Gas turbine, gas turbine blade used therefor and manufacturing m

Details Gas turbine, gas turbine blade used therefor and manufacturing m Gas turbine, gas turbine blade used therefor and manufacturing m

1994-08-15

1996-02-06

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Coating, specific composition or characteristic

416223A, 29889, 298897, 1641221, F01D 514

Patent

active

054891949

ABSTRACT:
A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.

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patent: 4637448 (1987-01-01), Burke et al.
patent: 5062469 (1991-11-01), Monte et al.
patent: 5113582 (1992-05-01), Monson et al.
An Alternative Process for the Manufacture of Single Crystal Gas Turbine Blades, Sulzer Technical Review Mar. 1988, by F. Staub, et al., pp. 11-16.
Nickel Base Superalloys Single Crystal Growth Technology for Large Size Buckets in Heavy Duty Gas Turbines, Presented to the International Gas Turbine and Aeroengine Congress and Exposition, Orlando, Fla., Jun., 1991, by A. Hoshinari, et al., pp. 1-6.

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