Rear hub cooling for high pressure compressor
US8459040B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 9, 2012 |
| Grant date | Jun 11, 2013 |
| Priority date | — |
| Expiry date | Jul 9, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/213
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.