|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/053B ; 600/390.92|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 28 인용 특허 : 7|
An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.
[ That which is claimed is:] [1.] An aircraft engine apparatus having a reduced inlet vortex, the aircraft engine apparatus comprising:an aircraft engine having an engine nacelle extending lengthwise between an opposing inlet and exhaust nozzle; anda vortex disruption system comprising at least one outlet port opening through said inlet of said engine nacelle, wherein said vortex disruption system bleeds fluid from said aircraft engine and periodically discharges pulses of fluid through said at least one outlet port such that the periodic pulses of fluid...