IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0322999
(2009-02-10)
|
등록번호 |
US-8292222
(2012-10-23)
|
우선권정보 |
DE-10 2006 037 539 (2006-08-10) |
발명자
/ 주소 |
- Solntsev, Alexander
- Eichholz, Johannes
- Bammann, Holger
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
12 |
초록
▼
Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to
Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to a plurality of zones (2, 4) of an aircraft, wherein warm air is fed through a first trim valve (12) into the second line (14) so that the air in the second line (14) is heated to the actual temperature T2act., and a first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2), wherein a second trim valve (26) is arranged in the first zone feed line (24), through which valve warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act., and the first line (6) downstream and/or upstream of the branching point (1) feeds cold air at least to one further zone. A second feed line (18) feeds air downstream of the first adjustment (12) to a second zone (4). A heating device (20) can be arranged in the second feed line (18).
대표청구항
▼
1. An aircraft air-conditioning system (1) for an aircraft containing a plurality of zones (2, 4), comprising a cold air source,a first line (6) for feeding cold, non-recirculated air at an actual temperature T1act., wherein the first line (6) is fed from the cold air source and the first line (6),
1. An aircraft air-conditioning system (1) for an aircraft containing a plurality of zones (2, 4), comprising a cold air source,a first line (6) for feeding cold, non-recirculated air at an actual temperature T1act., wherein the first line (6) is fed from the cold air source and the first line (6), downstream and/or upstream of a branching point (10) at which air is tapped off for a plurality of zones (2, 4), feeds cold air at least to one further region that is provided for passengers and/or freight,a second line (14) which branches off a portion of the air from the first line (6) at the branching point (10) and feeds this air to the plurality of zones (2, 4) of the aircraft, wherein warm air is fed into the second line (14) through a first trim valve (12) so that the air in the second line (14) is heated to the actual temperature T2act higher than about 0° C., anda first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2),wherein in the first zone feed line (24) a second trim valve (26) is arranged, through which warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act.,characterised in that the first line (6) feeds air to a mixing chamber, to which is also fed recirculated air. 2. The aircraft air-conditioning system (1) according to claim 1, characterised in that the cold air source is an air-conditioning PACK. 3. The aircraft air-conditioning system (1) according to claim 1, characterised in that the temperature of the air in the first line (6) is between about −10° C. and about 0° C. 4. The aircraft air-conditioning system (1) according to claim 1, characterised in that a second zone feed line (18) feeds air downstream of the first trim valve (12) to a second zone (4). 5. The aircraft air-conditioning system (1) according to claim 1, characterised in that a heating device (20) is arranged in the second zone feed line (18), which heats up the air in the second zone feed line (18) to the actual temperature Tzf2act.. 6. The aircraft air-conditioning system (1) according to claim 4, characterised in that the second zone (4) requires a smaller amount of warm air than the first zone (2). 7. The aircraft air-conditioning system (1) according to claim 1, characterised in that the aircraft air-conditioning system (1) furthermore includes a temperature sensor (16), which senses the actual temperature T2act. of the air in the second line (14) downstream of the first trim valve (12), and includes a regulating device which is adapted to control the first trim valve (12) and the second trim valve (26). 8. The aircraft air-conditioning system (1) according to claim 7, characterised in that the regulating device controls the first trim valve (12) in such a way that the actual temperature T2act. of the air in the second line (14) corresponds approximately to the set temperature Tzf2set of the air in the second zone feed line (18). 9. The aircraft air-conditioning system (1) according to claim 7, characterised in that the aircraft air-conditioning system (1) furthermore includes a first zone feed line temperature sensor (28), which senses the actual temperature Tzf1act. of the air in the first zone feed line (24) downstream of the trim valve (26), and includes a second zone feed line temperature sensor (22), which senses the actual temperature Tzf2act. of the air in the second zone feed line (18) downstream of the heating device (20). 