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US 2014/0196469 A1Published application
Low pressure compressor bleed exit for an aircraft pressurization system
AssigneeHamilton Sundstrand Corporation
InventorsAdam M. Finney, Louis J. Bruno
Life of this patent
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Abstract
An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level.
Claims4
An aircraft environmental control system comprising:
- a multi-spool turbine engine having at least one low pressure spool and at least one high pressure spool;
- a bleed port located on a low pressure compressor of the low pressure spool;
- a bleed air passage configured to deliver high pressure engine air from the bleed port of the low pressure compressor to an environmental control system.
Dependencies are inferred from the claim text.