Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade
US5620308A · kind A · utility
9Cited by
10References
30Claims
0Family size
Assignees
Inventors
Key dates
| Filing date | Jun 7, 1995 |
| Grant date | Apr 15, 1997 |
| Priority date | — |
| Expiry date | Jun 7, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49336
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.