Gas turbine engine with inertial particle separator
US11536196B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 23, 2021 |
| Grant date | Dec 27, 2022 |
| Priority date | — |
| Expiry date | Jun 23, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K3/02
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.