Air intake for gas turbine engine
US10794280B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 8, 2018 |
| Grant date | Oct 6, 2020 |
| Priority date | — |
| Expiry date | Apr 5, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.