Advanced environmental control system in an integrated split pack arrangement with one bleed/outflow heat exchanger
An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. The at least one compressing device includes a turbine and a compressor operably coupled via a shaft. A fan is operably coupled to the ram air circuit. At least one compressing device is arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from the axis of the shaft.
1. An environmental control system of an aircraft, comprising:
a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, the at least one heat exchanger including a first heat exchanger and a second heat exchanger;
a dehumidification system arranged in fluid communication with the ram air circuit;
a first compressing device and a second compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, each of the first compressing device and the second compressing device including a turbine and a compressor operably coupled by a shaft; and
a fan operably coupled to the ram air circuit to move air across the first heat exchanger and the second heat exchanger sequentially, wherein the first compressing device and the second compressing device are arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from an axis of the shaft of both the first compressing device and the second compressing device;
wherein the ram air circuit is mounted adjacent a first side of a structural beam of the aircraft and the first compressing device and the second compressing device are arranged adjacent a second, opposite side of the structural beam.
2. The environmental control system of claim 1 , wherein the ram air circuit is mounted in a first bay of the aircraft and the first compressing device and the second compressing device are mounted in a second bay of the aircraft, the first bay and the second bay being different.
3. The environmental control system of claim 1 , wherein the fan is a tip turbine fan.
4. The environmental control system of claim 1 , wherein the first compressing device and the second compressing device are arranged in parallel.
5. The environmental control system of claim 4 , further comprising at least one valve operable to control a flow of a medium to the first compressing device and the second compressing device.
6. The environmental control system of claim 5 , wherein in a first position, the at least one valve is configured to direct the flow of the medium to only a portion of the first compressing device and the second compressing device.
7. The environmental control system of claim 6 , wherein in a second position, the at least one valve is configured to direct the flow of the medium to each of the first compressing device and the second compressing device.
8. The environmental control system of claim 1 , wherein the ram air circuit includes a plurality of independent outlets formed in the shell.
9. The environmental control system of claim 8 , wherein at least one outlet is associated with each of the first compressing device and the second compressing device.
10. The environmental control system of claim 6 , wherein the turbine of at least one of the first compressing device and the second compressing device includes:
a first inlet and a second inlet and configured to provide energy by expanding one or more mediums, the first inlet being configured to receive a first medium of the one or more mediums and the second inlet being configured to receive a second medium of the one or more mediums.
11. The environmental control system of claim 10 , wherein the compressor of at least one of the first compressing device and the second compressing device is configured to receive energy from at least one of the first medium and the second mediums being expanded across the turbine, the compressor being configured to compress the second medium.
12. The environmental control system of claim 10 , wherein the environmental control system is operable in a plurality of modes, and during operation in at least one of the plurality of modes, the first medium and the second medium are mixed within the turbine.
13. The environmental control system of claim 10 , wherein the environmental control system is operable in a plurality of modes, and during operation in at least one of the plurality of modes, the first medium and the second medium are mixed downstream from the turbine.
14. The environmental control system of claim 10 , wherein the first medium is bleed air and the second medium is fresh air.
15. The environmental control system of claim 10 , wherein at least one of the first compressing device and the second compressing device further includes a power turbine configured to provide energy to the compressor by expanding a third medium of the one or more mediums.
16. The environmental control system of claim 15 , wherein the third medium of the one or more mediums is cabin discharge air provided from a pressurized area of the aircraft.
17. The environmental control system of claim 15 , wherein the third medium is supplied from the pressurized area of the aircraft via a single valve.
18. The environmental control system of claim 1 , further comprising a bleed air circuit for providing air to at least one of the first compressing device and the second compressing device wherein the bleed air circuit is operably coupled to a first engine, a second engine, and an auxiliary power unit.