Gas turbine nacelle ventilation manifold having a circumferential varying cross-sectional area
US10443429B2 · kind B2 · utility
2Cited by
7References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 20, 2015 |
| Grant date | Oct 15, 2019 |
| Priority date | — |
| Expiry date | Dec 8, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.