Shockwave-induced boundary layer bleed
US7147426B2 · kind B2 · utility
16Cited by
25References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 7, 2004 |
| Grant date | Dec 12, 2006 |
| Priority date | — |
| Expiry date | Sep 29, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned with a foot of an oblique shock wave which originates on the leading edge of an adjacent transonic rotor blade tip.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.