|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/039.02 ; 60/039.08 ; 60/039.83|
|§371/§102 date||19980427 (19980427)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 26 인용 특허 : 2|
A turboprop engine having an oil cooler which is disposed in the engine pod and upon which cooling air acts. The oil cooler is disposed in a flow duct which at the rear opens into the environment and at the front can be connected alternately to an air-inlet opening or to the feed duct of the compressor of the aircraft gas turbine.
[ What is claimed is:] [1.] An aircraft gas turbine engine, comprising:an engine casing defining a flow duct, said flow duct being communicable at a rearward end with an ambient environment, and said flow duct being selectively communicable at a forward end with one of the environment and an inflow duct of a compressor of the gas turbine engine; anda transmission oil cooler arranged in said flow duct.