METHOD AND SYSTEMS FOR BLEED AIR SUPPLY

• US 20100326089A1
• Filed: 06/30/2009
• Published: 12/30/2010
• Est. Priority Date: 06/30/2009
• Status: Active Grant

• Current Assignee: GE Aviation Systems LLC (GE Aerospace)
• Original Assignee: GE Aviation Systems LLC (GE Aerospace)
• Inventors: Hightower, Peter C., Weber, Kent, Burie, Bradley J., Kyriazopoulos, Athanasios
• Granted Patent: US 8,267,122 B2
• Time in Patent Office: Days
• US Class Current: 60/783
• CPC Class Codes: F01D 17/145 by means of valves, e.g. for steam turbines valves in general F16K
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F05D 2260/601 using an ejector or a jet pump
• CPC Class Codes: F16K 11/22 with an actuating member for each valve, e.g. interconnected to form multiple-way valves
• CPC Class Codes: Y10T 137/0396 Involving pressure control
• CPC Class Codes: Y10T 137/87619 With selectively operated flow control means in inlet
• CPC Class Codes: Y10T 137/87627 Flow control means is located in aspirated fluid inlet
• CPC Class Codes: Y10T 137/87684 Valve in each inlet

Abstract

A method and system for an integrated ejector valve assembly is provided. The integrated ejector valve assembly includes a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port, a second valve assembly configured to control a flow of relatively higher pressure fluid from a second inlet port, a first actuation chamber configured to close the first valve assembly, a second actuation chamber configured to close the second valve assembly, and a third actuation chamber configured to open the second valve assembly.

Claims

1. An integrated ejector valve assembly comprising:

a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port;

a second valve assembly configured to control a flow of relatively higher pressure fluid from a second inlet port;

a first actuation chamber configured to close said first valve assembly;

a second actuation chamber configured to close said second valve assembly; and

a third actuation chamber configured to open said second valve assembly.

2. An assembly in accordance with claim 1, wherein said first valve assembly comprises a poppet valve.

3. An assembly in accordance with claim 1, wherein said second valve assembly comprises a pintle valve.

4. An assembly in accordance with claim 1, further comprising an ejector configured to use the flow of relatively higher pressure fluid to facilitate increasing the flow of relatively lower pressure fluid.

5. An assembly in accordance with claim 1, further comprising a first manifold comprising a plurality of passages configured to control a pressure in said first actuation chamber.

6. An assembly in accordance with claim 1, further comprising a second manifold comprising a plurality of passages configured to control a differential pressure between said second actuation chamber and said third actuation chamber.

7. An assembly in accordance with claim 1, wherein said first valve assembly is configured to maintain a pressure at an outlet of said integrated ejector valve assembly greater than a first predetermined range of pressure, said second valve assembly is configured to maintain a pressure at the outlet of said integrated ejector valve assembly greater than a second predetermined range of pressure, wherein the first range of pressure is greater than the second range of pressure, and wherein the first and second ranges do not overlap.

8. A method of supplying engine bleed air to an aircraft using a first integrated ejector valve assembly, said method comprising:

controlling a flow of a relatively lower pressure fluid received at the first integrated ejector valve assembly using a first valve assembly;

controlling a flow of a relatively higher pressure fluid received at the first integrated ejector valve assembly using a second valve assembly; and

maintaining a pressure in an outlet of the first integrated ejector valve assembly using the controlled flow of relatively lower pressure fluid and the controlled flow of relatively higher pressure fluid.

9. A method in accordance with claim 8, further comprising receiving at least one of the flow of the relatively lower pressure fluid and the flow of the relatively higher pressure fluid from a bleed port on a gas turbine engine.

10. A method in accordance with claim 8, wherein controlling a flow of a relatively lower pressure fluid further comprises aspirating the flow of relatively lower pressure fluid through an ejector positioned within the first integrated ejector valve assembly using the flow of relatively higher pressure fluid.

11. A method in accordance with claim 8, further comprising biasing at least one of the first valve assembly and the second valve assembly based on the outlet flow from the first integrated ejector valve assembly.

12. A method in accordance with claim 8, further comprising supplying a portion of the engine bleed air to an aircraft using a second integrated ejector valve assembly.

13. A method in accordance with claim 8, further comprising coupling an outlet of a second integrated ejector valve assembly to an outlet of the first integrated ejector valve assembly.

14. A method in accordance with claim 8, wherein supplying engine bleed air to an aircraft comprises:

supplying engine bleed air to an aircraft using a first integrated ejector valve assembly to supply a first portion of the engine bleed air and a second integrated ejector valve assembly to supply a second portion of the engine bleed air;

measuring the flow of the first portion and the flow of the second portion; and

adjusting the flow of at least one of the first portion and the second portion such that the flow of the first portion and the second portion are substantially equal.

15. An aircraft system comprising:

a first gas turbine engine comprising a first high pressure bleed port and a first low pressure bleed port;

a second gas turbine engine comprising a second high pressure bleed port and a second low pressure bleed port;

an engine bleed air header configured to channel bleed air at a selectable pressure to the aircraft;

a first integrated ejector valve assembly coupled in flow communication between said first high pressure bleed port and first low pressure bleed port, and said engine bleed air header;

a second integrated ejector valve assembly coupled in flow communication between said second high pressure bleed port and second low pressure bleed port, and said engine bleed air header; and

a controller communicatively coupled to said first integrated ejector valve assembly and said second integrated ejector valve assembly, said controller configured to substantially match an output flow of said first integrated ejector valve assembly and said second integrated ejector valve assembly.

16. A system in accordance with claim 15 wherein at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly includes a first valve assembly configured to maintain a pressure at said engine bleed air header greater than a first predetermined range of pressure and a second valve assembly configured to maintain the pressure at said engine bleed air header greater than a second predetermined range of pressure, wherein the first range of pressure is greater than the second range of pressure, and wherein the first and second ranges do not overlap.

17. A system in accordance with claim 15 wherein at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly includes a bias assembly configured to receive a bias command from said controller, the at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly configured to adjust the output flow of a respective one of at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly using the bias command.

18. A system in accordance with claim 15 wherein at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly includes a bias assembly configured to receive a bias command from said controller, the at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly configured to adjust the output flow of a respective one of at least one of said first integrated ejector valve assembly and said second integrated ejector valve assembly using at least one of an associated first valve assembly and a second valve assembly positioned within said integrated ejector valve assembly.

19. A system in accordance with claim 18 wherein said bias assembly comprises a bias member configured to bias said first valve assembly and said second valve assembly to a closed position.

20. A system in accordance with claim 15 wherein said bias assembly comprises at least one of an electrical and a pneumatic positioning assembly.