Gas turbine high pressure compressor fluid return and reinjection including an annular air bleeding manifold
US8959926B2 · kind B2 · utility
3Cited by
15References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 19, 2009 |
| Grant date | Feb 24, 2015 |
| Priority date | — |
| Expiry date | May 1, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.