10. The aircraft air-conditioning system (1) according to claim 7, characterised in that if the set temperature Tzf1set of the air in the first zone feed line (24) is higher than the set temperature Tzf2set of the air in the second zone feed line (18), then the regulating device controls the first trim valve (12) in such a way that the actual temperature T2act. of the air in the second line (14) corresponds approximately to the set temperature Tzf2set of the air in the second zone feed line (18). 11. The aircraft air-conditioning system (1) according to claim 7, characterised in that if the set temperature Tzf1set of the air in the first zone feed line (24) is lower than the set temperature Tzf2set of the air in the second zone feed line (18), then the regulating device controls the first trim valve (12) in such a way that the actual temperature T2act. of the air in the second line (14) corresponds approximately to the set temperature Tzf1set of the air in the first zone feed line (24). 12. The aircraft air-conditioning system (1) according to claim 7, characterised in that if the set temperature Tzf1set of the air in the first zone feed line (24) is higher than the set temperature Tzf2set of the air in the second zone feed line (18), then the regulating device controls the first trim valve (12) in such a way that the actual temperature T2act. of the air in the second line (14) is increased, and controls the heating device (20) in such a way that the heating device (20) heats the air in the second zone feed line (18) to the set temperature Tzf2set. 13. The aircraft air-conditioning system (1) according to claim 7, characterised in that if the set temperature Tzf1set of the air in the first zone feed line (24) is lower than the set temperature Tzf2set of the air in the second zone feed line (18), then the regulating device controls the first trim valve (12) in such a way that the actual temperature T2act. of the air in the second line (14) is increased, and controls the second trim valve (26) in such a way that the air in the first zone feed line (24) is heated to the set temperature Tzf1set. 14. The aircraft air-conditioning system (1) according to claim 7, characterised in that the aircraft air-conditioning system (1) includes a first zone temperature sensor (32), which senses the actual temperature Tz1act. of the air in the first zone (2), wherein the regulating device determines the set temperature Tzf1set of the air in the first feed line (24) from the actual temperature Tz1act. and from the set temperature Tz1set of the air in the first zone (2). 15. The aircraft air-conditioning system (1) according to claim 7, characterised in that the aircraft air-conditioning system (1) includes a second zone temperature sensor (30), which senses the actual temperature Tz2act. of the air in the second zone (4), wherein the regulating device determines the set temperature Tzf2set of the air in the second feed line (18) from the actual temperature Tz2act. and from the set temperature Tz2set of the air in the second zone (4). 16. A method for the air conditioning of a plurality of zones (2, 4) in an aircraft, comprising the following steps: providing an aircraft air conditioning system according to claim 1;feeding non-recirculated cold air at an actual temperature T1act. in a first line (6);branching off part of the cold air into a second line (14) at a branching point (10);passing the cold air in the first line (6) to further zones, which are located downstream and/or upstream of the branching point (10);feeding warm air via a first trim valve (12) to the second line (14), so that the air in the second line (14) is heated to an actual temperature T2act. that is higher than 0° C.;passing a part of the air in the second line (14) through a first zone feed line (24) into a first zone (2); andfeeding warm air through a second trim valve (26) into the first zone feed line (24), so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act.,characterised by supplying air by the first line to a mixing chamber, to which is also fed recirculated air. 17. The method according to claim 16, characterised by the following steps: leading part of the air in the second line (14) through a second zone feed line (18) into a second zone (4); andheating the air in the second zone feed line (18) to the actual temperature Tzf2act. with a heating device (20). 18. The aircraft air-conditioning system (1) according to claim 2, characterised in that a second zone feed line (18) feeds air downstream of the first trim valve (12) to a second zone (4). 19. The aircraft air-conditioning system (1) according to claim 2, characterised in that a heating device (20) is arranged in the second zone feed line (18), which heats up the air in the second zone feed line (18) to the actual temperature Tzf2act.. 20. The aircraft air-conditioning system (1) according to claim 2, characterised in that the aircraft air-conditioning system (1) furthermore includes a temperature sensor (16), which senses the actual temperature T2act. of the air in the second line (14) downstream of the first trim valve (12), and includes a regulating device which is adapted to control the first trim valve (12) and the second trim valve (26).
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