|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/039.02; 060/039.07; 060/736|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 10 인용 특허 : 0|
An energy recovery system is provided for an aircraft gas turbine engine of the type in which some of the pneumatic energy developed by the engine is made available to support systems such as an environmental control system. In one such energy recovery system, some of the pneumatic energy made available to but not utilized by the support system is utilized to heat the engine fuel immediately prior to the consumption of the fuel by the engine. Some of the recovered energy may also be utilized to heat the fuel in the fuel tanks. Provision is made for multi...
1. A method of recovering heat in a gas turbine engine which drives a fan in an aircraft, comprising: (a) tapping a first compressor bleed airstream, B1, having a first temperature; (b) tapping a second compressor bleed airstream, B2, having a second temperature higher than the first temperature; (c) transferring heat from B1 through a first heat exchanger and into an aquaeous heat transfer medium; (d) transferring heat from the aqueous medium of (c) into high-pressure fuel having a pressure exceeding 500 psig; (e) bypassing some of B1 past the fi...