Gas turbine intake for aircraft engine and method of inspection thereof
US11821361B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 6, 2022 |
| Grant date | Nov 21, 2023 |
| Priority date | — |
| Expiry date | Jul 6, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/127
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The gas turbine intake can have a swirl housing assembly with 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 around the central axis and between the tangential inlet and the annular outlet, the swirl housing assembly having a proximal portion defining a first portion of the swirl path, a distal portion defining a second portion of the swirl path, vanes located in the swirl housing assembly, the vanes circumferentially interspaced from one another relative the central axis and extending between the proximal portion and the distal portion, the proximal portion fastened to the distal portion via a plurality of fasteners, a gasket sandwiched between the proximal portion and the distal portion by the plurality of fasteners, the gasket extending in a radial plane relative the central axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.