# US 2014/0196469 A1 · Low pressure compressor bleed exit for an aircraft pressurization system

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- Number: US 2014/0196469 A1
- Document ID: US20140196469A1
- Status: Published application
- Kind: A1
- Application number: 14/212,136
- Filed: 2014-03-14
- Published: 2014-07-17
- Earliest claimed: 2011-08-11
- Assignees: Hamilton Sundstrand Corporation
- Applicants: Hamilton Sundstrand Corporation
- Inventors: Adam M. Finney; Louis J. Bruno
- Web page: https://patentgrep.com/patent/US20140196469A1

## CPC

- B64D 13/02: the air being pressurised
- B64D 13/06: the air being conditioned (pressurising B64D13/02)
- B64D 2013/0618: {with arrangements for reducing or managing bleed air, using another air source, e.g. ram air}
- Y02T 50/50: On board measures aiming to increase energy efficiency
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 1

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.

### Claim 2 (depends on 1)

The aircraft environmental control system of claim 1, further comprising a valve downstream of the bleed port configured to divert at least a portion of the high pressure engine air to an auxiliary compressor.

### Claim 3 (depends on 2)

The aircraft environmental control system of claim 2, wherein the valve is configured to direct all of the high pressure engine air to the auxiliary compressor.

### Claim 4 (depends on 2)

The aircraft environmental control system of claim 2, wherein the valve is configured to direct none of the high pressure engine air to the auxiliary compressor.