An environmental control system (30) of a gas turbine engine (210) includes a higher pressure tap (34) at a higher pressure location (134) in a compressor section (254), and a lower pressure tap (32) at a lower pressure location (132). The lower pressure tap (32) communicates to a first passage (36) leading to a downstream outlet (44) and has a second passage leading into a compressor section (54) of a turbocompressor (60). The higher pressure tap (34) air drives the turbine section (52) of the turbocompressor (60) to in turn drive the compressor section (54) of the turbocompressor (60). A combined outlet (62) of the compressor section (54) and the turbine section (52) of the turbocompressor (60) intermixes and passes air downstream to be delivered to an aircraft use (152). The higher pressure tap (34) extends above a plane including the lowermost surface (216) of a pylon (214) that supports the engine (210). The higher pressure tap (34) includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon (214).
LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT
NIEDERDRUCK- KLIMAREGELUNGSSYSTEM MIT SICHEREM PYLONÜBERGANG
SYSTÈME DE COMMANDE ENVIRONNEMENTAL DE BASSE PRESSION À SÉCURITÉ DE TRANSIT DE PYLÔNE
2023-10-25
Patent
Elektronische Ressource
Englisch
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