Air intake of a turbojet engine nacelle comprising guide vanes
US11614051B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 8, 2020 |
| Grant date | Mar 28, 2023 |
| Priority date | — |
| Expiry date | Apr 8, 2040 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/0226
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Disclosed is a method for using an aircraft turbojet engine comprising an air inlet comprising a plurality of rectifier vanes, each rectifier vane being mounted such that it can move between a retracted position to assist the thrust phase and a deployed position in which the rectifier vane protrudes from the inner wall in a radially inward direction in order to rectify the reverse air flow of the inner wall to assist a thrust-reverse phase, in which method at least one rectifier vane is in the retracted position during a turbojet engine thrust phase, the method comprising, during a thrust-reverse phase of the turbojet engine, a step of moving the rectifier vane to the deployed position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.