ENHANCED METHOD AND AIRCRAFT FOR PRE-COOLING AN ENVIRONMENTAL CONTROL SYSTEM USING A TWO WHEEL TURBO-MACHINE WITH SUPPLEMENTAL HEAT EXCHANGER

• US 20180057170A1
• Filed: 08/23/2016
• Published: 03/01/2018
• Est. Priority Date: 08/23/2016
• Status: Abandoned Application

• Current Assignee: GE Aviation Systems LLC (GE Aerospace)
• Original Assignee: GE Aviation Systems LLC (GE Aerospace)
• Inventors: Sautron, Dominique Patrick
• Application Number:
  US15/244,086
• Publication Number:
  US 20180057170A1
• Time in Patent Office: Days
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: B64D 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/185 Cooling means for reducing the temperature of the cooling air or gas
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F05D 2220/62 with energy recovery turbines
• CPC Class Codes: F05D 2260/601 using an ejector or a jet pump
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.

Claims

1. A method of providing bleed air to environmental control systems using a gas turbine engine, the method comprising:

determining a bleed air demand for the environmental control systems;

selectively supplying low pressure bleed air and high pressure bleed air from a compressor of the gas turbine engine to a turbine section and compressor section of a turbo air cycle machine, with the turbine section emitting a cooled air stream and the compressor section emitting a compressed air stream;

selectively cooling the compressed air stream; and

combining the cooled air stream emitted from the turbine section and the compressed air stream emitted from the compressor section to form a conditioned air stream;

wherein the selectively supplying and selectively cooling are controlled such that the conditioned air stream satisfies the determined bleed air demand.

2. The method of claim 1 wherein selectively cooling the compressed air stream comprises providing the compressed air stream to a heat exchanger and selectively providing cooler fan air to the heat exchanger as a heat sink for the compressed air stream.

3. The method of claim 1 wherein selectively supplying low pressure bleed air further comprises selectively supplying low pressure bleed air or ambient air to the compressor section.

4. The method of claim 3 wherein selectively supplying low pressure bleed air and ambient air comprises supplying 100% of one of the low pressure bleed air or ambient air and 0% of the other of the low pressure bleed air or ambient air.

5. The method of claim 1 wherein the determining the bleed air demand comprises determining at least one of air pressure or air temperature demand for the environmental control systems.

6. The method of claim 5 wherein the determining the bleed air demand comprises determining both the air pressure and the air temperature demand for the environmental control systems.

7. The method of claim 1 wherein the bleed air demand is a function of at least one of number of aircraft passengers, aircraft flight phase, or operational subsystems of the environmental control systems.

8. The method of claim 1 wherein selectively supplying low pressure and high pressure bleed air comprises supplying 100% of one of the low pressure bleed air or the high pressure bleed air and 0% of the other of the low pressure bleed air or the high pressure bleed air.

9. The method of claim 1 wherein selectively supplying low pressure and high pressure bleed air comprises proportionally supplying the low pressure bleed air and the high pressure bleed air.

10. The method of claim 9 wherein the selectively supplying the low pressure bleed air and the high pressure bleed air is a function of an aircraft flight phase.

11. The method of claim 1 wherein selectively supplying low pressure and high pressure bleed air comprises continuously selectively supplying the low pressure bleed air and the high pressure bleed air.

12. An aircraft comprising:

an environmental control system having a bleed air inlet;

a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply;

a turbo air cycle machine having rotationally coupled turbine section and compressor section;

an upstream turbo-ejector fluidly coupling the low pressure bleed air supply and the high pressure bleed air supply to the turbine section and compressor section;

a downstream turbo-ejector fluidly combining fluid outputs from the turbine section and compressor section into a common flow that is supplied to the bleed air inlet of the environmental control system; and

a heat exchanger having a hot side fluidly coupled between the compressor section and the downstream turbo-ejector.

13. The aircraft of claim 12 wherein the heat exchanger comprises a cool side selectively fluidly coupled to a cool fan air supply of the gas turbine engine.

14. The aircraft of claim 13, further comprising a fan air valve fluidly coupled between the cool fan air supply and the heat exchanger.

15. The aircraft of claim 12, further comprising a source valve fluidly coupling an ambient air supply to the low pressure bleed air supply in the upstream turbo-ejector.

16. The aircraft of claim 15 wherein the upstream turbo-ejector is configured to simultaneously supply the low pressure bleed air supply to the turbine section.

17. The aircraft of claim 16, further comprising a controller module configured to controllably operate at least one of the upstream turbo-ejector, downstream turbo-ejector, heat exchanger, fan air valve, or source valve.

18. A method of providing air to an environmental control systems of an aircraft, the method comprising:

selectively supplying ambient air and low pressure bleed air and high pressure bleed air from a compressor of a gas turbine engine to a turbo air cycle machine to precondition the ambient air and bleed air according to operational demands of the environmental control systems.

19. The method of claim 18 wherein preconditioning comprises compressing one of ambient air or low pressure bleed air to form a compressed air stream.

20. The method of claim 19 wherein preconditioning comprises selectively cooling the compressed air stream.