Aircraft engine, gas turbine intake therefore, and method of guiding exhaust gasses
US11891947B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 23, 2022 |
| Grant date | Feb 6, 2024 |
| Priority date | — |
| Expiry date | Jun 23, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine intake has a swirl housing having a tangential inlet fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the tangential inlet, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis, each vane having a twisted and flat body having a length extending from a leading end to a trailing end, the leading end being oriented mainly circumferentially and axially at the swirl path, the trailing end being oriented mainly axially and radially at the annular outlet, the twisted and flat body twisting between leading and trailing ends around the central axis, around a radial axis perpendicular to the central axis, and around a tangential axis perpendicular to both the central axis and the radial axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.