Geared turbofan engine equipped with a low pressure system for monitoring the environment of the aircraft

摘要

A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system (30) includes a higher pressure tap (34) at a higher pressure location in the main compressor section, and a lower pressure tap (32) at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap (32) communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor (42). The higher pressure tap (34) leads into a turbine section of the turbocompressor (42) such that air in the higher pressure tap (34) drives the turbine section to in turn drive the compressor section of the turbocompressor (42). The pylon includes a lowermost surface and the higher pressure tap (34) does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor (42) intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed.