|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/039.75 ; 60/909 ; 415/199.5 ; 415/200 ; 415/216.1 ; 416/201R|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 1|
A compressor for a gas turbine, comprises a rotor including a plurality of rotor parts, and blades for a plurality of stages, e.g., twelve stages, implanted in the rotor parts, the rotor part in which the blades for at least two of the stages 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 balan...
[ What is claimed is:] [1.] A high-temperature gas turbine including a compressor for compressing 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 axially arranged and blades of at least twelve stages axially arranged from an upstream end to a downstream end with respect to the movement of the air through the compressor, a radial length of the blades decreasing from the most upstream stage towards the most downstream stage, and the blades for at least two ...