US4292801A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual stage-dual mode low nox combustor
Assignee: General Electric Co
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Filing: 1979-07-11
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Granted: 1981-10-06
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Expires: 1999-07-11
Abstract
Abstract An improved dual stage-dual mode combustor capable of reduced emissions of nitrogen oxide from a combustion turbine is disclosed. The combustor includes two combustion chambers separated by a throat region. Fuel is initially introduced and ignited in the first chamber. Thereafter, fuel is introduced near the downstream end of the first chamber for ignition and burning in the second chamber. Burning in the first chamber is extinguished by shifting the fuel flow to burning in the second chamber and after termination of the flame in the first chamber, fuel is reintroduced into the first chamber for premixing only with burning in the second chamber. By selectively controlling the percentage of fuel introduced into the first stage, low emissions of nitrogen oxide are realized.
Inventors
- 👤 Colin Wilkes
- 👤 Milton B. Hilt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 06:14
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/08; F05D2270/082; F05D2270/30; F05D2270/31; F23D; F23D2209/00; F23D2209/10
Claims Analysis
Total Claims: 21
Claim 1
Independent Claim
297 words
A method of operating a gas turbine combustor to achieve low emissions of nitrogen oxide, said combustor including first and second combustion stages separated by a throat region of reduced diameter relative to said combustion stages with a plurality of fuel nozzles and air swirlers for introducing fuel and air respectively into said first stage and a single fuel nozzle and air swirler positioned adjacent said throat region for introducing additional fuel and air respectively into said second stage, said method comprising: introducing fuel and air into said first stage from said plurality of fuel nozzles and air swirlers for mixing therein to create a combustible fuel-air mixture; introducing additional fuel and air into said second stage from said single fuel nozzle and air swirler, said additional fuel and air mixing with the combustible fuel-air mixture in said second stage for combustion therein and wherein the step of introducing additional fuel and air into said second stage from said single fuel nozzle and air swirler includes locating said single fuel nozzle and air swirler relative to said throat region and dimensioning said throat region relative to said combustion stages to minimize flashback from said second combustion stage to said first combustion stage; introducing additional air into said second stage from said throat region for further reducing the possibility of flashback into said first stage from said second stage; introducing dilution air into the downstream end of said second stage to reduce residence time of the products of combustion at NOx producing temperatures in said second stage; and adjusting the fuel flow to said single fuel nozzle and said plurality of fuel nozzles while maintaining a substantially constant total fuel flow until a majority of the total fuel flow is equally distributed among said plurality of fuel nozzles.
Claim 2
Independent Claim
297 words
A method of operating a gas turbine combustor to achieve low emissions of nitrogen oxide, said combustor including first and second combustion stages separated by a throat region of reduced diameter relative to said combustion stages with a plurality of fuel nozzles and air swirlers for introducing fuel and air respectively into said first stage and a single fuel nozzle and air swirler positioned adjacent said throat region for introducing additional fuel and air respectively into said second stage, said method comprising: introducing fuel and air into said first stage from said plurality of fuel nozzles and air swirlers for mixing therein to create a combustible fuel-air mixture; introducing additional fuel and air into said second stage from said single fuel nozzle and air swirler, said additional fuel and air mixing with the combustible fuel-air mixture in said second stage for combustion therein and wherein the step of introducing additional fuel and air into said second stage from said single fuel nozzle and air swirler includes locating said single fuel nozzle and air swirler relative to said throat region and dimensioning said throat region relative to said combustion stages to minimize flashback from said second combustion stage to said first combustion stage; introducing additional air into said second stage from said throat region for further reducing the possibility of flashback into said first stage from said second stage; introducing dilution air into the downstream end of said second stage to reduce residence time of the products of combustion at NOx producing temperatures in said second stage; and adjusting the fuel flow to said single fuel nozzle and said plurality of fuel nozzles while maintaining a substantially constant total fuel flow until a majority of the total fuel flow is equally distributed among said plurality of fuel nozzles.
Claim 3
Dependent Claim
22 words
The method of claim 1 wherein between approximately 75 and 95% of the total fuel flow is introduced into said first stage.
Claim 4
Dependent Claim
34 words
The method of claim 1 wherein said first and second stages include walls having a plurality of openings therein and introducing compressed air into said first and second stages through said plurality of openings.
Claim 5
Dependent Claim
27 words
The method of claim 3 further comprising the step of introducing between approximately 25 and 50% of the total air to said combustor into said first stage.
Claim 6
Dependent Claim
30 words
The method of claim 4 wherein approximately 15 to 25% of the total flow in said combustor is introduced as dilution air into the downstream end of said second stage.
Claim 7
Dependent Claim
27 words
The method of claim 3 further comprising the step of introducing between approximately 45 to 65% of the total air to said combustor into said second stage.
Claim 8
Dependent Claim
26 words
The method of claim 5 wherein the additional air introduced into said throat region is up to approximately 5% of the total airflow to said combustor.
