Compressor for turbine and gas turbine

Details Compressor for turbine and gas turbine Compressor for turbine and gas turbine

1995-01-17

1999-05-25

Verdier, Christopher

Power plants

Combustion products used as motive fluid

Combustion products generator

60909, 4151995, 415200, 4152161, 416201R, F02C 300

Patent

active

059060964

ABSTRACT:
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 balance being substantially Fe. Blades for at least two of the stages are implanted in one of the rotor parts.

REFERENCES:
patent: 2356605 (1944-08-01), Meininghaus
patent: 2807932 (1957-10-01), Bodine, Jr.
patent: 3059901 (1962-10-01), Snow et al.
patent: 4850187 (1989-07-01), Siga et al.
Seiichi-Kawabata as Author published from Nippon-Kohkuh-Gijutsu-kyoukai on Jun. 20, 1971.
Pp. 9-27 of the "Jet Engine 3rd Edition" of Rolls-Royce Limited as editor published on Jul. 1984. edition of Nasuji-Matsuoka as Author published on Dec. 26, 1978.

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