Cooling air supply for the cooling of different systems requiring cooling air in an aircraft
A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air ( 38, 44, 56 ) within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.
1. A cooling air supply system configured to supply cooling air from the surroundings of an aircraft to at least two devices requiring cooling air within the aircraft, the cooling air supply system comprising:
an air inlet,
an air channel communicating with the air inlet,
an air distribution device configured to distribute air from the air channel directly to the at least two devices requiring cooling air, the air distribution device being located downstream from the air channel and upstream from the at least two devices requiring cooling air, and
at least one shutter disposed in the air distribution device and configured to throttle the distribution of air from the air channel
to the at least two devices requiring cooling air,
whereby the air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.
2. The cooling air supply system of claim 1 , characterized in that the air inlet is located in an outer skin of the aircraft.
3. The cooling air supply system of claim 1 , characterized in that the air channel communicating with the air inlet includes a diffuser.
4. The cooling air supply system of claim 3 , further comprising:
at least one air compressor located in the diffuser or in a first bypass line leading off from the diffuser.
5. The cooling air supply system of claim 4 , characterized in that the at least one air compressor is a turbo-compressor.
6. The cooling air supply system of claim 4 , further comprising:
a check valve provided in the diffuser or in a second bypass line leading off from the diffuser, the check valve preventing the cooling air from flowing back into the diffuser.
7. The cooling air supply system of claim 6 , characterized in that the first bypass line and the second bypass line are arranged in parallel.
8. The cooling air supply system of claim 7 , further comprising:
a cooling air collection chamber located downstream of the diffuser and the first and second bypass lines.
9. The cooling air supply system of claim 8 , further comprising:
at least one cooling air supply line positioned between the cooling air collection chamber and each of the at least two devices requiring cooling air.
10. The cooling air supply system of claim 1 , characterized in that a pack bay ventilation system is one of the at least two devices requiring cooling air.
11. The cooling air supply system of claim 1 , characterized in that an on board oxygen generation system is one of the at least two devices requiring cooling air.
12. The cooling air supply system of claim 1 , characterized in that a heat exchanger which uses the cooling air in order to eliminate heat is one of the at least two devices requiring cooling air.
13. The cooling air supply system of claim 1 , further comprising:
air pipes connecting the at least two devices requiring cooling air with a common cooling air outlet.
14. An aircraft comprising:
an outer skin;
at least two devices requiring cooling air; and
a cooling air supply system including:
an air inlet at the outer skin,
an air channel communicating with the air inlet,
an air distribution device configured to distribute air from the air channel directly to the at least two devices requiring cooling air, the air distribution device being located downstream from the air channel and upstream from the at least two devices requiring cooling air, and
at least one shutter disposed in the air distribution device and configured to throttle the distribution of air from the air channel to the at least two devices requiring cooling air,
whereby the air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.
15. The aircraft of claim 14 , characterized in that the air channel communicating with the air inlet includes a diffuser, and the cooling air supply system further comprises:
at least one air compressor located in the diffuser or in a first bypass line leading off from the diffuser.
16. The aircraft of claim 15 , characterized in that the at least one air compressor is a turbo-compressor.
17. The aircraft of claim 15 , characterized in that the cooling air supply system further comprises:
a check valve provided in the diffuser or in a second bypass line leading off from the diffuser, the check valve preventing the cooling air from flowing back into the diffuser.
18. The aircraft of claim 17 , characterized in that the first bypass line and the second bypass line are arranged in parallel.
19. The aircraft of claim 18 , characterized in that the cooling air supply system further comprises:
a cooling air collection chamber located downstream of the diffuser and the first and second bypass lines.
20. The aircraft of claim 19 , characterized in that the cooling air supply system further comprises:
at least one cooling air supply line positioned between the cooling air collection chamber and each of the at least two devices requiring cooling air.