Diffuser and associated compressor section of aircraft engine
US12012972B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 25, 2022 |
| Grant date | Jun 18, 2024 |
| Priority date | — |
| Expiry date | Jul 25, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/682
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The compressor section can have a centrifugal impeller operable to rotate around an axis, the centrifugal impeller having blades, a compressor inlet oriented towards the front and axially relative the axis, a compressor outlet oriented radially outwardly relative the axis, a diffuser having a diffusion flow path, a diffuser inlet in fluid flow communication with the compressor outlet, a diffusion flow path between a rear wall and a front wall; a collector extending circumferentially around the axis, having a collector inlet in fluid communication with the diffuser outlet, and a collector outlet; and hollow structural members protruding rearwardly from the rear wall, the hollow structural members being circumferentially interspaced from one another, each hollow structural member having a length extending radially along the rear wall and having an internal conduit extending radially inwardly along the length.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.