IP Library › Granted Patent US 8,267,122
Granted Patent B2
US 8,267,122 · App. 12/495,366 · Granted Sep 18, 2012

Method and systems for bleed air supply

Assignee: GE Aviation Systems LLC
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Quick Facts
Patent No.
US 8,267,122
App. No.
12/495,366
Granted
Sep 18, 2012
Kind
B2
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 (12)

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, said second valve assembly being coaxially aligned with said first valve assembly;

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

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

a third actuation chamber configured to open said second valve assembly; and

an ejector configured to use the flow of relatively higher pressure fluid to facilitate increasing the flow of relatively lower pressure fluid.

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 a first manifold comprising a plurality of passages configured to control a pressure in said first actuation chamber.

5. 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.

6. 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.

Assignments (2)
CORRECTIVE ASSIGNMENT TO CORRECT THE ASSIGNEE'S ADDRESS PREVIOUSLY RECORDED ON REEL 022897 FRAME 0542. ASSIGNOR(S) HEREBY CONFIRMS THE CORRECT ADDRESS OF THE ASSIGNEE IS: GE AVIATION SYSTEMS, LLC, 3290 PATTERSON DRIVE SE, GRAND RAPIDS, MICHIGAN, USA 49512. Recorded Jun 28, 2012
From: WEBER, KENT; KYRIAZOPOULOS, ATHANASIOS; HIGHTOWER, PETER C.; BURIE, BRADLEY J.
To: GE AVIATION SYSTEMS, LLC
Reel/Frame 028458/0913 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jun 30, 2009
From: WEBER, KENT; KYRIAZOPOULOS, ATHANASIOS; HIGHTOWER, PETER C.; BURIE, BRADLEY J.
To: GE AVIATION SYSTEMS LLC
Reel/Frame 022897/0542 →
Continuity (1)
Related Publication 20100326089A1 · Dec 30, 2010