Simultaneous dual engine bleed thermal management system

1. An environmental control system of an aircraft comprising:

at least one heat exchanger;

a compression device arranged in fluid communication with the at least one heat exchanger, the compression device including a plurality of components including a first component and a second component coupled by a shaft;

a first bleed port arranged in fluid communication with the first component; and

a second bleed port, distinct from the first bleed port, arranged in fluid communication with the second component;

wherein the at least one heat exchanger includes a first precooler arranged upstream from the first component and a second precooler arranged upstream from the second component, and ram air is arranged in a heat exchange relationship with a first medium provided from the first bleed port in the first precooler;

wherein the environmental control system is operable in a first mode and a second mode, and during operation in the second mode, fluid from the first bleed port is provided to the first component and fluid from the second bleed port is provided to the second component simultaneously.

2. The environmental control system of claim 1 , wherein a first medium drawn from the first bleed port has a first pressure and a second medium drawn from the second port has a second pressure, the second pressure being higher than the first pressure.

3. The environmental control system of claim 1 , wherein at least one of the first bleed port and the second bleed port is in fluid communication with an engine of the aircraft.

4. The environmental control system of claim 3 , wherein at least one of the first bleed port and the second bleed port is arranged in fluid communication with a low pressure spool of a compressor of the engine.

5. The environmental control system of claim 1 , wherein at least one of the first bleed port and the second bleed port is in fluid communication with an auxiliary power unit of the aircraft.

6. The environmental control system of claim 1 , wherein the first component is a compressor and the second component is a turbine.

7. The environmental control system of claim 4 , wherein the plurality of components of the compression device further includes another turbine arranged downstream from and in fluid communication with the compressor.

8. The environmental control system of claim 1 , wherein the environmental control system is operable in a first mode during conditions with a medium or high engine power setting and/or a low environmental control system demand.

9. The environmental control system of claim 8 , wherein conditions with a medium or high engine power setting and/or a low environmental control system demand include at least one of a cruise and climb of the aircraft.

10. The environmental control system of claim 1 , wherein during operation of the environmental control system in the first mode, fluid from the first bleed port is provided to the first component, but no fluid from the second bleed port is provided to the second component.

11. The environmental control system of claim 1 , wherein the environmental control system is operable in a second mode during conditions with a low engine power setting and/or a high environmental control system demand.

12. The environmental control system of claim 11 , wherein conditions with a medium or high engine power setting and/or a low environmental control system demand include engine idle conditions including taxi, or descent.

13. The environmental control system of claim 1 , wherein the at least one heat exchanger includes a secondary heat exchanger is positioned downstream from the compressor.

14. The environmental control system of claim 1 , wherein ram air is arranged in a heat exchange relationship with a second medium provided from the second bleed port in the second precooler.

15. The environmental control system of claim 1 , wherein the second bleed port is selectively operable to tune a flow of fluid provided to the compression device.