Gas turbine engine with low-pressure compressor bypass
US11814969B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jul 21, 2021 |
| Grant date | Nov 14, 2023 |
| Priority date | — |
| Expiry date | Jul 21, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/335
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.