Aircraft engine fuel pump
US11920606B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 16, 2021 |
| Grant date | Mar 5, 2024 |
| Priority date | — |
| Expiry date | Jul 16, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/628
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.