Patent ID: 6092989
Filing Date: 2000-07-25
Classification: C22C,F01D,Y02E,Y10S

Abstract:
A high-temperature gas turbine including a compressor for compressing an air, and a turbine coupled to the compressor and rotated by a combustion gas, whereinthe compressor has a rotor including a plurality of rotor parts, and blades for a plurality of stages implanted in the rotor parts, the rotor part in which the blades for the last stage are implanted is made of a Ni--Cr--Mo--V low alloy steel, and the Ni--Cr--Mo--V low alloy steel has substantially an entire bainite microstructure comprising, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35% and the balance being substantially Fe.