Nitrogen enriched air supply system and aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B01D-053/02
B64D-037/32
출원번호
US-0070663
(2013-11-04)
등록번호
US-9272790
(2016-03-01)
우선권정보
JP-2012-247270 (2012-11-09)
발명자
/ 주소
Fukuda, Koki
출원인 / 주소
MITSUBISHI AIRCRAFT CORPORATION
대리인 / 주소
Pearne & Gordon LLP
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system produces NEA that is enriched with nitrogen upon supply of sour
The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system produces NEA that is enriched with nitrogen upon supply of source gas during a flight through an ascent phase, a cruising phase, and a descent phase, and supplies the NEA to a fuel tank, the system including: an air separation module that separates oxygen and nitrogen in the source gas; and a temperature regulation mechanism that regulates a temperature of the source gas supplied to the air separation module. In at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism regulates the temperature of the source gas to below a temperature of the source gas in the descent phase.
대표청구항▼
1. A nitrogen enriched air supply system which produces nitrogen enriched air that is enriched with nitrogen upon supply of source gas during a flight of an aircraft through an ascent phase, a cruising phase, and a descent phase, and supplies the nitrogen enriched air to a fuel tank of the aircraft,
1. A nitrogen enriched air supply system which produces nitrogen enriched air that is enriched with nitrogen upon supply of source gas during a flight of an aircraft through an ascent phase, a cruising phase, and a descent phase, and supplies the nitrogen enriched air to a fuel tank of the aircraft, the system comprising: an altimeter that detects an altitude of the aircraft during the flight;an air separation module that separates oxygen and nitrogen in the source gas; anda temperature regulation mechanism that regulates a temperature of the source gas supplied to the air separation module according to the ascent phase, the cruising phase, and the descent phase determined based on altitude information from the altimeter,wherein, in at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism sets the temperature of the source gas to below a temperature of the source gas in the descent phase. 2. The nitrogen enriched air supply system according to claim 1, wherein in at least a part of the flight period through the ascent phase and the cruising phase,the source gas supplied to the air separation module is set to a flow rate smaller than that in the descent phase. 3. The nitrogen enriched air supply system according to claim 1, wherein the air separation module includes a hollow fiber polymer membrane. 4. The nitrogen enriched air supply system according to of claim 1, wherein the system includes a main pipe through which the source gas flows,the temperature regulation mechanism includes a bypass pipe for the main pipe, and regulates a temperature of the source gas in the bypass pipe. 5. The nitrogen enriched air supply system according to claim 4, wherein the temperature regulation mechanism regulates an amount of the source gas distributed to the main pipe and the bypass pipeaccording to the temperature of the source gas supplied to the air separation module. 6. The nitrogen enriched air supply system according to claim 4, wherein the air separation module is disposed on the main pipe. 7. The nitrogen enriched air supply system according to claim 6, wherein the system further includes a flow control valve on the main pipe,the produced nitrogen enriched air is supplied to the fuel tank through the main pipe by an opening/closing operation of the flow control valve. 8. The nitrogen enriched air supply system according to claim 4, wherein the temperature regulation mechanism further includesa temperature sensor,cooling means that cools the source gas passing through the bypass pipe or the main pipe, anda flow regulation valve that is placed at a branch point between the gas pipe and the bypass pipe. 9. The nitrogen enriched air supply system according to claim 8, wherein the cooling means is a heat exchanger that is placed around the bypass pipe. 10. The nitrogen enriched air supply system according to claim 1, wherein the system further includes a filter for removing a substance that contaminates the air separation module, andthe source gas which has been temperature-regulated by the temperature regulation mechanism passes through the filter and is supplied to the air separation module. 11. The nitrogen enriched air supply system according to claim 1, wherein the source gas is a bleed air from an engine that generates a thrust for the aircraft. 12. An aircraft comprising the nitrogen enriched air supply system according to claim 1. 13. A nitrogen enriched air supply system which produces nitrogen enriched air that is enriched with nitrogen upon supply of source gas during a flight of an aircraft through an ascent phase, a cruising phase, and a descent phase, and supplies the nitrogen enriched air to a fuel tank of the aircraft, the system comprising: a main pipe through which the source gas flows;an air separation module that separates oxygen and nitrogen in the source gas;a temperature regulation mechanism comprising a bypass pipe for the main pipe, a temperature sensor, and cooling means that cools the source gas passing through the bypass pipe or the main pipe, the temperature regulation mechanism regulating a temperature of the source gas supplied to the air separation module, a temperature of the source gas in the bypass pipe, and an amount of the source gas flowing into the bypass pipe; anda flow regulation valve that regulates the amount of the source gas flowing through the bypass pipe and the main pipe according to instructions from the temperature regulation mechanism,wherein, in at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism sets the temperature of the source gas to below a temperature of the source gas in the descent phase, andwherein the flow regulation valve is placed upstream at a branch point of the bypass pipe and the main pipe.
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이 특허에 인용된 특허 (3)
Massey, Alan; Wood, John; Ashton, Dominic, Aircraft fuel tank and inerting system therefor.
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