[특허]Autonomous electricity production and conditioning system for an aircraft, associated aircraft and method

Dassault Aviation

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Autonomous electricity production and conditioning system for an aircraft, associated aircraft and method

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-041/00 B64D-013/06
미국특허분류(USC)	244/058; 244/053A
출원번호	US-0471801 (2012-05-15)
등록번호	US-8882030 (2014-11-11)
우선권정보	FR-11 01511 (2011-05-18)
발명자 / 주소	Loison, Renaud
출원인 / 주소	Dassault Aviation
대리인 / 주소	Dowell & Dowell, PC
인용정보	피인용 횟수 : 2 인용 특허 : 14

초록

An environmental control system including an upstream assembly supplying outside air to a rotary system of an aircraft, the air not having passed through a propulsion engine of the aircraft, and wherein the rotary system includes a rotary shaft, a power turbine, a compressor and a cold turbine, and wherein the upstream supply assembly is connected to an inlet of the compressor mounted with the rotary shaft that is rotated by the power turbine and wherein the shaft is supplied with compressed gas from the compressor toward the cold turbine.

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1. An autonomous electricity production and conditioning system for an aircraft, including: a rotary shaft;a main compressor mounted integral with the rotary shaft;a power turbine for rotating the rotary shaft; anda cold expansion turbine rotated by the rotary shaft and supplied with a compressed gas from the main compressor;wherein the system comprises an upstream assembly supplying outside air to the aircraft, which outside air has not passed through a propulsion engine of the aircraft, the upstream assembly being connected to an inlet of the main compressor, the system also including a main alternator mechanically connected to the rotary shaft, and an auxiliary alternator separate from the main alternator, and wherein the auxiliary alternator is mechanically connected to the rotary shaft; andan electric network of the aircraft includes batteries which are electrically connectable to the auxiliary alternator to supply the auxiliary alternator with power and cause it to operate as an engine to start rotation of the rotary shaft and electrically disconnectable from the auxiliary alternator when the power turbine rotates the rotary shaft independently, such that when the rotary shaft is rotated by the power turbine, the main alternator operates as a generator and provides electric power to the electric network of the aircraft. 2. The system according to claim 1, wherein the supply assembly includes an upstream heat exchanger for placing the air outside the aircraft, not having passed through a propulsion engine of the aircraft, in a heat exchange relationship with at least part of the compressed gas from the main compressor. 3. The system according to claim 1, including a downstream heat exchanger, a condenser, and a separator that receive at least part of the compressed gas from the main compressor, to produce a compressed gas to be introduced into the cold turbine, the condenser placing a cooled expanded gas from the cold turbine in heat exchange with a compressed gas from the downstream heat exchanger. 4. The system according to claim 1, including at least one gas distribution hose for conducting an expanded gas from the cold turbine toward an enclosure of the aircraft to be conditioned. 5. An aircraft, comprising a system according to claim 1 and a fuel storage device, the fuel storage device comprising:at least one main reservoir to contain a first batch of fuel;at least one feed line for supplying a propulsion engine of the aircraft with the first batch of fuel contained in the at least one main reservoir; andat least one auxiliary reservoir to contain a second batch of fuel separate from the first batch of fuel, the auxiliary reservoir being connected to the at least one main reservoir, the storage device including an intake line for bringing the second batch of fuel contained in the at least one auxiliary reservoir toward a combustion chamber of the aircraft independent of any engine of the aircraft. 6. The system according to claim 1, including a combustion chamber, independent of any propulsion engine of the aircraft, the system including a channel for supplying the power turbine with at least one combustion gas from the combustion chamber. 7. The system of claim 6 including: at least one fuel reservoir to contain a first batch of fuel to supply the propulsion engine for propulsion of the aircraft; andmeans for conveying fuel from the at least one fuel reservoir to the combustion chamber. 8. The system according to claim 6, including a withdrawal hose for withdrawing a compressed gas from the main compressor emerging in the combustion chamber. 9. The system according to claim 8, including an auxiliary compressor arranged downstream of the main compressor and upstream of the cold turbine to receive at least part of the compressed gas from the main compressor, the withdrawal hose being tapped between the main compressor and the auxiliary compressor upstream of the auxiliary compressor. 10. The system according to claim 9, wherein the auxiliary compressor is rotated by the rotary shaft. 11. The system according to claim 1, including an auxiliary compressor positioned away from the rotary shaft, the system including an auxiliary motor for rotating the auxiliary compressor. 12. The system of claim 11 wherein the auxiliary motor is an electric motor rotated by electricity supplied by the electrical network of the aircraft. 13. The system according to claim 1, including a member for transmitting the rotating movement of the rotary shaft mechanically connected to the rotary shaft. 14. The system of claim 13 wherein the member for transmitting rotating movement to the rotary shaft is a speed reducer. 15. A method for conditioning an aircraft, including the following steps: providing the autonomous system according to claim 1;activating the power turbine to rotate the rotary shaft;jointly rotating the main compressor and the expansion turbine; andsupplying the main compressor with air outside the aircraft not having passed through a propulsion engine of the aircraft; andthe method including a starting step in which the batteries of the electric network of the aircraft are electrically connected to the auxiliary alternator to supply the auxiliary alternator and cause it to operate as an engine, then deactivating the auxiliary alternator by disconnecting the batteries from the auxiliary alternator when the power turbine rotates the shaft independently, such that when the rotary shaft is rotated, the main alternator operates as a generator and provides electric power to the electric network of the aircraft. 16. The method according to claim 15, including the following steps: activating a combustion chamber of the aircraft to produce a combustion gas;supplying the power turbine with the combustion gas; andwithdrawing at least part of the compressed gas from the main compressor to supply the combustion chamber.

이 특허에 인용된 특허 (14)

이 특허를 인용한 특허 피인용횟수: 2

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Autonomous electricity production and conditioning system for an aircraft, associated aircraft and method

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이 특허에 인용된 특허 (14)

이 특허를 인용한 특허 피인용횟수: 2

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Autonomous electricity production and conditioning system for an aircraft, associated aircraft and method

초록

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이 특허에 인용된 특허 (14)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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