Advanced environmental control system in an integrated split pack arrangement with two bleed/outflow heat exchangers
AssigneeHamilton Sunstrand Corporation
InventorsGregory L. DeFrancesco, Donald E. Army
Life of this patent
Estimating the term…
Abstract
An environmental control system for providing conditioned air to a volume of an aircraft includes a ram air circuit including a ram air shell with 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. A plurality of mediums is receivable within the environmental control system. A first medium of the plurality of mediums is provided from the volume of the aircraft via at least one valve.
Claims19
An environmental control system for providing conditioned air to a volume of an aircraft, comprising:
- a ram air circuit including a ram air shell having at least one heat exchanger positioned therein;
- a dehumidification system arranged in fluid communication with the ram air circuit;
- at least one compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, the at least one compressing device including a first compressing device and a second compressing device, the first compressing device and the second compressing device are arranged adjacent a first side of a structural beam of the aircraft and the ram air circuit being mounted adjacent a second, opposite side of the structural beam, each of the first and second compressing devices including:
- a compressor and at least one turbine operably coupled via a shaft;
- and
- a fan operably coupled to the ram air circuit, the fan being located remotely from the shaft;
- and
- a plurality of mediums receivable within the environmental control system, the plurality of mediums including a first medium, a second medium, and a third medium, wherein a first flow of the third medium is receivable from the volume of the aircraft via a first conduit and a first valve and a second flow of the third medium is receivable from the volume of the aircraft via a second conduit and a second valve, the first conduit extending from the volume of the aircraft at a first position and the second conduit extending from the volume of the aircraft at a second position, different from the first position, the first valve and the second valve being operable independently, wherein the first flow of the third medium is provided to the at least one turbine of the first compressing device and is exhausted from the at least one turbine of the first compressing device into the ram air circuit and the second flow of the third medium is provided to the at least one turbine of the second compressing device and is exhausted from the at least one turbine of the second compressing device into the ram air circuit.
Dependencies are inferred from the claim text.