US5896741A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Low emission combustion system for a gas turbine engine
Assignee: Solar Turbines Inc
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Filing: 1996-10-22
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Granted: 1999-04-27
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Expires: 2016-10-22
Abstract
Abstract The control systems for reducing NOx in the combustion systems of past gas turbine engines has incorporated a variety of expensive and complicated techniques to reduce the NOx level. For example, such systems use schemes for introducing more air into the primary combustion zone, recirculating cooled exhaust products into the combustion zone and injecting water spray into the combustion zone. The present system reduces the formation of NOx within the combustion zone by controlling the air/fuel ratio and more explicitly by controlling the air portion of the air/fuel ratio. The present system includes a device for directing a portion of the flow of compressed air exiting a compressor section into an injection nozzle and into a combustor, a device for reducing the flow of compressed air into the combustor. The system monitors an engine parameter, such as a power turbine inlet gas temperature, sends a signal to a computer which interpreters the signal and directs a second signal to a power cylinder which causes a throttling mechanism to move between an open position and a closed position depending on the temperature of the gases. The system provides an economical, reliable and effective method for reducing and controlling the amount of nitrogen oxide, carbon monoxide and unburned hydrocarbon emitted from the gas turbine engine.
Inventors
- 👤 Colin J. Etheridge
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 08:46
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F02; F02C; F02C9/00; F02C9/16; F02C9/18; F23R3/02; F23R3/26; F05; F05D; F05D2270/00; F05D2270/30; F05D2270/303
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
315 words
A gas turbine engine having an exhaust being emitted therefrom and a control system for reducing the formation of exhaust emissions during operation of a gas turbine engine, the engine including a source of compressed air, a combustor defining an outer shell and an inner shell being coaxially positioned about the outer shell, an inlet end portion having a opening therein and a turbine arranged in serial order, a fuel injection nozzle being positioned in the opening in the inlet end portion of the combustor and said fuel injection nozzle having an apparatus directing a combustible fuel and directing compressed air into the combustor; said control system comprising: said fuel injection nozzle defining a cylindrical main body having an outer surface, an outer cylindrical member being radially spaced from the cylindrical main body defining an air inlet end and having a passage being formed between the outer cylindrical member and the outer surface of the cylindrical main body, said air inlet end and said passage having a fixed preestablished area, said preestablished area being sized allowing about 25 percent of the compressed air entering the injection nozzle to be vented therefrom, said apparatus directing the combustible fuel into said passage; means for directing air from the source of compressed air through the inlet end and the passage of the injection nozzle into the combustor in an amount sufficient, with the addition of an appropriate amount of fuel, to support full fuel operation of the gas turbine at rated speed; means for controllably reducing the amount of air directed into the combustor by venting a portion of the air from said passage formed between the outer cylindrical member and the outer surface of the cylindrical main body of the injection nozzle when the engine is operated at less than full fuel or rated speed and said air vented from said passage being dumped into the exhaust.
Claim 2
Dependent Claim
315 words
A gas turbine engine having an exhaust being emitted therefrom and a control system for reducing the formation of exhaust emissions during operation of a gas turbine engine, the engine including a source of compressed air, a combustor defining an outer shell and an inner shell being coaxially positioned about the outer shell, an inlet end portion having a opening therein and a turbine arranged in serial order, a fuel injection nozzle being positioned in the opening in the inlet end portion of the combustor and said fuel injection nozzle having an apparatus directing a combustible fuel and directing compressed air into the combustor; said control system comprising: said fuel injection nozzle defining a cylindrical main body having an outer surface, an outer cylindrical member being radially spaced from the cylindrical main body defining an air inlet end and having a passage being formed between the outer cylindrical member and the outer surface of the cylindrical main body, said air inlet end and said passage having a fixed preestablished area, said preestablished area being sized allowing about 25 percent of the compressed air entering the injection nozzle to be vented therefrom, said apparatus directing the combustible fuel into said passage; means for directing air from the source of compressed air through the inlet end and the passage of the injection nozzle into the combustor in an amount sufficient, with the addition of an appropriate amount of fuel, to support full fuel operation of the gas turbine at rated speed; means for controllably reducing the amount of air directed into the combustor by venting a portion of the air from said passage formed between the outer cylindrical member and the outer surface of the cylindrical main body of the injection nozzle when the engine is operated at less than full fuel or rated speed and said air vented from said passage being dumped into the exhaust.
Claim 3
Dependent Claim
40 words
The gas turbine engine of claim 1 wherein said means for controllably reducing the amount of air directed into the combustor by venting a portion of the air from the injection nozzle includes a valve connected to the injection nozzle.
Claim 4
Dependent Claim
22 words
The gas turbine engine of claim 2 wherein said connection between said valve and the injection nozzle includes a plurality of passages.
