No primary heat exchanger and bleed air (cabin discharge air) assist
An airplane is provided. The airplane includes a pressurized compartment and an environmental control system. The environmental control system includes a compressing device. The compressing device includes a compressor and a turbine. The airplane also includes a first flow of first medium configured to enter the pressurized compartment and a second flow of the first medium configured to enter the turbine.
1. An airplane comprising:
a pressurized compartment;
an environmental control system comprising a compressing device,
the compressing device comprising a compressor and a turbine;
a first flow of a first medium configured to enter the pressurized compartment; and
a second flow of the first medium configured to enter the turbine,
wherein the environmental control system is configured to operate in a boost cooling mode when a pressure of the first medium is above a cabin pressure and ram air temperatures are unable to cool the first medium to a required temperature,
wherein, in the boost cooling mode, energy is provided to the compressing device by expanding a second flow of the first medium across the turbine.
2. The airplane of claim 1 , wherein the second flow of the first medium is sent overboard after exiting the turbine.
3. The airplane of claim 1 , wherein the first flow of the first medium is configured to enter the compressor.
4. The airplane of claim 1 , wherein the environmental control system comprises a ram air heat exchanger.
5. The airplane of claim 1 , wherein the environmental control system comprises a plurality of compressors that include the compressor, a plurality of turbines that include the turbine, and at least one fan.
6. The airplane of claim 1 , wherein a second medium mixes with the first medium downstream of the turbine.
7. The airplane of claim 6 , wherein the first medium comprises bleed air, and
wherein the second medium comprises recirculation air.
8. The airplane of claim 6 , wherein the environmental control system comprises a high pressure water separator.
9. The airplane of claim 8 , wherein the second medium mixes with the first medium between of the turbine and a condenser of the high pressure water separator.
10. The airplane of claim 1 , wherein the environmental control system is configured to operate in a high pressure mode.
11. The airplane of claim 1 , wherein the environmental control system is configured to operate in a low pressure mode.
12. The airplane of claim 1 , wherein the environmental control system is configured to operate in a pressure boost mode.
13. The airplane of claim 1 , wherein the first flow of the first medium comprises a first portion of bleed air, and
wherein the second flow of the first medium comprises a second portion of bleed air.
14. The airplane of claim 1 , wherein the first flow of the first medium comprises a bleed air and the second flow of the first medium comprises a cabin discharge air.
15. The airplane of claim 1 , wherein the first flow of the first medium comprises air from an electric air compressor, and
wherein the second flow of the first medium comprises a cabin discharge air.
16. The airplane of claim 1 , wherein the first flow of the first medium is a first portion of air from an electric air compressor, and
wherein the second flow of the first medium is a second portion of air from an electric air compressor.
17. The airplane of claim 1 , wherein the compressor comprises at least one of a mixed flow compressor and a variable geometry.
18. The airplane of claim 1 , wherein the first flow enters the compressor prior to entering a ram air heat exchanger.
19. An airplane comprising:
a pressurized compartment;
an environmental control system comprising a compressing device,
the compressing device comprising a compressor and a turbine;
a first flow air configured to enter the pressurized compartment and configured to enter the compressor in accordance with a mode of operation; and
a second flow air configured to enter the turbine and to be sent overboard after exiting the turbine,
wherein the environmental control system is configured to operate in a boost cooling mode when a pressure of the first medium is above a cabin pressure and ram air temperatures are unable to cool the first medium to a required temperature,
wherein, in the boost cooling mode, energy is provided to the compressing device by expanding a second flow of the first medium across the turbine.