发明名称 |
PROPULSION SYSTEM USING LARGE SCALE VORTEX GENERATORS FOR FLOW REDISTRIBUTION AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM |
摘要 |
A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined speed, the plurality of vortex generators create a plurality of vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards a portion of the engine having a higher sensitivity to changes in stagnation pressure and a low-velocity portion of the airflow to move away from the portion of the engine having the higher sensitivity to changes in stagnation pressure prior to the airflow reaching a face of the engine. |
申请公布号 |
EP2956363(A4) |
申请公布日期 |
2016.10.12 |
申请号 |
EP20140798514 |
申请日期 |
2014.02.05 |
申请人 |
GULFSTREAM AEROSPACE CORPORATION |
发明人 |
RYBALKO, MICHAEL;CONNORS, TIMOTHY;WAYMAN, TOM |
分类号 |
B64D33/02 |
主分类号 |
B64D33/02 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|