Abstract: A turbine wheel is provided with a groove having a bottom surface and a pair of side wall surfaces. The turbine wheel includes: a balance weight that is arranged in the groove, is insertable from any circumferential position of the opening of the groove, and has a through-hole opened toward one of the pair of side wall surfaces; and a retaining member that contacts the one of the pair of side wall surfaces in a state of being inserted in the through-hole of the balance weight, to thereby cause the balance weight to abut against the other one of the pair of side wall surfaces and be retained in the groove. The groove has engagement recesses provided at intervals in a circumferential direction at the bottom surface or an engagement protrusion fitted to one of fitting recesses provided at intervals in the circumferential direction at the bottom surface and protruding from the bottom surface.

Abstract: Each wheel-side tab section of a turbine wheel is formed such that a bottom surface of a second groove are continuous with bottom surfaces of first grooves that are adjacent thereto. The outline shape of each wheel-side tab section when seen in an axial direction is a shape in which a portion of a particular shape is replaced with straight portions along predetermined straight lines. The particular shape includes a predetermined range of an outline shape of an attachment section as seen in the axial direction. The portion is at least on the radially inward side of the bottom surface of the second groove and is on an outer side, in the circumferential direction, of the predetermined straight lines. The predetermined straight lines pass through a central axis and points within a range along the particular shape from intersections with the bottom surface of the second groove to peaks of wheel-side hook portions adjacent, on the radially inward side, to the bottom surface of the second groove.

Abstract: Provided is a blade for an axial flow turbomachine, including: a blade profile section; an endwall having a flow path wall surface disposed at least on a hub side of the blade profile section and adapted to demarcate a part of an annular flow path of a working fluid; and a fillet disposed at the boundary between the blade profile section and the flow path wall surface. The fillet is externally shaped so as to have an arc-shaped curved surface having a radius of R as viewed in a cross-section orthogonal to the flow path wall surface and the blade surface of the blade profile section. A narrow portion existing on the flow path wall surface is configured such that the distance d between the outer edge of a projection of the blade profile section onto the flow path wall surface and the outer edge of the flow path wall surface is smaller than the maximum value of the radius R of the fillet.

Abstract: Each wheel-side tab section of a turbine wheel is formed such that a bottom surface of a second groove are continuous with bottom surfaces of first grooves that are adjacent thereto. The outline shape of each wheel-side tab section when seen in an axial direction is a shape in which a portion of a particular shape is replaced with straight portions along predetermined straight lines. The particular shape includes a predetermined range of an outline shape of an attachment section as seen in the axial direction. The portion is at least on the radially inward side of the bottom surface of the second groove and is on an outer side, in the circumferential direction, of the predetermined straight lines. The predetermined straight lines pass through a central axis and points within a range along the particular shape from intersections with the bottom surface of the second groove to peaks of wheel-side hook portions adjacent, on the radially inward side, to the bottom surface of the second groove.

Abstract: A turbine wheel is provided with a groove having a bottom surface and a pair of side wall surfaces. The turbine wheel includes: a balance weight that is arranged in the groove, is insertable from any circumferential position of the opening of the groove, and has a through-hole opened toward one of the pair of side wall surfaces; and a retaining member that contacts the one of the pair of side wall surfaces in a state of being inserted in the through-hole of the balance weight, to thereby cause the balance weight to abut against the other one of the pair of side wall surfaces and be retained in the groove. The groove has engagement recesses provided at intervals in a circumferential direction at the bottom surface or an engagement protrusion fitted to one of fitting recesses provided at intervals in the circumferential direction at the bottom surface and protruding from the bottom surface.

Abstract: Provided is a blade for an axial flow turbomachine, including: a blade profile section; an endwall having a flow path wall surface disposed at least on a hub side of the blade profile section and adapted to demarcate a part of an annular flow path of a working fluid; and a fillet disposed at the boundary between the blade profile section and the flow path wall surface. The fillet is externally shaped so as to have an arc-shaped curved surface having a radius of R as viewed in a cross-section orthogonal to the flow path wall surface and the blade surface of the blade profile section. A narrow portion existing on the flow path wall surface is configured such that the distance d between the outer edge of a projection of the blade profile section onto the flow path wall surface and the outer edge of the flow path wall surface is smaller than the maximum value of the radius R of the fillet.

Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.

Abstract: Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal. A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30. The turbine 30 includes: a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A-5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin sheet metals 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 blazed with each other, each of the corrugated thin sheet metals 71 having trapezoids alternately continued.