AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM SELECTIVELY POWERED BY THREE BLEED PORTS

摘要

An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports (204, 206, 208) 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 (204, 206, 208) 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.