| 摘要 |
An aircraft pressurization system, includes an auxiliary compressor (42) for further compressing compressed air received from a low pressure compressor section (22) of a gas turbine engine (10) while the compressed air is below a predetermined pressure level; a bleed passage (40) for fluidically connecting the auxiliary compressor (42) to the low pressure compressor section (22); and an environmental control system (38) coupled to an output of the auxiliary compressor (42) for conditioning the compressed air to a predetermined level. |
