Gas turbine engine compressor impeller cooling air sinks
US10830144B2 · kind B2 · utility
7Cited by
51References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 8, 2016 |
| Grant date | Nov 10, 2020 |
| Priority date | — |
| Expiry date | Jan 15, 2038 |
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 devices, systems, and methods for providing bleed air from the compressor impeller to the turbine for cooling and/or other use. The bleed air may include compressor cooling air that is routed through the diffuser and external to an outer bypass duct and/or internally to a forward wheel cavity of the turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.