Claim 9
Dependent Claim
22 words
The method of claim 1 further comprising the step of conveying the products of combustion from said second stage to said turbine.
Claim 10
Dependent Claim
262 words
A low NOx combustor for a gas turbine comprising: first and second combustion chambers interconnected by a throat region, said throat region being of reduced dimensions compared to said combustion chambers and including gradual converging and diverging sections and functioning as an aerodynamic separator or isolator for minimizing flashback from the second chamber to the first chamber; first fuel introduction means adjacent the upstream end of said first chamber for introducing fuel therein, said first fuel introduction means comprising a plurality of fuel nozzles circumferentially positioned along the rear wall of said first combustion chamber and projecting into said first chamber; first means adjacent the pluarlity of fuel nozzles of said first fuel introduction means for introducing compressed air into said first chamber for mixing with said fuel and creating a combustible fuel-air mixture therein; second fuel introduction means located centrally of said first fuel introduction means for introducing fuel into said second chamber for mixing with the fuel-air mixture or combustion products from said first chamber for burning in said second chamber, said centrally located second fuel introduction means being positioned relative to the downstream end of said first chamber and said throat region for further minimizing possible flashback from said second combustion chamber to said first combustion chamber; second means adjacent said second fuel introduction means for introducing compressed air into said combustion chamber for mixing with said fuel; and means for introducing dilution air into the downstream end of said second chamber to reduce residence time of the products of combustion at NOx producing temperatures in said second chamber.
Claim 11
Dependent Claim
262 words
A low NOx combustor for a gas turbine comprising: first and second combustion chambers interconnected by a throat region, said throat region being of reduced dimensions compared to said combustion chambers and including gradual converging and diverging sections and functioning as an aerodynamic separator or isolator for minimizing flashback from the second chamber to the first chamber; first fuel introduction means adjacent the upstream end of said first chamber for introducing fuel therein, said first fuel introduction means comprising a plurality of fuel nozzles circumferentially positioned along the rear wall of said first combustion chamber and projecting into said first chamber; first means adjacent the pluarlity of fuel nozzles of said first fuel introduction means for introducing compressed air into said first chamber for mixing with said fuel and creating a combustible fuel-air mixture therein; second fuel introduction means located centrally of said first fuel introduction means for introducing fuel into said second chamber for mixing with the fuel-air mixture or combustion products from said first chamber for burning in said second chamber, said centrally located second fuel introduction means being positioned relative to the downstream end of said first chamber and said throat region for further minimizing possible flashback from said second combustion chamber to said first combustion chamber; second means adjacent said second fuel introduction means for introducing compressed air into said combustion chamber for mixing with said fuel; and means for introducing dilution air into the downstream end of said second chamber to reduce residence time of the products of combustion at NOx producing temperatures in said second chamber.
Claim 12
Dependent Claim
27 words
The low NOx combustor of claim 9 further comprising: p1 means for altering the relative rates of fuel flow between said first and second fuel introduction means.
Claim 13
Dependent Claim
24 words
The low NOx combustor of claim 10 wherein the fuel flow into said first combustion chamber is greater than into said second combustion chamber.
Claim 14
Dependent Claim
28 words
The low NOx combustor of claim 11 wherein between approximately 75 and 95% of the total fuel flow to said combustor is introduced into said first combustion chamber.
Claim 15
Dependent Claim
31 words
The low NOx combustor of claim 9 wherein the compressed air introduced into said first combustion chamber is between approximately 25 and 50% of the total air introduced into said combustor.
Claim 16
Dependent Claim
31 words
The low NOx combustor of claim 9 wherein said throat region further includes means for the introducing compressed air into said second combustion chamber for further reducing the possibility of flashback.
Claim 17
Dependent Claim
34 words
The low NOx combustor of claim 14 wherein said compressed air introduced into said second combustion chamber from said throat region comprises up to approximately 5% of the total air introduced into said combustor.
Claim 18
Dependent Claim
52 words
The low NOx combustor of claim 15 wherein the airflow to said combustor comprises approximately 5 to 15% introduced by said first means, 15 to 25% introduced as dilution air in said second combustion chamber and the balance through louvers or slots in the walls of said first and second combustion chambers.
Claim 19
Dependent Claim
24 words
The low NOx combustor of claim 9 wherein approximately 15 to 25% of the total air flow to said combustor comprises said dilution air.
Claim 20
Dependent Claim
40 words
The low NOx combustor of claim 13 wherein the compressed air introduced into said second combustion chamber is between approximately 45 and 65% of the total air introduced into said combustor and the balance is introduced in said throat region.
Claim 21
Dependent Claim
28 words
The low NOx combustor of claim 9 wherein said second fuel introduction means includes a single fuel nozzle supported from the rear wall of said first combustion chamber.
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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) | 1984-10-05 | 1985-04-06 | 1985-10-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-10-05 | 1989-04-06 | 1989-10-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-10-05 | 1993-04-06 | 1993-10-06 | $7700.00 | Window Closed / Lapsed |