US5036657A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual manifold fuel system
Assignee: General Electric Co
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Filing: 1989-10-19
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Granted: 1991-08-06
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Expires: 2009-10-19
Abstract
Abstract A dual manifold fuel supply system for the combustor of gas generator in a turbofan engine wherein alternating circumferentially aligned fuel injectors are alternately supplied with fuel by a first or second fuel manifold. Fuel flow to both manifolds are controlled by a fuel control, preferably a full authority digital electronic control, and the second manifold has an off valve interposed between it and the fuel control.
Inventors
- 👤 Stanford P. T. Seto
- 👤 Richard E. Stenger
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 09:11
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; F02C7/228; F02C7/222
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
83 words
A fuel injection system for use in the combustor section of a gas turbine engine said fuel injection system comprising: a plurality of generally downstream facing fuel nozzles wherein a portion of said fuel nozzles are connected to a shutoff valve means which is interruptible, a means for interrupting said valve means in response to a control signal, and a means for generating said control signal based on the gas turbine engine fuel to air ratio and an overriding weight on wheels signal.
Claim 2
Dependent Claim
83 words
A fuel injection system for use in the combustor section of a gas turbine engine said fuel injection system comprising: a plurality of generally downstream facing fuel nozzles wherein a portion of said fuel nozzles are connected to a shutoff valve means which is interruptible, a means for interrupting said valve means in response to a control signal, and a means for generating said control signal based on the gas turbine engine fuel to air ratio and an overriding weight on wheels signal.
Claim 3
Dependent Claim
96 words
A fuel injection system for use in the combustor section of a gas turbine engine said fuel injection system comprising: first and second fuel lines, first and second pluralities of generally downstream facing fuel nozzles in fluid supply communication with said first and second fuel lines respectively, a shutoff valve interposed in said first fuel line, a means for shutting on and off said valve in response to a control signal; and a means for generating said control signal based upon the gas turbine engine fuel to air ratio and an overriding weight on wheels signal.
Claim 4
Dependent Claim
96 words
A fuel injection system for use in the combustor section of a gas turbine engine said fuel injection system comprising: first and second fuel lines, first and second pluralities of generally downstream facing fuel nozzles in fluid supply communication with said first and second fuel lines respectively, a shutoff valve interposed in said first fuel line, a means for shutting on and off said valve in response to a control signal; and a means for generating said control signal based upon the gas turbine engine fuel to air ratio and an overriding weight on wheels signal.
Claim 5
Dependent Claim
34 words
A fuel injection system as set forth in claim 2 comprising: first and second fuel manifolds disposed between said first and second fuel lines and said first and second pluralities of fuel nozzles respectively.
Claim 6
Dependent Claim
28 words
A fuel injection system as set forth in claim 3 wherein: said first and second pluralities of fuel nozzles are arranged in a generally circular and alternating pattern.
Claim 7
Dependent Claim
24 words
A fuel injection system as set forth in claim 4 including: a fuel control in supply communication with said first and second fuel lines.
Claim 8
Dependent Claim
32 words
A fuel injection system as set forth in claim 5 wherein said means for generating said control signal is an electronic engine control which controls said shutoff valve and said fuel control.
Claim 9
Dependent Claim
21 words
A fuel injection system as set forth in claim 6 wherein: said electronic engine control is a digital electronic engine control.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1994-08-05 | 1995-02-04 | 1995-08-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1998-08-05 | 1999-02-04 | 1999-08-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2002-08-05 | 2003-02-04 | 2003-08-06 | $7700.00 | Window Closed / Lapsed |