Gas turbine engine and method for cooling the compressor of a gas turbine engine
US8979470B2 · kind B2 · utility
6Cited by
5References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 4, 2011 |
| Grant date | Mar 17, 2015 |
| Priority date | — |
| Expiry date | Nov 8, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.