Engine compressor, particularly aircraft jet engine compressor, fitted with an air bleed system
US9181962B2 · kind B2 · utility
1Cited by
6References
5Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Apr 5, 2011 |
| Grant date | Nov 10, 2015 |
| Priority date | — |
| Expiry date | Oct 17, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/682
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor including at least one cascade of fixed vanes, the vanes of which are mounted on a wall and between them form air-flow passages, and an air bleed system which bleeds air from the passages between two vanes, through openings made in the wall, the openings being discontinuous and each including a plurality of orifices arranged one behind the other in a direction of the air flow. An upstream orifice of each opening has a larger cross-sectional area than downstream orifices of the opening, and a number and cross section of the downstream orifices are adjusted to suit a predetermined bleed-off flow rate.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.