Fluid temperature control installation for rotorcraft, associating a system for cooling a power plant with a system for heating a cabin
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F25B-027/00
B64D-013/08
B64D-013/06
F25B-009/06
F25B-019/02
출원번호
US-0741551
(2013-01-15)
등록번호
US-9469407
(2016-10-18)
우선권정보
FR-12 00191 (2012-01-24)
발명자
/ 주소
Pomme, Vincent
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A fluid temperature control installation for a rotorcraft, the installation comprising a system for cooling a main transmission (3) and a system for temperature control of the ambient air (32) of a cabin (16). A heat exchanger (8) is fitted with a bladeless ventilator (9). A source air stream (11) g
A fluid temperature control installation for a rotorcraft, the installation comprising a system for cooling a main transmission (3) and a system for temperature control of the ambient air (32) of a cabin (16). A heat exchanger (8) is fitted with a bladeless ventilator (9). A source air stream (11) generated by an accessory compressor (5) driven by the main transmission (3) passes through the heat exchanger (8) where it takes heat. The source air stream (11) is distributed selectively to the bladeless ventilator (9) to generate a cooling air stream (13) passing through the heat exchanger (8), and/or is distributed to the cabin (16) after passing through the heat exchanger (8) in order to heat the ambient air (32) of the cabin.
대표청구항▼
1. A fluid temperature control installation for an aircraft, the installation comprising at least one cooling system that requires cooling at least one member for cooling, and at least one temperature control system for controlling the temperature of the air of a cabin of the aircraft; the cooling s
1. A fluid temperature control installation for an aircraft, the installation comprising at least one cooling system that requires cooling at least one member for cooling, and at least one temperature control system for controlling the temperature of the air of a cabin of the aircraft; the cooling system comprising a closed circuit for circulating a fluid for cooling between the member for cooling and at least one heat exchanger fitted with an airflow generator member, the heat exchanger being interposed on the closed circuit by means of an internal circuit for the fluid for cooling, and including a heat exchange structure through which there is passed a stream of cooling air generated by the airflow generator member; andthe air temperature control system comprising a distributor valve for regulating a stream of heating air admitted to the cabin, and an open circuit conveying a plurality of air streams, the open circuit having a first air circuit for conveying a source air stream generated by a compressor to at least one temperature control device, and a second air circuit for conveying to the cabin the stream of heating air from the temperature control of the source air stream;wherein:the airflow generator member is a bladeless ventilator generating the cooling air stream from an activation air stream; and whereinthe cooling system and the temperature control system include a group of members in common, comprising at least:a) the compressor generating a source air stream, the compressor being an accessory compressor provided with an air inlet and driven by a drive member;b) the heat exchanger comprising co-operating means for cooling the fluid for cooling and for heating the source air stream coming from the accessory compressor, the heating of the source air stream producing a hot air stream by taking heat contributing to cooling the heat exchange structure; andc) the distributor valve distributes the source air stream selectively: in a first mode solely to the bladeless ventilator thereby forming the activation air stream, in a second mode solely to the cabin thereby forming the heating air stream coming from the hot air stream and in a third mode to both of the bladeless ventilator and the cabin. 2. The installation according to claim 1, wherein the distributor valve is placed on the first air circuit at the outlet from the heat exchanger, the activation air stream coming from the hot air stream formed by the source air stream heated by the heat exchanger. 3. The installation according to claim 1, wherein the distributor valve is a member for temperature controlling fluids selectively between heating the ambient air of the cabin and cooling the fluid for cooling by inversely proportional amounts of the source air stream respectively to the second air circuit and/or to the bladeless ventilator. 4. The installation according to claim 1, wherein the distributor valve is under the control of control means that may equally well be manually controlled and/or automatically controlled, between a mode for temperature control of the cabin in which a major quantity of the source air stream is distributed to the cabin after being heated by the heat exchanger, and a cooling mode in which a major quantity of the source air stream is distributed to the bladeless ventilator. 5. The installation according to claim 4, wherein use of the automatic control means for controlling the distributor valve depends at least on means for measuring the temperature of the fluid for cooling, means for measuring the temperature of the ambient air inside the cabin, and means for measuring the temperature of the source air stream. 6. The installation according to claim 1, wherein the heat exchanger is organized as a dual heat exchange member, including both heat exchange between the fluid for cooling and the stream of cooling air, and also heat exchange between the fluid for cooling and the source air stream. 7. The installation according to claim 6, wherein the heat exchange structure is in air-flow communication with an outside air admission opening, the outside air forming the cooling air stream comes, and has passing therethrough a channel of the first air circuit conveying the source air stream through the heat exchange structure in order to form the hot air stream that is maintained in the compressed state. 8. The installation according to claim 1, wherein the installation is fitted with a heat exchange device comprising the heat exchanger having the heat exchange structure, means for taking heat, and a first internal circuit for conveying a flow of a fluid for cooling, the means for taking heat associating: a second internal circuit for passing a flow of a heat-transfer fluid coming from the source air stream; andthe bladeless ventilator provided with means for admitting an activation air stream coming from the source air stream. 9. The installation according to claim 8, wherein the activation air stream admission means comprise a regulated admission valve for regulated admission of the source air stream to the bladeless ventilator, the regulated admission valve being constituted by the distributor valve. 10. The installation according to claim 1, wherein the bladeless ventilator comprises at least one module having at least one air ejector of conical shape or elongate shape. 11. The installation according to claim 10, wherein the bladeless ventilator comprises a plurality of juxtaposed independent modules, each module comprising a housing containing an elongate air ejector or housing a plurality of elongate air ejectors arranged in parallel inside the housing. 12. The installation according to claim 1, wherein the air inlet of the accessory compressor is in air-flow communication with a third air circuit included in the open circuit, the third air circuit having a selection valve for selecting suction of an admission air stream by the accessory compressor, the selection valve distributing to the accessory compressor and in inversely proportional quantities a stream of ambient air taken from the cabin and/or a stream of air from outside the cabin. 13. The installation according to claim 12, wherein the selection valve contributes with the distributor valve for regulating the heating air stream, use of the selection valve being under the control of control means. 14. The installation according to claim 1, wherein the accessory compressor is driven from a main gearbox forming part of a main power plant of the aircraft. 15. An aircraft fitted with the installation according to claim 1. 16. The aircraft according to claim 15, wherein the aircraft is a rotorcraft fitted: with a main power plant for driving at least one rotor, and comprising at least one engine member engaged with a main transmission from which the accessory compressor is driven;with the cooling system for cooling at least one member that requires cooling, including the main gearbox, comprising:the closed circuit for circulation of a fluid for cooling incorporating at least the heat exchanger fitted with the bladeless ventilator; andthe first air circuit for conveying a source air stream generated by the accessory compressor from which the activation air stream is taken;with at least the heat exchange system for a cabin, the system comprising:a) the accessory compressor fed with air selectively from the ambient air in the cabin and/or from an intake for air outside the cabin via the selection valve;b) the first air circuit and the heat exchanger having passing therethrough a channel for conveying the source air stream; andc) the second air circuit for conveying heating air coming from hot air obtained by heating the source air stream by means of the heat exchanger; andwith the selected distributor valve for the source air stream included in the cooling system and the temperature control system in association, the distributor valve distributing inversely proportional admissions of the source air stream to the bladeless ventilator and to the second air circuit after temperature control of the source air stream by the heat exchanger.
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이 특허에 인용된 특허 (2)
Dziorny, Paul J.; Sellers, Benjamin D., Air conditioning apparatus.
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