Shoestring environmental control system for an aircraft
An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a flow of a first medium and a turbine configured to receive the flow of the first medium from the compressor and a flow of a second medium. The turbine is arranged downstream from the compressor along a flow path of the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is operable configured to divert the flow of the first medium around the turbine and at least a portion of the dehumidification system.
1. An environmental control system of an aircraft comprising:
a compressing device including a turbine configured to receive a flow of a first medium and a flow of a second medium and a compressor configured to receive the flow of the second medium, the turbine being arranged downstream from the compressor along a flow path of the second medium;
a dehumidification system in fluid communication with the turbine, the dehumidification system being arranged upstream from the turbine along a flow path of the first medium; and
a bypass valve selectively operable to divert the flow of the first medium around the dehumidification system and the turbine.
2. The environmental control system of claim 1 , wherein the turbine has a first inlet and a second inlet, the flow of the first medium being arranged in fluid communication with one of the first inlet and the second inlet, and the flow of the second medium being arranged in fluid communication with the other of the first inlet and the second inlet.
3. The environmental control system of claim 2 , wherein the flow of the first medium mixes with the flow of the second medium at an exit of the turbine.
4. The environmental control system of claim 1 , wherein the first medium is bleed air.
5. The environmental control system of claim 1 , wherein the second medium is cabin recirculation air.
6. The environmental control system of claim 4 , wherein the bleed air is drawn from at least one of an engine and an auxiliary power unit of the aircraft.
7. The environmental control system of claim 1 , wherein the environmental control system is operable in a plurality of modes including a first mode and a second mode.
8. The environmental control system of claim 7 , wherein the environmental control system is operable in the first mode when an ambient temperature is at or above a design point of the environmental control system.
9. The environmental control system of claim 7 , wherein the environmental control system is operable in the second mode when an ambient temperature is below a design point of the environmental control system.
10. The environmental control system of claim 7 , wherein the bypass valve is in a closed position during operation in the first mode and the bypass valve is in an open position during operation in the second mode.
11. The environmental control system of claim 1 , wherein a mixture of the flow of the first medium and the flow of the second medium is provided to a load, and the bypass valve is operable to control a temperature of the mixture of the flow of the first medium and the flow of the second medium provided to the load.
12. The environmental control system of claim 1 , further comprising a ram air circuit including a ram air shell having at least one heat exchanger positioned therein.
13. The environmental control system of claim 12 , wherein the compressing device includes a fan operably coupled to the compressor and the turbine via a shaft, the fan being arranged in fluid communication with the ram air circuit.
14. The environmental control system of claim 12 , wherein the at least one heat exchanger includes a first heat exchanger and a second heat exchanger.