Turbine engine with induced pre-swirl at the compressor inlet
US4720235A · kind A · utility
25Cited by
10References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 3, 1986 |
| Grant date | Jan 19, 1988 |
| Priority date | — |
| Expiry date | Jun 3, 2006 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A jet flap construction for the compressor of an aircraft gas turbine engine provided with a bleed for bleeding air interstage of the compressor and communicating with the hollowed-out struts in the airflow path to the compressor. The hollow struts are each provided with one or more rows of discrete openings extending from the shroud to the hub on the strut to form an aligned series of jets for discharging the pressurized bleed air and forming a jet flap, thereby providing pre-swirl at the compressor inlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.