|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64D-033/10 F02K-003/115 F02C-007/141 B64D-033/02|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 30|
In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at l...
1. A method of cooling a hot portion of a gas turbine engine of an aircraft having a compressor and a turbine, the method comprising: bleeding air from a discharge region of a high pressure compressor of the compressor to form a flow of compressor discharge air;circulating a cooling fluid and the compressor discharge air through a heat exchanger located inside a core cowl of a nacelle;exchanging heat in the heat exchanger from the compressor discharge air to the cooling fluid to cool the compressor discharge air and change a phase of the cooling fluid fr...