Abstract: This stationary vane ring comprises a vane group having a plurality of vanes arrayed in the circumferential direction of an axis, a shroud segment in which the radial ends of the plurality of vanes of the vane group are connected to form an arc so as to connect the plurality of vanes in the circumferential direction, and a pressing portion that applies radial pressure to the vane group so that the vane group is pressed against the shroud segment, the pressing portion having pressure distribution such that the pressure at the circumferential center of the shroud segment is less than the pressure at both circumferential ends of the shroud segment.

Abstract: A rotor blade (22) provided in an axial flow compressor (1) including a rotating shaft, a casing (3), a diffuser portion (4) provided on a downstream side of the casing to communicate with a flow path (C) of the casing and form an annular shape and configured to define a diffuser flow path (DC) in which a cross-sectional area of the flow path expands toward the downstream side, a plurality of stator vane rows (10), and rotor blade rows (20) performing compression of a gas. A plurality of rotor blades are spaced apart from each other in a circumferential direction, and constitute a final rotor blade row (20A) positioned on a most downstream side among the rotor blade rows, and include a blade portion (25) having a larger deflection angle on a hub side and a chip side than at a central portion in a blade height direction.

Abstract: A rotor blade (22) provided in an axial flow compressor (1) including a rotating shaft, a casing (3), a diffuser portion (4) provided on a downstream side of the casing to communicate with a flow path (C) of the casing and form an annular shape and configured to define a diffuser flow path (DC) in which a cross-sectional area of the flow path expands toward the downstream side, a plurality of stator vane rows (10), and rotor blade rows (20) performing compression of a gas. A plurality of rotor blades are spaced apart from each other in a circumferential direction, and constitute a final rotor blade row (20A) positioned on a most downstream side among the rotor blade rows, and include a blade portion (25) having a larger deflection angle on a hub side and a chip side than at a central portion in a blade height direction.

Abstract: Provided are turbine blades and a gas turbine capable of damping the vibrations caused by an excitation force and facilitating mounting/disassembly. Included are a shroud portion disposed at an end portion of an airfoil portion; a holder casing that can slide relative to the shroud portion, that can also be attached thereto/detached therefrom, and that forms a space with the shroud portion therebetween; and an elastic portion that is disposed in the space, that biases the shroud portion in a direction that separates it from the holder casing, and is disposed in a movable manner relative to the shroud portion; and a pressing portion that is disposed between the elastic portion and the holder casing and that can be moved toward and away from the shroud portion.

Abstract: A stator blade ring is provided with which the possibilities of thermal deformation and a decrease in strength can be reduced, the shape flexibility can be ensured, and the compression performance can be improved. It includes stator blade segments (21) in each of which an inner shroud portion (31) and an outer shroud portion (29) divided corresponding to one stator blade (27) are provided at both ends of the stator blade (27) so as to be formed as a single part, and connecting members (23) that are formed of arch-shaped plates and are disposed on at least one of the inner shroud portions (31) and the outer shroud portions (29) of the stator blade segments (21) adjoining in a circumferential direction, on a side opposite to the stator blades (27). The stator blade segments (21) are welded to the connecting members (23) at a portion of the length thereof in the circumferential direction.

Abstract: Provided are turbine blades and a gas turbine capable of damping the vibrations caused by an excitation force and facilitating mounting/disassembly. Included are a shroud portion disposed at an end portion of an airfoil portion; a holder casing that can slide relative to the shroud portion, that can also be attached thereto/detached therefrom, and that forms a space with the shroud portion therebetween; and an elastic portion that is disposed in the space, that biases the shroud portion in a direction that separates it from the holder casing, and is disposed in a movable manner relative to the shroud portion; and a pressing portion that is disposed between the elastic portion and the holder casing and that can be moved toward and away from the shroud portion.

Abstract: A stator blade ring is provided with which the possibilities of thermal deformation and a decrease in strength can be reduced, the shape flexibility can be ensured, and the compression performance can be improved. It includes stator blade segments (21) in each of which an inner shroud portion (31) and an outer shroud portion (29) divided corresponding to one stator blade (27) are provided at both ends of the stator blade (27) so as to be formed as a single part, and connecting members (23) that are formed of arch-shaped plates and are disposed on at least one of the inner shroud portions (31) and the outer shroud portions (29) of the stator blade segments (21) adjoining in a circumferential direction, on a side opposite to the stator blades (27). The stator blade segments (21) are welded to the connecting members (23) at a portion of the length thereof in the circumferential direction.

Abstract: A gas turbine starting control system is provided, wherein starting power is increased while an inlet gas temperature of the turbine is prevented from rising during starting of the gas turbine, so that a starting motor can be reduced in size and the system cost can also be reduced. Accordingly, a gas turbine starting control system for a gas turbine in which starting power is supplied to a rotational shaft of a compressor and a turbine by using a starting motor in order to start the compressor and the turbine, comprises: a steam pipe for supplying steam to a combustor in the gas turbine; a temperature detector for detecting an inlet gas temperature of the turbine; a steam control valve provided at the steam pipe for opening and closing the steam pipe; and a valve controlling unit for controlling the opening degree of the steam control valve in response to detection signals of the inlet gas temperature from the temperature detector.