Turbine blade cooling system
US7458766B2 · kind B2 · utility
13Cited by
11References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 19, 2005 |
| Grant date | Dec 2, 2008 |
| Priority date | — |
| Expiry date | Jan 26, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/087
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Efficient cooling of a stage of gas turbine engine turbine blades (36) is achieved by first reducing the pressure of the cooling air after it has been bled from the annulus of the compressor (12) by passing it through a diffuser (30), to a pressure magnitude lower than is required at entry to the turbine blades, then re-pressurizing the bled air up to the required entry pressure, by passing it through a radial compressor defined by a cowl (44) positioned in close spaced, co-rotational relationship with the downstream face of the associated turbine disk (34).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.