Abstract: Disclosed is a method of evaluating creep damage of a high temperature component which assesses the degree of creep damage of a high temperature component for use under a high temperature environment. In the method of evaluating creep damage of a high temperature component, temporal change in damage parameter of the high temperature component under an uniaxial condition and temporal change in multiaxiality of the high temperature component are obtained, and the temporal change in damage parameter is corrected by the temporal change in multiaxiality to assess the degree of creep damage of the high temperature component.

Abstract: A steam turbine blade includes a blade; a shroud attached to a tip of the blade; a blade root projecting toward the radial inner circumferential side of a turbine rotor so as to be fitted into a blade groove provided in an outer circumferential portion of a turbine rotor; and a platform disposed between the blade and the blade root. The blade root is inserted into the blade groove along the axial direction of the turbine rotor. The blade, the shroud, the blade root and the platform are integrally molded. The number of the blade roots is larger than that of the blades.

Abstract: An object of the invention is to provide a steam turbine blade having a high degree of strength reliability that reduces the stress caused by a steam force acting on a steam turbine blade during the operation of a steam turbine and increases rigidity in the circumferential and axial directions of a turbine rotor to suppress vibration of the steam turbine blade resulting from the steam force, and a steam turbine and a steam turbine power plant using the same. A steam turbine blade includes a blade; a shroud attached to a tip of the blade; a blade root projecting toward the radial inner circumferential side of a turbine rotor so as to be fitted into a blade groove provided in an outer circumferential portion of a turbine rotor; and a platform disposed between the blade and the blade root. The blade root is inserted into the blade groove along the axial direction of the turbine rotor. The blade, the shroud, the blade root and the platform are integrally molded.

Abstract: In a gas turbine, in which a compressor and a turbine are connected by means of a distant piece, the distant piece and a turbine first-stage disk 1 are connected by means of a joint portion. On the distant piece is formed a projection portion, and a spacer is held by means of a spigot portion. Thin portion is formed on an outer diameter side of the spacer, and is in contact with a fin of a turbine disk through a seal member. The turbine disk, the distant piece and the spacer define a cavity.

Abstract: A life management system for high-temperature parts of a gas turbine has one server system 3 and a plurality of client systems 5a, 5b, 5c, and 5d, all of which are connected via an Intranet. Further, the server system 3 manages a program for performing evaluation of the remaining life and the life management, and each of the client systems 5a, 5b, 5c, and 5d has a subprogram for accessing the database 4 and for entering data respectively. The clients are dedicated to different objects and share respective element data such as real component damage, design, materials, etc. which are necessary for the evaluation of the remaining life. Further, this system enables the operation of the gas turbine to be optimized based on the damage of the evaluated parts, hence contributing to operational cost reduction of the gas turbine.