Abstract: A turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade are disclosed. The turbine blade has a blade body having hollow shape, cavities defined inside the blade body, and a cooling passage that opens from the cavities to a rear end portion of the blade body. The cooling passage includes: a first passage on a third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage on a rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate in a radial direction of the rotor disc. The method includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction via a clearance between a platform of a blade and a region of an outer peripheral surface of the rotor disc except a blade groove for receiving the blade to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of moving the seal plate restraint part along the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes toward the second side in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of moving the seal plate restraint part along the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes toward the second side in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

Abstract: A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate in a radial direction of the rotor disc. The method includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction via a clearance between a platform of a blade and a region of an outer peripheral surface of the rotor disc except a blade groove for receiving the blade to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction.

Abstract: Provided are a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade. This turbine blade has a blade body having hollow shape, cavities provided inside the blade body, and a cooling passage that opens from the cavities to the rear end portion of the blade body. The cooling passage includes: a first passage provided on the third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage provided on the rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.

Abstract: In a variable vane drive device of an axial-flow fluid machine, a ring support unit supporting a movable ring includes: a first roller; a first support part supporting the first rollers so as to be relatively immovable with respect to a vane holding ring in a radial direction and in an axial direction; a second roller; a second support part supporting the second roller so as to be relatively movable with respect to the vane holding ring in the radial direction and pressing the second roller in the radial direction; a third roller allowing relative movement of the movable ring in the radial direction and restricting relative movement of the movable ring in the axial direction; and a third support part supporting the third roller so as to be relatively immovable with respect to the vane holding ring in the axial direction and in the radial direction.

Abstract: The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them.

Abstract: In a variable vane drive device of an axial-flow fluid machine, a ring support unit supporting a movable ring includes: a first roller; a first support part supporting the first rollers so as to be relatively immovable with respect to a vane holding ring in a radial direction and in an axial direction; a second roller; a second support part supporting the second roller so as to be relatively movable with respect to the vane holding ring in the radial direction and pressing the second roller in the radial direction; a third roller allowing relative movement of the movable ring in the radial direction and restricting relative movement of the movable ring in the axial direction; and a third support part supporting the third roller so as to be relatively immovable with respect to the vane holding ring in the axial direction and in the radial direction.

Abstract: A turbine vane of the invention includes: a plurality of outer shrouds (8a) that are provided along the turbine circumferential direction so as to be adjacent to each other and form an outer wall of a main passageway; inner shrouds (8b) that form an inner wall; a airfoil body (8c) that protrudes from a front surface of the inner shroud (8b) and defines a flow of combustion gas directed from the upstream side of the main passageway toward the downstream side thereof; and a retainer (8d) which protrudes from a rear surface of the inner shroud (8b) and extends along the turbine circumferential direction, wherein the retainer (8d) is disposed on the downstream side in relation to an intersection point (Q) between a dividing gap (K1) of the adjacent inner shrouds (8b) and a throat line (P) which connects the contact points of a minimal inscribed circle according to the blade shapes of the adjacent airfoil bodies (8c).

Abstract: The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them.

Abstract: A gas turbine includes a cooling-air transfer system. The cooing-air transfer system extracts part of air discharged from a compressor to a chamber, and transfers the part of air as cooling air to a rotor disk. The cooling-air transfer system includes a plurality of tubular nozzles independently arranged in a circle inside the chamber to surround a rotor, and a seal disk having seal-disk cooling conduits arranged in a circle around the axis of the rotor so as to receive cooling air ejected from the tubular nozzles. The cooling-air transfer system swirls the cooling air ejected from the tubular nozzles.