Gas turbine engine buffer system
US10487734B2 · kind B2 · utility
6Cited by
39References
26Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 7, 2014 |
| Grant date | Nov 26, 2019 |
| Priority date | — |
| Expiry date | Nov 4, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.