|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-006/18 F02K-011/00 B64B-001/24|
|미국특허분류(USC)||60/3907 ; 60/262 ; 60/266 ; 60/3983|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 35 인용 특허 : 0|
The hot core engine compartment of a turbojet engine is cooled by the metered flow of cooling air exhausted through a laminar flow nacelle system. This arrangement reduces the need for extracting bypass ram air from the engine performance cycle for cooling purposes and thereby improves specific fuel consumption and engine efficiency. A turbocompressor pump driven by bleed air from the core engine compressor draws cooling air through the laminar flow nacelle system and pumps the air into a manifold surrounding the core engine.
A cooling system for a turbojet engine, comprising: nacelle means defining an air inlet leading into said engine, said nacelle means having port means disposed about said inlet for admitting air through said nacelle for promoting laminar flow around said nacelle; duct means disposed within said nacelle and communicating with said port means; a core engine disposed within said turbojet engine: core air inlet means disposed within said nacelle for providing air to said core engine; bypass means for bypassing air from said core air inlet mean around said co...