Aircraft engine, gas turbine intake therefore, and method of guiding exhaust gasses
US11851202B1 · kind B1 · utility
0Cited by
18References
20Claims
0Family size
Assignee
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Key dates
| Filing date | Jun 23, 2022 |
| Grant date | Dec 26, 2023 |
| 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
The gas turbine intake can have a swirl housing having an inlet portion 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 inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.