[특허]Aircraft cooling method

[미국특허] Aircraft cooling method 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/18
출원번호	US-0103602 (1993-08-06)
발명자 / 주소	Glickstein Marvin R. (North Palm Beach FL)
출원인 / 주소	United Technologies Corporation (Hartford CT 02)
인용정보	피인용 횟수 : 53 인용 특허 : 0

초록 ▼

A method for supplying cooling air on vehicles such as high speed aircraft includes diverting high pressure air from the compressor section of a gas turbine engine, cooling this air in a heat exchanger, and expanding the diverted high pressure air through an auxiliary turbine. Coolant in the heat exchanger may be inlet ram air, fan air, or aircraft fuel (which may be endothermic), and the coolant is ultimately introduced into the engine downstream of the compressor section. An auxiliary compressor may be used to further compress the diverted high pressure air or coolant prior to the flowing thereof through the heat exchanger, and one or more auxiliary turbines may be used to power the auxiliary compressor, or mechanical accessories on the vehicle.

대표청구항 ▼

A method for generating cooled air for cooling components of a vehicle, said vehicle including a heat exchanger having first and second flow paths extending therethrough, each flow path having an inlet and an outlet, and an auxiliary unit having an auxiliary compressor and an auxiliary turbine, said auxiliary turbine connected to said auxiliary compressor by a shaft to provide power thereto, said method comprising: providing at least one gas turbine engine in said vehicle, said engine having in serial flow arrangement an engine inlet section and a compressor section, said engine inlet section for receiving ambient air and delivering said ambient air to said compressor section, said compressor section for compressing said ambient air thereby producing compressed air a combustor section for mixing fuel with said compressed air and igniting said fuel and compressed air to produce combustion products, a turbine section for expanding said combustion products and driving the compressor section, and an exhaust section for conveying said combustion products from said turbine section and out of said gas turbine engine; diverting a first portion of said ambient air from said engine inlet section; delivering said first portion to said auxiliary compressor and compressing said first portion, thereby increasing the pressure and temperature of said first portion exiting said auxiliary compressor: diverting a second portion of said compressed air from said compressor section; cooling said second portion while heating said first portion by flowing said first portion to the inlet of said first flow path, flowing said first portion through said heat exchanger, and flowing said first portion out the outlet of said first flow path, and delivering said second portion to the inlet of said second flow path, flowing said second portion through said heat exchanger, thereby simultaneously cooling said second portion and heating said first portion through the transfer of heat energy from said second portion to the first portion, and flowing said second portion out the outlet of said second flow path; discharging said first portion into said combustion products at said exhaust section; and, using said second portion that has been cooled to cool said components.

이 특허를 인용한 특허 (53) 인용/피인용 타임라인 분석

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[미국특허] Aircraft cooling method 원문보기

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