Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Coating – specific composition or characteristic
Patent
1995-06-07
1997-04-15
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
056203080
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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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, Florida, Jun., 1991, by A. Yoshinari, et al., pp. 1-6.
Hashida Ryozo
Iijima Katsumi
Ishida Tadami
Kano Kimio
Saito Tosiaki
Hitachi , Ltd.
Kwon John T.
Tohoku Electric Power Co. Inc.
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