Abstract: In a radial turbine nozzle and its assembling method, a first flange member of a first divided annular portion is inserted into a first outer side groove of a first ring. A second flange member of a second divided annular portion is inserted into a second outer side groove of a second ring. A plurality of segments are connected together in a circumferential direction, by overlapping first divided surfaces of two of the segments that are adjacent in a circumferential direction of a radial turbine, and overlapping second divided surfaces of the two of the segments.

Abstract: In a gas turbine and a method for assembling a radial turbine nozzle, the radial turbine nozzle is assembled in a manner so that a first ring and a second ring are assembled to an outer circumferential portion of a nozzle main body. The radial turbine nozzle is arranged on an outside of a first holder in a radial direction in a manner so that the inner circumferential portion of the nozzle main body can be seated on the first holder and the plurality of segments can move in the radial direction of the radial turbine.

Abstract: An axial compressor includes: a cylindrical casing; a rotor rotatably disposed in the casing; rotor blades arranged on an outer circumferential surface of the rotor around a central axis of the rotor; stationary blades arranged on an inner circumferential surface of the casing at a position adjacent to and behind the rotor blades in an axial direction, each stationary blade having a tip opposing the rotor and having a chord length defined between a leading edge and a trailing edge of the tip; and at least one bleed passage having a bleed opening that opens out in the outer circumferential surface of the rotor. The bleed opening opens at a position located ahead of a position axially spaced rearward from the leading edges of the tips of the stationary blades by one half of the chord length in such a manner that the bleed opening faces toward the tips.

Abstract: In a turbine wheel, each of seal plates is formed from an elastic plate member whose radially intermediate portion is curved projecting toward one axial end surfaces of turbine blades and a turbine disk. The seal plate includes: an assembly recessed portion recessed in a direction getting closer to the one axial end surfaces, near a radially outer end of the plate; and a disassembly protrusion projecting in a direction getting away from the one axial end surfaces, near a radially inner end of the plate. When the recessed portion is pressed for attaching the plate, a tip end of the recessed portion comes into contact with the one axial end surface of each turbine blade or the disk. The plate is accordingly inhibited from being excessively deformed. Thus, the plate is blocked from being plastically deformed, and is precluded from coming off the wheel.

Abstract: In a turbine wheel, each of seal plates is formed from an elastic plate member whose radially intermediate portion is curved projecting toward one axial end surfaces of turbine blades and a turbine disk. The seal plate includes: an assembly recessed portion recessed in a direction getting closer to the one axial end surfaces, near a radially outer end of the plate; and a disassembly protrusion projecting in a direction getting away from the one axial end surfaces, near a radially inner end of the plate. When the recessed portion is pressed for attaching the plate, a tip end of the recessed portion comes into contact with the one axial end surface of each turbine blade or the disk. The plate is accordingly inhibited from being excessively deformed.