Methods and apparatus for delivering cooling air within gas turbines
US6585482B1 · kind B1 · utility
40Cited by
5References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 20, 2000 |
| Grant date | Jul 1, 2003 |
| Priority date | — |
| Expiry date | Jun 20, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor rotor assembly which directs air at a sufficient pressure and temperature to a downstream turbine for cooling. The compressor assembly includes a compressor including an impeller and a cooling circuit. The impeller includes an exit, an inlet, and a body extending therebetween. The impeller body includes a first opening positioned a distance from the impeller exit. The cooling circuit extends between the compressor and the turbine and is in flow communication with the impeller opening.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.