Aircraft environmental control system selectively powered by three bleed reports
AssigneeHamilton Sundstrand Corporation
InventorsLouis J. Bruno, Thomas M. Zywiak
Life of this patent
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Abstract
An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.
Claims17
An engine compressor bleed system of an engine for an aircraft is provided, comprising:
- a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft, wherein a first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.
A method of operating a compressor bleed supply system of an engine for an aircraft, comprising:
- identifying a flight condition of the aircraft;
- and
- selecting one of a plurality of pressure ports configured to supply bleed air to satisfy a cooling load for the aircraft, wherein a first pressure port of the plurality of pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.
Dependencies are inferred from the claim text.