Flow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow
Routing of full compressor flow through hollow turbine blades achieves unusually effective blade cooling and allows a significant increase in turbine inlet gas temperature and, hence, engine efficiency. The invention, ''flow integrating section'' alleviates the turbine dissipation of kinetic energy of air jets leaving the hollow blades as they enter the compressor diffuser.
- Research Organization:
- DOE Energy Related Invention Program (US)
- Sponsoring Organization:
- US Department of Energy (US)
- DOE Contract Number:
- FG01-97EE15668
- OSTI ID:
- 764563
- Report Number(s):
- Final; TRN: US200311%%276
- Resource Relation:
- Other Information: PBD: 14 Nov 1999
- Country of Publication:
- United States
- Language:
- English
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