Single stage engine bleed

Patent metadata

Field	Value
Publication number	US-2016107754-A1
Application number	US-201514944479-A
Country	US
Kind code	A1
Filing date	Nov 18, 2015
Priority date	Aug 21, 2013
Publication date	Apr 21, 2016
Grant date	—

Abstract

An environmental control system is provided. The environmental control system may receive pressurized air from a single supply line. A pressure regulating turbomachine may be located within the supply line. A motor-generator may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator.

First claim

1 . An environmental control system comprising:
a pressure regulating turbomachine located within a supply line, wherein a location of the supply line is selected such that a minimum pressure in the supply line is less than a desired pressure in the environmental control system, and wherein a maximum pressure in the supply line is greater than the desired pressure in the environmental control system; and a motor-generator coupled to the pressure regulating turbomachine, wherein the pressure regulating turbomachine is configured to supply energy to the motor-generator, and wherein the motor-generator is configured to supply energy to the pressure regulating turbomachine.

2 . The environmental control system of claim 1 , wherein the pressure regulating turbomachine is configured to supply energy to the motor-generator in response to a pressure in the supply line being greater than the desired pressure in the environmental control system.

3 . The environmental control system of claim 1 , wherein the motor-generator is configured to supply energy to the pressure regulating turbomachine in response to a pressure in the supply line being less than the desired pressure of the environmental control system.

4 . The environmental control system of claim 1 , further comprising a precooler in fluid communication with the pressure regulating turbomachine.

5 . The environmental control system of claim 1 , further comprising a primary generator coupled to the motor-generator.

6 . The environmental control system of claim 1 , wherein the supply line receives pressurized air from a high pressure compressor in a gas turbine engine.

7 . The environmental control system of claim 1 , wherein the environmental control system consists of only one supply line.

8 . The environmental control system of claim 1 , further comprising at least one of a downstream pressure sensor and an upstream pressure sensor.

9 . An aircraft environmental control system comprising:
a gas turbine engine including a compressor and a primary generator; a supply line coupled to the compressor, wherein a pressure in the supply line is less than a desired pressure in the aircraft environmental control system during idle, and wherein the pressure in the supply line is greater than the desired pressure in the aircraft environmental control system during cruise; a pressure regulating turbomachine located within the supply line; and a motor-generator coupled to the pressure regulating turbomachine and the primary generator.

10 . The aircraft environmental control system of claim 9 , wherein the pressure regulating turbomachine is configured to function as a compressor and a turbine.

11 . The aircraft environmental control system of claim 9 , wherein the motor-generator is configured to supplement power supplied by the primary generator in response to a pressure in the supply line being greater than the desired pressure in the aircraft environmental control system.

12 . The aircraft environmental control system of claim 9 , wherein the motor-generator is configured to drive the pressure regulating turbomachine as a compressor in response to a pressure in the supply line being less than the desired pressure in the aircraft environmental control system.

13 . The aircraft environmental control system of claim 9 , further comprising a precooler downstream of the pressure regulating turbomachine.

14 . The aircraft environmental control system of claim 9 , wherein the aircraft environmental control system comprises only one supply line.

15 . An aircraft power distribution system comprising:
a primary aircraft power distribution system comprising a primary generator coupled to an engine gearbox; and a secondary aircraft power distribution system comprising:
a pressure regulating turbomachine located within a supply line, wherein a pressure in the supply line is less than a desired pressure in an environmental control system during idle, and wherein the pressure in the supply line is greater than the desired pressure in the environmental control system during cruise; and
a motor-generator coupled to the pressure regulating turbomachine,
wherein the motor-generator is configured to produce power that is supplied to the primary aircraft power distribution system through the secondary aircraft power distribution system, and wherein the motor-generator is configured to supply power from the primary aircraft power distribution system to the pressure regulating turbomachine.

16 . The aircraft power distribution system of claim 15 , wherein the motor-generator is configured to produce power that is supplied to the primary aircraft power distribution system in response to a pressure in the environmental control system being greater than the desired pressure in the environmental control system.

17 . The aircraft power distribution system of claim 15 , wherein the motor-generator is configured to supply power from the primary aircraft power distribution system to the pressure regulating turbomachine in response to a pressure in the environmental control system being less than the desired pressure in the environmental control system.

18 . The aircraft power distribution system of claim 15 , wherein the environmental control system consists of a single supply line.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Ronan Michael

Classifications

• B64D2013/0648

  with energy recovery means, e.g. using turbines · CPC title

• B64D2013/0644

  including electric motors or generators · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title