Gas turbine engine and method to cool a gas turbine engine case assembly
US10619569B2 · kind B2 · utility
1Cited by
2References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 17, 2016 |
| Grant date | Apr 14, 2020 |
| Priority date | — |
| Expiry date | May 1, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a precooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the precooler into a core compartment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.