Claim 5
Dependent Claim
15 words
The gas turbine engine of claim 3 wherein said valve includes a butterfly type valve.
Claim 6
Dependent Claim
21 words
The gas turbine engine of claim 3 wherein said valve includes a housing and a lever positioned externally of the housing.
Claim 7
Dependent Claim
24 words
The gas turbine engine of claim 2 wherein said valve has a throttling mechanism being movable between and open position and a closed position.
Claim 8
Dependent Claim
38 words
The gas turbine engine of claim 2 wherein said valve has a throttling mechanism being movable between an open position and a closed position, said throttling mechanism being infinitely variable between the open position and the closed position.
Claim 9
Dependent Claim
387 words
A gas turbine engine having an exhaust being emitted therefrom and a control system for reducing the formation of exhaust emissions during operation of a gas turbine engine, the engine including a source of compressed air, a combustor defining an outer shell and an inner shell being coaxially positioned about the outer shell, an inlet end portion having a opening therein and a turbine arranged in serial order, a fuel injection nozzle being positioned in the opening in the inlet end portion of the combustor and said fuel injection nozzle having an apparatus directing a combustible fuel and directing compressed air into the combustor; said control system comprising: said fuel injection nozzle defining a cylindrical main body having an outer surface, an outer cylindrical member being radially spaced from the cylindrical main body defining an air inlet end and having a passage being formed between the outer cylindrical member and the outer surface of the cylindrical main body, said air inlet end and said passage having a fixed preestablished area, said apparatus directing the combustible fuel into said passage; means for directing air from the source of compressed air through the inlet end and the passage of the injection nozzle into the combustor in an amount sufficient, with the addition of an appropriate amount of fuel, to support full fuel operation of the gas turbine at rated speed; means for controllably reducing the amount of air directed into the combustor by venting a portion of the air from said passage formed between the outer cylindrical member and the outer surface of the cylindrical main body of the injection nozzle when the engine is operated at less than full fuel or rated speed and said means for controllably reducing the amount of air directed into the combustor includes a manifold having a passage therein and circling the outer housing, said manifold having a outlet opening therein a valve being connected to the outlet opening and to the exhaust, each of said injection nozzles having one of a main air passage and a secondary air passage with a preestablished area through which a portion of the compressed air can enter, and orifice having a preestablished area through which a portion of the compressed air can be vented and a tube passage being connected to the orifice and the passage.
Claim 10
Dependent Claim
387 words
A gas turbine engine having an exhaust being emitted therefrom and a control system for reducing the formation of exhaust emissions during operation of a gas turbine engine, the engine including a source of compressed air, a combustor defining an outer shell and an inner shell being coaxially positioned about the outer shell, an inlet end portion having a opening therein and a turbine arranged in serial order, a fuel injection nozzle being positioned in the opening in the inlet end portion of the combustor and said fuel injection nozzle having an apparatus directing a combustible fuel and directing compressed air into the combustor; said control system comprising: said fuel injection nozzle defining a cylindrical main body having an outer surface, an outer cylindrical member being radially spaced from the cylindrical main body defining an air inlet end and having a passage being formed between the outer cylindrical member and the outer surface of the cylindrical main body, said air inlet end and said passage having a fixed preestablished area, said apparatus directing the combustible fuel into said passage; means for directing air from the source of compressed air through the inlet end and the passage of the injection nozzle into the combustor in an amount sufficient, with the addition of an appropriate amount of fuel, to support full fuel operation of the gas turbine at rated speed; means for controllably reducing the amount of air directed into the combustor by venting a portion of the air from said passage formed between the outer cylindrical member and the outer surface of the cylindrical main body of the injection nozzle when the engine is operated at less than full fuel or rated speed and said means for controllably reducing the amount of air directed into the combustor includes a manifold having a passage therein and circling the outer housing, said manifold having a outlet opening therein a valve being connected to the outlet opening and to the exhaust, each of said injection nozzles having one of a main air passage and a secondary air passage with a preestablished area through which a portion of the compressed air can enter, and orifice having a preestablished area through which a portion of the compressed air can be vented and a tube passage being connected to the orifice and the passage.
Claim 11
Dependent Claim
47 words
The gas turbine engine of claim 8 wherein said valve has a throttling mechanism therein being movable between an open position and a closed position and said position between the open position and the closed position being dependent on the operating parameters of the gas turbine engine.
Claim 12
Dependent Claim
26 words
The gas turbine engine of claim 8 wherein one valve controls the portion of the flow of compressed air vented from all of the injection nozzles.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 2002-04-26 | 2002-10-26 | 2003-04-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2006-04-26 | 2006-10-26 | 2007-04-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2010-04-26 | 2010-10-26 | 2011-04-27 | $7700.00 | Window Closed / Lapsed |