Turbine cooling cycle
US5697208A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 2, 1995 |
| Grant date | Dec 16, 1997 |
| Priority date | — |
| Expiry date | Jun 2, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/022
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Air flow delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by directing a portion of a compressed air formed by the compressor section and located in a first fluid flow path to a second fluid flow path including a heat exchanger positioned operatively within the second flow path. The second fluid flow path results in a flow of cooled cooling air to be directed to the components of the gas turbine engine to be cooled. Thus, the components of the gas turbine engine are more efficiently cooled with a smaller quantity of air drawn from the compressor section generated air than if compressor generated air was used for cooling components of the gas turbine engine. Furthermore, more compressor generated air remains for combustion within the combustor section of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.