|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3907 ; 60/3983 ; 60/269|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 57 인용 특허 : 0|
A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle is enclosed so that effectively all of the cooling air entering the bay leaves the bay through the engine exhaust and is not dumped overboard, thereby adding to the effective thrust of the engine. An engine oil and generator oil heat exchanger is positioned in the cooling air duct into the bay so that t...
In a nacelle having a turbine engine in a bay thereof, an engine inlet for supplying combustion air to said engine, an exhaust shroud forming an annular passage with an exhaust conduit of said engine for evacuating air from within said engine bay, a chin scoop for receiving cooling air and an air/oil heat exchanger receiving cooling air from said chin scoop, a cooling and ventilation system comprising: duct means for discharging air from said heat exchanger into said bay wherein said discharged air cools said engine and is drawn through said annular pass...