IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0744165
(2008-11-26)
|
등록번호 |
US-8572996
(2013-11-05)
|
우선권정보 |
DE-10 2007 057 536 (2007-11-29) |
국제출원번호 |
PCT/EP2008/010030
(2008-11-26)
|
§371/§102 date |
20110301
(20110301)
|
국제공개번호 |
WO2009/068265
(2009-06-04)
|
발명자
/ 주소 |
- Dittmar, Jan
- Antoine, Nicolas
- Buchholz, Uwe
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
3 |
초록
▼
An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to t
An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems—such as, for example, wing de-icing—and therefore reduces the excess fuel consumption of the aircraft.
대표청구항
▼
1. Energy supply system for operating at least one air conditioning system of an aircraft, comprising at least one air line network and at least one electric line network, whereinthe air line network is connected to the air conditioning system and to at least one bleed air connection for routing ble
1. Energy supply system for operating at least one air conditioning system of an aircraft, comprising at least one air line network and at least one electric line network, whereinthe air line network is connected to the air conditioning system and to at least one bleed air connection for routing bleed air to the air conditioning system,the air conditioning system includes an electrically operable cooling device,the electric line network is connected to the air conditioning system and at least one electrical energy source, which is a generator/starter unit, for routing electrical energy to the air conditioning system, and whereinthe generator/starter unit is adapted to compensate an energy difference between energy required for cooling and energy provided by the bleed air by electrical energy provided by the generator/starter unit. 2. Energy supply system according to claim 1, in which no precooler operated by bleed air is provided. 3. Energy supply system according to claim 1, with at least one ram air channel through which ram air flows during flight and which has a heat exchanger which can be connected to the air line network. 4. Energy supply system according to claim 3, wherein an additional fan to make air flow through the ram air channel when on the ground is integrated into the ram air channel. 5. Energy supply system according to claim 1, in which the engines of the aircraft each have two bleed air connections at different pressure levels which are connected to the air line network. 6. Energy supply system according to claim 5, in which the respective bleed air connection of a higher pressure has a throttle valve for regulating the pressure and/or volumetric flow rate of the bleed air withdrawn from the bleed air connection. 7. Energy supply system according to claim 5, in which the respective bleed air connection of a lower pressure has a non-return valve for preventing the return flow of bleed air from the bleed air connection of a higher pressure via the bleed air connection of a lower pressure into the engine. 8. Energy supply system according to claim 1, in which the bleed air is withdrawn from a compressor driven by an APU. 9. Energy supply system according to claim 1, with an external air inlet and an additional fan for supplying the air conditioning system with air when on the ground. 10. Energy supply system according to claim 9, wherein the external air inlet is integrated into the ram air channel. 11. Energy supply system according to claim 8, in which the engines and the APU of the aircraft are each equipped with a generator/starter unit as an electrical energy source, wherein the generator/starter units are further adapted to start the engines electrically without bleed air. 12. Energy supply system according to claim 1, in which the cooling device is further adapted to be operated by bleed air by means of an expansion cooling circuit. 13. Energy supply system according to claim 1, and further adapted to supply a de-icing system with electrical energy, wherein the de-icing system is adapted for operation without the use of bleed air. 14. Air conditioning system for an aircraft which is connected to the energy supply system according to claim 1, wherein the air line network routes bleed air for pressurising the cabin of the aircraft to the air conditioning system, and the electric line network routes electrical energy for operating the electrical cooling device to the air conditioning system. 15. Method for air-conditioning an aircraft using an energy supply system according to claim 1, in which in which the generator/starter unit is controlled to compensate an energy difference between energy required for cooling and energy provided by the bleed air by electrical energy provided by the generator/starter unit, wherein the bleed air is cooled by an electrically operable cooling device powered via at least one electric line network, and wherein the energy required for cooling of the bleed air is provided by the generator/starter unit in the form of electrical energy. 16. Method according to claim 15, in which the bleed air is not precooled by a precooler operated by bleed air. 17. Method according to claim 15, in which the bleed air is precooled by a heat exchanger which is disposed in a ram air channel and can be connected to the air line network. 18. Method according to claim 15, in which an additional fan is operated to make air flow through the ram air channel when the aircraft is on the ground. 19. Method according to claim 15, in which the bleed air is withdrawn from two respective bleed air connections at different pressure levels of the engines of the aircraft. 20. Method according to claim 15, in which the bleed air volumetric flow rate and bleed air pressure from a respective bleed air connection of a higher pressure is regulated by means of a throttle valve. 21. Method according to claim 15, in which a return flow of bleed air from a bleed air connection of a higher pressure via a bleed air connection of a lower pressure into the engine is prevented by means of a non-return valve. 22. Method according to claim 15, in which the bleed air is withdrawn from a compressor driven by an APU. 23. Method according to claim 15, in which air is routed via an additional fan and an external air inlet into the air conditioning system when the aircraft is on the ground.
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