Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.

Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.

Abstract: A dummy ring assembly for removal is provided with a plurality of dummy rings. Each of the dummy rings has a dummy shroud section fitted into a vane ring groove of a casing into which a shroud of a vane segment is fitted, and has an arc shape whose central angle centered on a rotational axis is less than 90°. The dummy shroud sections of the plurality of dummy rings are fitted sequentially into the vane ring groove of the casing. The vane segment is removed from the casing by moving the dummy rings in a circumferential direction along the vane ring groove.

Abstract: An object of the present invention is to easily remove last-stage turbine blades. Provided is an exhaust chamber inlet-side member that has an annular shape around a rotor so as to form a part of an inner diffuser at a position facing, from the axially downstream side, base ends of last-stage turbine blades disposed on the most downstream side in the axial direction, and that is divided in the circumferential direction and provided so as to be detachable from the inner diffuser. When the exhaust chamber inlet-side member is dismounted from the inner diffuser, a space on the axially downstream side from the last-stage turbine blades is cleared.

Abstract: An insert assembly (79) includes an insert (80), a reinforcing member (85), and a retaining member (90). The insert (80) is fixed to an end of an airfoil body (51) on one side in a radial direction. The reinforcing member (85) is disposed adjacent to an end of the insert (80) on the other side in the radial direction and enhances the rigidity of the insert (80). The retaining member (90) is fixed to an end of the airfoil body (51) on the other side in the radial direction, and allows the insert (80) to be positioned relative to the airfoil body (51) in a direction orthogonal to the radial direction.

Abstract: Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.

Abstract: A hanging device of a component of a turbine includes: a bridge member that bridges upper ends of a pair of side wall plates facing each other with the turbine interposed therebetween, among plates which constitute an enclosure surrounding an outer periphery of the turbine, and has a traveling path; and a hanging tool that hangs the component of the turbine and travels along the traveling path.

Abstract: Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.

Abstract: An insert assembly (79) includes an insert (80), a reinforcing member (85), and a retaining member (90). The insert (80) is fixed to an end of an airfoil body (51) on one side in a radial direction. The reinforcing member (85) is disposed adjacent to an end of the insert (80) on the other side in the radial direction and enhances the rigidity of the insert (80). The retaining member (90) is fixed to an end of the airfoil body (51) on the other side in the radial direction, and allows the insert (80) to be positioned relative to the airfoil body (51) in a direction orthogonal to the radial direction.

Abstract: In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap.

Abstract: A measurement device for a ring-shaped assembly that measures relative positions, is provided with: a first contact section that comes into contact with a reference surface that is continuous in the circumferential direction of the ring-shaped member and is capable of sliding in the circumferential direction; a second contact section capable of pressing against an opposing surface that faces an opposite side in the radial direction from the reference surface of the ring-shaped member; a base section that supports the first contact section and the second contact section; a third contact section that comes into contact with a measurement-target part of the assembled member; a connecting section that connects the third contact section and the base section; and a measurement unit that measures a displacement of the third contact section relative to the base section.

Abstract: A transition piece assembling apparatus according to the disclosure includes a pair of rails which is provided to be in the direction parallel with an axis of a combustor transition piece, and to be spaced at intervals and in a plane perpendicular to the axis of a combustor transition piece, support portions which are connected to the combustor transition piece and support the member to be movable in longitudinal directions of the rails, a trapezoidal screw which is disposed in parallel with the axis of the combustor transition piece between the pair of rails, a female screw block which is threaded onto the trapezoidal screw, and a sliding member which is provided between the female screw block and the combustor transition piece and connects the female screw block and the combustor transition piece to be movable relative to each other in a plane perpendicular to a female screw axis.

Abstract: A hanging device of a component of a turbine includes: a bridge member that bridges upper ends of a pair of side wall plates facing each other with the turbine interposed therebetween, among plates which constitute an enclosure surrounding an outer periphery of the turbine, and has a traveling path; and a hanging tool that hangs the component of the turbine and travels along the traveling path.

Abstract: An object of the present invention is to easily remove last-stage turbine blades. Provided is an exhaust chamber inlet-side member that has an annular shape around a rotor so as to form a part of an inner diffuser at a position facing, from the axially downstream side, base ends of last-stage turbine blades disposed on the most downstream side in the axial direction, and that is divided in the circumferential direction and provided so as to be detachable from the inner diffuser. When the exhaust chamber inlet-side member is dismounted from the inner diffuser, a space on the axially downstream side from the last-stage turbine blades is cleared.

Abstract: A measurement device for a ring-shaped assembly that measures relative positions, is provided with: a first contact section that comes into contact with a reference surface that is continuous in the circumferential direction of the ring-shaped member and is capable of sliding in the circumferential direction; a second contact section capable of pressing against an opposing surface that faces an opposite side in the radial direction from the reference surface of the ring-shaped member; a base section that supports the first contact section and the second contact section; a third contact section that comes into contact with a measurement-target part of the assembled member; a connecting section that connects the third contact section and the base section; and a measurement unit that measures a displacement of the third contact section relative to the base section.

Abstract: A vane segment according to the present invention includes: an outer connection member connecting a plurality of vanes; positioning jigs for positioning end vanes located at both ends, of the plurality of vanes; and radial restriction sections which restrict the outer connection member so as to be relatively immovable to an outer side in a radial direction of a vane ring, wherein: each of the plurality of vanes has a vane main body and an outer shroud; grooves are formed in the outer shrouds; openings into each of which the positioning jig is inserted are formed in portions of the outer connection member; holes into each of which the positioning jig inserted in the opening is inserted are formed in bottoms of the grooves of the two end vanes; and at least one of the positioning jigs is an eccentric positioning jig.

Abstract: A dummy ring assembly for removal is provided with a plurality of dummy rings. Each of the dummy rings has a dummy shroud section fitted into a vane ring groove of a casing into which a shroud of a vane segment is fitted, and has an arc shape whose central angle centered on a rotational axis is less than 90°. The dummy shroud sections of the plurality of dummy rings are fitted sequentially into the vane ring groove of the casing. The vane segment is removed from the casing by moving the dummy rings in a circumferential direction along the vane ring groove.

Abstract: In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap.

Abstract: A vane segment according to the present invention includes: an outer connection member connecting a plurality of vanes; positioning jigs for positioning end vanes located at both ends, of the plurality of vanes; and radial restriction sections which restrict the outer connection member so as to be relatively immovable to an outer side in a radial direction of a vane ring, wherein: each of the plurality of vanes has a vane main body and an outer shroud; grooves are formed in the outer shrouds; openings into each of which the positioning jig is inserted are formed in portions of the outer connection member; holes into each of which the positioning jig inserted in the opening is inserted are formed in bottoms of the grooves of the two end vanes; and at least one of the positioning jigs is an eccentric positioning jig.

Abstract: A groove 50 formed in each stator ring segment piece 41 is formed to have side wall portions 50b on opposite sides inclined with respect to a bottom 50a so that a width of the groove 50 gradually decreases from an outer peripheral side toward the bottom 50a. A coupling member 42 has a sectional shape so as to have a maximum width at protrusions 42b at an intermediate portion in a thickness direction. The protrusions 42b on the opposite sides abut against or approach the side wall portions 50b of the groove 50 when the coupling member 42 is placed in the groove 50, a space 100 is formed on the side of the bottom 50a of the groove 50, and a welding groove 200 having a substantially V-shaped section is formed on the side remote from the bottom 50a of the groove 50.