|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/204 ; 60/2261 ; 60/3983 ; 165/142|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 32 인용 특허 : 0|
A heat exchanger for cooling turbine components of a gas turbofan engine in which air to be cooled is directed along a first annular, radially extending path away from the engine and cooled by bypass air. The cooled air is returned to the engine along a second radially-extending path concentric to the first path. In a preferred embodiment, the heat exchanger is a standpipe extending from the compressor outlet to the bypass air duct and includes inner and outer tubular members oriented concentrically to form inner and outer counterflowing air flow paths w...
A method for cooling air in a substantially cylindrical gas turbine engine having a compressor producing high pressure air, a turbine and a bypass duct existing between a core casing and an outer casing for ducting high pressure bypass air surrounding the compressor and turbine, the method comprising the steps of: independently statically and sealingly mounting first radial and unshrouded heat exchanger tube constructed of a first heat conductive material to the combustor casing and second radial heat exchanger tube constructed of a second heat insulativ...