It has 1 convex part, and
A stator vane group in which a gap is formed between the first seal member, the inner shroud, and the inner plate portion in a state where the stator body is not thermally expanded. A stator blade group including a plurality of the stator blades according to any one of claims 1 to 3, wherein the plurality of stator blades are annularly arranged,
The outer shrouds are circumferentially arranged adjacent to one another, spaced apart,
The outer plate portion is provided to each of the outer shrouds disposed in the circumferential direction,
And a second seal member disposed in a space formed between the adjacent stator vanes in the circumferential direction.
The second seal member faces and is separated from a third end portion disposed between two of the inner outer plate portions adjacent to each other in the circumferential direction and is separated from each other Are disposed between the third end and the fourth end, the fourth end facing and capable of contacting the outer surfaces of the two outer shrouds disposed adjacent to each other. And connecting the third end and the fourth end, and having a second connecting portion whose width in the circumferential direction is smaller than the width of the third and fourth ends. Yes,
Of the third end, the surface facing the fourth end is a tapered surface capable of contacting an inverse tapered surface formed at the end of the outer plate,
The outer shroud divides a flow passage through which cooling air is allowed to pass by projecting from the inner surface of the plate portion facing the outer plate portion to the outer plate portion side from the inner surface of the plate portion facing the outer plate portion. It has 2 convex parts, and
A stator vane group in which gaps are respectively formed between the second seal member, the outer shroud, and the outer plate portion in a state where the stator body is not thermally expanded. A vane group comprising a plurality of vanes arranged in an annular manner,
The vane is an inner shroud made of a metallic material;
An outer shroud disposed on the outside of the inner shroud and made of a metallic material so as to face the inner shroud;
A wing extending in a direction from the inner shroud toward the outer shroud, an inner plate disposed along the outer surface of the inner shroud and connected to one end of the wing, and disposed along the inner surface of the outer shroud A vane body having an outer side plate portion connected to the other end of the wing and made of a ceramic base composite material;
A fastening member disposed through the stator vane body in a direction from the inner shroud toward the outer shroud and clamping the outer shroud, the stator vane body, and the inner shroud;
Between one end of the fastening member located inside the inner surface of the inner shroud and the inner surface of the inner shroud, and the other end of the fastening member located outside the outer surface of the outer shroud A spring member interposed between at least one of the outer shroud and the outer surface of the outer shroud;
And have
The inner shrouds are circumferentially arranged adjacent to one another in a spaced apart condition,
The inner plate portion is provided to each of the plurality of inner shrouds arranged in the circumferential direction,
The first seal member is disposed in a space formed between the stator vanes adjacent to each other in the circumferential direction, and is formed of a ceramic base composite material.
The first seal member faces a first end portion disposed between the two inner plate portions adjacent to each other in the circumferential direction and the first end portion, and is separated from each other. Disposed between the first end and the second end, the second end capable of being in contact with the inner surfaces of the two adjacent inner shrouds, and the first end and the second end; And a first connecting portion having a circumferential width smaller than the widths of the first and second ends.
Of the first end, a surface facing the second end is a reverse tapered surface capable of being in contact with the tapered surface formed at the end of the inner plate portion,
The inner shroud has a plate portion opposed to the inner plate portion, and a first convex portion defining a flow path for passing cooling air by projecting from the plate portion to the inner plate portion side. Yes,
A stator vane group in which a gap is formed between the first seal member, the inner shroud, and the inner plate portion in a state where the stator body is not thermally expanded. The vane according to any one of claims 1 to 10,
A combustor for generating a combustion gas to be supplied to the outside of the stationary blade;
A gas turbine equipped with A vane group according to claim 11 or 12;
A combustor for generating a combustion gas to be supplied to the outside of the stationary blade;
A gas turbine equipped with

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