Inertial particle separator for aircraft engine
US11339716B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 17, 2019 |
| Grant date | May 24, 2022 |
| Priority date | — |
| Expiry date | May 27, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldChemical engineering
- WIPO sectorChemistry
Abstract
An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.