Gas turbine engine with inertial particle separator
US11066996B2 · kind B2 · utility
1Cited by
30References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2018 |
| Grant date | Jul 20, 2021 |
| Priority date | — |
| Expiry date | Mar 17, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K3/02
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
There is disclosed an inertial particle separator communicating with an engine inlet. The inertial particle separator has: a main duct body; a bypass duct; and a splitter defined by an intersection of the main duct and the bypass duct. The main duct and the bypass duct having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet is also provided.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.