Auxiliary refrigerated air system employing mixture of air bled from turbine engine compressor and air recirculated within auxiliary system
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F25D-009/00
출원번호
US-0501578
(1990-03-30)
발명자
/ 주소
Renninger, Stanton W.
Giffin, III, Rollin G.
출원인 / 주소
General Electric Company
대리인 / 주소
Squillaro, Jerome C.
인용정보
피인용 횟수 :
11인용 특허 :
8
초록▼
An auxiliary refrigerated air system includes first and second tandemly-arranged auxiliary turbine components, air mixing and dividing valves, an air recirculation loop, an auxiliary air compressor, and a heat exchanger. The air mixing valve is connectable to a suitable input air source for receivin
An auxiliary refrigerated air system includes first and second tandemly-arranged auxiliary turbine components, air mixing and dividing valves, an air recirculation loop, an auxiliary air compressor, and a heat exchanger. The air mixing valve is connectable to a suitable input air source for receiving and mixing input air with dilution air and producing an air mixture. The air dividing valve is connected in communication between an exit side of the first auxiliary turbine component and an entrance side of the second auxiliary turbine component for diverting a portion of the energy-depleted air exiting from the first auxiliary turbine component. The air recirculation loop is connected in communication between the mixing and dividing valves for recirculating to the mixing valve the portion of the air diverted by the dividing valve to provide the dilution air to the mixing valve. The auxiliary compressor is drivingly connected to the auxiliary turbine components, connected in communication with the mixing valve, and operable for receiving the air mixture from the mixing valve and producing compressed air upon operation of the first and second auxiliary turbine components. The heat exchanger uses the turbine engine fuel to cool compressed air routed from the auxiliary compressor to the entrance side of the first auxiliary turbine component.
대표청구항▼
1. An auxiliary refrigerated air system, comprising: (a) first and second tandemly-arranged auxiliary turbine components having respective entrance and exit sides, said turbine components being operable for successively receiving air at said entrance sides thereof and producing energy-depleted ai
1. An auxiliary refrigerated air system, comprising: (a) first and second tandemly-arranged auxiliary turbine components having respective entrance and exit sides, said turbine components being operable for successively receiving air at said entrance sides thereof and producing energy-depleted air at said exit sides thereof; (b) means connectable to a source of input air for receiving and mixing input air with dilution air and producing an air mixture; (c) means connected in communication between said exit side of said first auxiliary turbine component and said entrance side of said second auxiliary turbine component for diverting a portion of the energy-depleted air exiting from said first auxiliary turbine component; (d) an air recirculation loop connected in communication between said mixing means and said diverting means for recirculating to said mixing means from said diverting means said portion of the air exiting said exit side of said first turbine component to provide dilution air to said mixing means; (e) an auxiliary air compressor having inlet and outlet sides, said auxiliary compressor being drivingly connected to said first and second auxiliary turbine components and connected in communication at said inlet side with said mixing means, said auxiliary compressor being operable for receiving the air mixture therefrom at said inlet side and producing compressed air at said outlet side upon operation of said first and second turbine components; and (f) a heat exchanger having a first side connectable in communication with a flow of fluid providing a heat sink and a second side connected in communication between said outlet side of said auxiliary air compression for receiving compressed air therefrom and said entrance side of said first turbine component for discharging conditioned air thereto. 2. The auxiliary system as recited in claim 1, further comprising: a common drive shaft drivingly interconnecting said auxiliary air compressor and said first and second auxiliary turbine components for causing operation of said auxiliary compressor upon operation of said turbine components. 3. The auxiliary system as recited in claim 1, wherein the pressure of the recirculated air from said recirculation loop is substantially equal to the pressure of the input air to said mixing means. 4. The auxiliary system as recited in claim 1, wherein the pressure of the air at said exit side of said first auxiliary turbine component is substantially equal to the pressure of the input air to said mixing means. 5. The auxiliary system as recited in claim 1, wherein said mixing means is an air mixing valve. 6. The auxiliary system as recited in claim 1, wherein said diverting means is an air dividing valve. 7. The auxiliary system as recited in claim 1, wherein said first and second auxiliary turbine components are two separate turbines. 8. The auxiliary system as recited in claim 1, wherein said first and second auxiliary turbine components are of a single turbine. 9. In combination with an aircraft turbine engine which includes an air compressor, an auxiliary refrigerated air system comprising: (a) first and second tandemly-arranged auxiliary turbine components having respective entrance and exit sides, said turbine components being operable for successively receiving air at said entrance sides thereof, generating motive power to perform work, and producing energy-depleted air at said exit sides thereof; (b) an air mixing valve connected in communication to said turbine engine compressor for receiving and mixing input air bled off from said engine compressor with dilution air and producing an air mixture; (c) an air dividing valve connected in communication between said exit side of said first auxiliary turbine component and said entrance side of said second auxiliary turbine component for diverting a portion of the energy-depleted air exiting from said first auxiliary turbine component; (d) an air recirculation loop connected in communication between said mixing valve and said dividing valve for recirculating to said mixing valve from said dividing valve said portion of the air exiting said exit side of said first turbine component to provide dilution air to said mixing valve; (e) an auxiliary air compressor having inlet and outlet sides, said auxiliary compressor being drivingly connected to said first and second auxiliary turbine components and connected in communication at said inlet side with said mixing valve, said auxiliary compressor being operable for receiving the air mixture therefrom at said inlet side and producing compressed air at said outlet side upon operation of said first and second turbine components; and (f) a heat exchanger having a cool side connectable in communication with a flow of fluid providing a heat sink and a hot side connected in communication between said outlet side of said auxiliary air compression for receiving compressed air therefrom and said entrance side of said first turbine component for discharging cooler air thereto. 10. The auxiliary system as recited in claim 9, further comprising: a common drive shaft drivingly interconnecting said auxiliary compressor and said first and second auxiliary turbine components for causing operation of said auxiliary compressor upon operation of said turbine components. 11. The auxiliary system as recited in claim 9, wherein the pressure of the recirculated air from said recirculation loop is substantially equal to the pressure of the input air to said mixing means. 12. The auxiliary system as recited in claim 9, wherein the pressure of the air at said exit side of said first auxiliary turbine component is at least equal to the pressure of the input air to said mixing means. 13. The auxiliary system as recited in claim 9, wherein said first and second auxiliary turbine components are two separate turbines. 14. The auxiliary system as recited in claim 9, wherein said first and second auxiliary turbine components are of a single turbine.
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이 특허에 인용된 특허 (8)
Edwards Thomas C. (Casselberry FL), Air conditioning system having super-saturation for reduced driving requirement.
Atkey, Warren A.; Mackin, Steve G.; Millar, Rod, System and method for improved cooling efficiency of an aircraft during both ground and flight operation.
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