Environmental control system with an outflow heat exchanger
An airplane is provided. The airplane includes a pressurized volume and an air conditioning system. The pressurized volume provides a first medium. The air conditioning system includes a heat exchanger and a compressor. The heat exchanger transfers heat from a second medium to the first medium. The compressor receives the second medium. The compressor is upstream of the heat exchanger in a flow path of the second medium.
1. An airplane comprising:
a pressurized volume configured to provide a first medium;
an air conditioning system comprising:
a heat exchanger configured to transfer heat from a second medium to the first medium, and
a compressor configured to receive the second medium,
wherein the compressor is upstream of the heat exchanger in a flow path of the second medium;
a flow of a third medium; and
an additional heat exchanger configured to transfer heat from the third medium to the first medium.
2. The airplane of claim 1 , wherein the first medium is cabin discharge air, and
wherein the second medium is fresh air.
3. The airplane of claim 1 , comprising:
an outflow valve downstream of the heat exchanger in a flow path of the first medium.
4. The airplane of claim 1 , comprising:
a turbine downstream of the heat exchanger in a flow path of the first medium.
5. The airplane of claim 1 , wherein the heat exchanger and the additional heat exchanger comprise a continuous second medium surface.
6. The airplane of claim 1 , wherein the heat exchanger and the additional heat exchanger comprise one or more a continuous second medium fins.
7. The airplane of claim 1 , wherein the heat exchanger and the additional heat exchanger are included in a dual heat exchanger.
8. The airplane of claim 1 , wherein the third medium is pressurized air.
9. The airplane of claim 1 , wherein the additional heat exchanger is downstream of the heat exchanger in a flow path of the first medium.
10. The airplane of claim 1 , further comprising an outflow valve downstream of the heat exchanger in the flow path of the first medium.
11. The airplane of claim 1 , further comprising a turbine downstream of the heat exchanger in the flow path of the first medium.
12. An airplane comprising:
a pressurized volume configured to provide a first medium; and
an air conditioning system comprising:
a three medium heat exchanger; and
a compressor configured to receive a second medium,
wherein the compressor is upstream of the three medium heat exchanger in a flow path of the second medium.
13. The airplane of claim 12 , wherein the first medium is cabin discharge air, and
wherein the second medium is fresh air.
14. The airplane of claim 12 , wherein the three medium heat exchanger is configured to receive the first medium, the second medium, and a third medium, and
wherein the third medium and the first medium are heat sinks for the second medium.
15. The airplane of claim 14 , wherein the third medium is ram air.
16. The airplane of claim 14 , wherein the second medium rejects heat to the first medium and then subsequently rejects heat to the third medium.
17. The airplane of claim 14 , wherein the second medium rejects heat to the third medium and then subsequently rejects heat to the first medium.
18. The airplane of claim 14 , wherein the flow path of the second medium through the three medium heat exchanger is linear.
19. The airplane of claim 14 , wherein the flow path of the second medium through the three medium heat exchanger is non-linear.
20. An airplane comprising:
a pressurized volume configured to provide a first medium; and
an air conditioning system comprising:
a four medium heat exchanger; and
a compressor configured to receive a second medium,
wherein the compressor is upstream of the four medium heat exchanger in a flow path of the second medium.
21. The airplane of claim 20 , wherein the first medium is cabin discharge air, and
wherein the second medium is fresh air.
22. The airplane of claim 20 , wherein the four medium heat exchanger is configured to receive the first medium, the second medium, a third medium, and a fourth medium, and
wherein the third medium and the first medium are heat sinks for the second medium and the fourth medium.
23. The airplane of claim 22 , wherein the third medium is ram air, and
wherein the fourth medium is pressurized air.
24. The airplane of claim 22 , wherein the second medium rejects heat to the first medium and rejects heat to the third medium, and
wherein the fourth medium rejects heat to the first medium and rejects heat to the third medium.
25. The airplane of claim 22 , wherein the first medium receives heat from the second medium and receives heat from the fourth medium.
26. An airplane comprising:
a pressurized volume is configured to provide a first medium; and
an air conditioning system comprising:
a first heat exchanger configured to transfer heat from a second medium to the first medium,
a second heat exchanger configured to transfer heat from the second medium to a third medium,
a third heat exchanger configured to transfer heat from a fourth medium to the first medium, and
a fourth heat exchanger configured to transfer heat from the fourth medium to the third medium.
27. The airplane of claim 26 , wherein the first heat exchanger is upstream of the third heat exchanger in a flow path of the first medium.
28. The airplane of claim 26 , wherein the first heat exchanger is upstream of the second heat exchanger in a flow path of the second medium.
29. The airplane of claim 26 , wherein the third heat exchanger is upstream of the forth heat exchanger in a flow path of the fourth medium.