An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.
SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM
2020-01-02
Patent
Elektronische Ressource
Englisch
Simultaneous dual engine bleed thermal management system
Europäisches Patentamt | 2020
|SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM
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