US5345757A
Expired / Lapsed
US
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Combustor apparatus for use in a gas turbine engine
Assignee: General Electric Co
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Filing: 1993-09-20
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Granted: 1994-09-13
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Expires: 2013-09-20
Abstract
Abstract A combustor apparatus is provided for a gas turbine engine including a circumferential ring of injectors. A fuel manifold provides a source of fuel for the injectors. The combustor apparatus includes a plurality of first fuel flow paths between the manifold and all of the injectors. Fuel is provided to all of the injectors via these first flow paths. At least one second fuel flow path including an electronically switchable valve is coupled between the manifold and a selected one of the injectors to provide additional fuel thereto at certain times when special engine operating conditions, such as demand for initial ignition, crossfire and altitude relight are sensed.
Inventors
- 👤 Thomas L. MacLean
- 👤 Richard W. Stickles
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 06:59
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; F02C9/00; F02C9/26; F02C9/28; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/09; F05D2270/092
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
142 words
A combustor apparatus for a gas turbine engine comprising: a plurality of injectors situated in said engine; a fuel manifold for supplying fuel to said injectors; a plurality of first fuel flow paths coupling said manifold to said plurality of injectors to provide fuel thereto; at least one second fuel flow path for switchably coupling said manifold to at least one of said injectors to supply additional fuel thereto, not every one of said injectors having said second fuel flow path so coupled; sensing means coupled to said engine for determining if a predetermined engine condition is present, and electronic control means, coupled to said sensing means and said second fuel flow path, for switching said second fuel path to provide additional fuel to said at least one of said injectors when said sensing means determines that a predetermined engine condition exists.
Claim 2
Dependent Claim
142 words
A combustor apparatus for a gas turbine engine comprising: a plurality of injectors situated in said engine; a fuel manifold for supplying fuel to said injectors; a plurality of first fuel flow paths coupling said manifold to said plurality of injectors to provide fuel thereto; at least one second fuel flow path for switchably coupling said manifold to at least one of said injectors to supply additional fuel thereto, not every one of said injectors having said second fuel flow path so coupled; sensing means coupled to said engine for determining if a predetermined engine condition is present, and electronic control means, coupled to said sensing means and said second fuel flow path, for switching said second fuel path to provide additional fuel to said at least one of said injectors when said sensing means determines that a predetermined engine condition exists.
Claim 3
Dependent Claim
14 words
The combustor apparatus of claim 1 wherein said first fuel paths include respective valves.
Claim 4
Dependent Claim
27 words
The combustor apparatus of claim 1 wherein each second fuel path includes a solenoid valve which is coupled to said electronic control means and switchably controlled thereby.
Claim 5
Dependent Claim
20 words
The combustor apparatus of claim 1 wherein only one of said injectors has attached thereto said second fuel flow path.
Claim 6
Dependent Claim
20 words
The combustor apparatus of claim 1 wherein only two of said injectors has attached thereto said second fuel flow paths.
Claim 7
Dependent Claim
22 words
The combustor apparatus of claim 1 wherein only every other one of said injectors has attached thereto said second fuel flow paths.
Claim 8
Dependent Claim
126 words
A combustor apparatus for a gas turbine engine comprising: a plurality of injectors situated in said engine; a fuel manifold for supplying fuel to said injectors; a plurality of first fuel flow paths coupling said manifold to said plurality of injectors to provide fuel thereto; second fuel flow paths for switchably coupling said manifold to only every other one of said injectors to supply additional fuel thereto; sensing means coupled to said engine for determining if a predetermined engine condition is present, and electronic control means, coupled to said sensing means and said second fuel flow paths, for switching said second fuel paths to provide additional fuel to said every other one of said injectors when said sensing means determines that a predetermined engine condition exists.
Claim 9
Dependent Claim
126 words
A combustor apparatus for a gas turbine engine comprising: a plurality of injectors situated in said engine; a fuel manifold for supplying fuel to said injectors; a plurality of first fuel flow paths coupling said manifold to said plurality of injectors to provide fuel thereto; second fuel flow paths for switchably coupling said manifold to only every other one of said injectors to supply additional fuel thereto; sensing means coupled to said engine for determining if a predetermined engine condition is present, and electronic control means, coupled to said sensing means and said second fuel flow paths, for switching said second fuel paths to provide additional fuel to said every other one of said injectors when said sensing means determines that a predetermined engine condition exists.
Claim 10
Dependent Claim
14 words
The combustor apparatus of claim 7 wherein said first fuel paths include respective valves.
Claim 11
Dependent Claim
30 words
The combustor apparatus of claim 7 wherein each of said second fuel paths includes a solenoid valve which is coupled to said electronic control means and is switchably controlled thereby.
References Cited (Backward Citations)
US3335567A
Cited
US3426527A
Cited
US4157012A
Cited
US4499735A
Cited
US4656827A
Cited
US4711085A
Cited
US4833878A
Cited
US4802334A
Cited
US5187936A
Cited
US5184457A
Cited
US5242117A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-09-12 | 1998-03-14 | 1998-09-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-09-12 | 2002-03-14 | 2002-09-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-09-12 | 2006-03-14 | 2006-09-13 | $7700.00 | Window Closed / Lapsed |