IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0355876
(2012-01-23)
|
등록번호 |
US-8814086
(2014-08-26)
|
우선권정보 |
DE-10 2011 012803 (2011-03-02) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Scully, Scott, Murphy & Presser, P.C.
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
8 |
초록
▼
An on-board supply system (10) for use in an aircraft comprises a fuel cell unit (20) for generating electrical energy and heat energy, and at least one consumer system (100). The fuel cell unit (20) is designed to release heat energy in the form of hot air, and the consumer system (100) is designed
An on-board supply system (10) for use in an aircraft comprises a fuel cell unit (20) for generating electrical energy and heat energy, and at least one consumer system (100). The fuel cell unit (20) is designed to release heat energy in the form of hot air, and the consumer system (100) is designed to absorb the electrical energy and the heat energy in the form of hot air. The fuel cell unit (20) can comprise at least one low-temperature (LT) fuel cell (30) and at least one high-temperature (HT) fuel cell (40), which can both (30, 40) be designed to be regulated to their respective operating temperature in operation by means of air cooling, and an air cooling inlet (44) of the HT fuel cell (40) can be connected in fluid communication with an air cooling outlet (36) of the LT fuel cell (30).
대표청구항
▼
1. An on-board supply system for use in an aircraft, comprising: a fuel cell unit for generating electrical energy and heat energy,at least one consumer system,the fuel cell unit configured to release heat energy in the form of hot air, andthe at least one consumer system configured to absorb the el
1. An on-board supply system for use in an aircraft, comprising: a fuel cell unit for generating electrical energy and heat energy,at least one consumer system,the fuel cell unit configured to release heat energy in the form of hot air, andthe at least one consumer system configured to absorb the electrical energy and the heat energy in the form of hot air,wherein the fuel cell unit comprises at least one low-temperature (LT) fuel cell and at least one high-temperature (HT) fuel cell, the at least one LT fuel cell and the at least one HT fuel cell are configured to be regulated to the respective operating temperature in operation by means of air cooling, and an air cooling outlet of the at least one LT fuel cell is connected in direct fluid communication with an air cooling inlet of the at least one HT fuel cell,a hot air pipe bus system configured to guide hot air from the at least one HT fuel cell to the at least one consumer system, anda fan disposed upstream of an air cooling inlet of the at least one LT fuel cell, for conveying air required for feeding an oxidation medium to the at least one LT fuel cell and the at least one HT fuel cell, such that the discharged air of the at least one HT fuel cell has substantially the same oxygen content as air outside of the aircraft. 2. The on-board supply system according to claim 1, wherein an air cooling outlet of the at least one HT fuel cell is connected in fluid communication with a hot air inlet of at least one consumer of heat energy of the at least one consumer system. 3. The on-board supply system according to claim 1, wherein the cooling air inlet of the at least one LT fuel cell is connected in fluid communication with the air outside the aircraft. 4. The on-board supply system according to claim 2, further comprising a heating device which is configured to heat air to be fed into an aircraft cabin during operation. 5. The on-board supply system according to claim 4, wherein the heating device has an air inlet which is connected in fluid communication with an air outlet of the at least one consumer of heat energy of the at least one consumer system. 6. The on-board supply system according to claim 1, further comprising an emergency power supply device which comprises the fuel cell unit of the on-board supply system. 7. The on-board supply system according to claim 1, wherein at least one consumer of the at least one consumer system is configured to absorb electrical energy in the form of direct current. 8. The on-board supply system according to claim 1, wherein the fuel cell unit and the at least one consumer system belong to a first on-board galley for use in the aircraft. 9. The on-board supply system according to claim 1, wherein the at least one consumer system comprises at least one consumer of electrical energy and at least one consumer of heat energy in the form of hot air, andwherein the on-board supply system comprises a first control unit which is configured to supply the consumer of electrical energy and the consumer of heat energy with electrical energy and heat energy in the form of hot air, respectively, such that the balance between the electrical energy and the heat energy corresponds to the dynamic electrochemical balance during the operation of the fuel cell unit. 10. The on-board supply system according to claim 9, wherein the at least one consumer system comprises two or more consumers of electrical energy, and the on-board supply system includes a second control unit which is configured to feed the electrical energy generated by the fuel cell unit to the two or more consumers time-shifted with respect to one another. 11. The on-board supply system according to claim 10, wherein the second control unit is configured to feed the electrical energy emitted by the fuel cell unit to the two or more consumers in accordance with predetermined priorities which are assigned to the respective consumers and time-shifted with respect to one another according to predetermined rules relating to the supply of the consumers. 12. The on-board supply system according to claim 1, further comprising a DC high-voltage bus system which connects the current output of the HT fuel cell to the two or more consumers of electrical energy of the consumer system in an electrically conducting manner. 13. An aircraft comprising at least two on-board supply systems according to claim 1. 14. The aircraft according to claim 13, further comprising at least two on-board galleys each of which includes said on-board supply system. 15. The aircraft according to claim 13, further comprising a conventional emergency power supply system with an electrical component, a conventional emergency power supply unit and a conventional alternating current (AC) emergency power bus system. 16. The aircraft according to claim 15, wherein the conventional emergency power supply system is connected to a DC high-voltage bus system of the on-board supply system via a DC emergency power bus system in an electrically conducting manner. 17. The aircraft according to claim 16, wherein the an electrical component is arranged between the conventional AC emergency power bus system and the DC emergency power bus system and is configured to convert the alternating voltage and the alternating current in the conventional AC emergency power bus system into the direct voltage and direct current of the DC emergency power bus system.
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