US4534165A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Catalytic combustion system
Assignee: General Electric Co
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Filing: 1983-10-07
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Granted: 1985-08-13
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Expires: 2003-10-07
Abstract
Abstract A catalytic combustor comprises a pilot zone having means to introduce fuel therein; upstream of said pilot zone and communicating therewith a catalytically supported thermal combustion zone comprising a plurality of catalytically supported thermal combustion sections each comprising a solid oxidation catalyst, means for introducing air into said section and means to introduce fuel into said section; and means to control the rate of fuel flow in each of the means to introduce fuel into a catalytically supported thermal combustion section and the means to introduce fuel into the pilot zone. The combustor is operated by staging the fuel supply in order to maximize the amount of combustion in the catalytically supported thermal combustion zone and minimize NOx emissions under all load conditions.
Inventors
- 👤 L. Berkley Davis, Jr.
- 👤 Milton B. Hilt
- 👤 Colin Wilkes
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 04:25
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F23R3/40
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
285 words
A method for operating a combustor of a gas turbine, said combustor being of the type having a catalytic combustion zone including a plurality of independent catalytically supported combustion sections, a single pilot zone downstream of said catalytic combustion zone, means for feeding a fuel to said single pilot zone, means for independently introducing fuel and air into said plurality of independent catalytically supported combustion sections and all of an effluent of said plurality of independent catalytically supported combustion sections entering said single pilot zone, comprising: initially accelerating said gas turbine to a predetermined load condition using hot gases generated only in said single pilot zone by feeding said fuel to said single pilot zone and air into at least one of said plurality of independent catalytically supported combustion sections, said air passing downstream of said at least one of said plurality of independent catalytically supported combustion sections to be useable as combustion air with said fuel in said single pilot zone; and further accelerating said gas turbine to a greater load condition by staging fuel to individual ones of said plurality of independent catalytically supported combustion sections to produce additional hot gases which pass downstream of said plurality of catalytically supported combustion sections, an excess air in said additional hot gases being effective to support combustion of said fuel fed to said single pilot zone and combustion in said single pilot zone being effective to clean up unburned portions of fuel entering said single pilot zone with said hot gases from said plurality of catalytically supported combustion sections; and at least partially preheating a catalyst in said catalytically supported combustion sections toward an operating temperature during the step of initially accelerating said gas turbine.
Claim 2
Independent Claim
285 words
A method for operating a combustor of a gas turbine, said combustor being of the type having a catalytic combustion zone including a plurality of independent catalytically supported combustion sections, a single pilot zone downstream of said catalytic combustion zone, means for feeding a fuel to said single pilot zone, means for independently introducing fuel and air into said plurality of independent catalytically supported combustion sections and all of an effluent of said plurality of independent catalytically supported combustion sections entering said single pilot zone, comprising: initially accelerating said gas turbine to a predetermined load condition using hot gases generated only in said single pilot zone by feeding said fuel to said single pilot zone and air into at least one of said plurality of independent catalytically supported combustion sections, said air passing downstream of said at least one of said plurality of independent catalytically supported combustion sections to be useable as combustion air with said fuel in said single pilot zone; and further accelerating said gas turbine to a greater load condition by staging fuel to individual ones of said plurality of independent catalytically supported combustion sections to produce additional hot gases which pass downstream of said plurality of catalytically supported combustion sections, an excess air in said additional hot gases being effective to support combustion of said fuel fed to said single pilot zone and combustion in said single pilot zone being effective to clean up unburned portions of fuel entering said single pilot zone with said hot gases from said plurality of catalytically supported combustion sections; and at least partially preheating a catalyst in said catalytically supported combustion sections toward an operating temperature during the step of initially accelerating said gas turbine.
Claim 3
Dependent Claim
30 words
A method according to claim 1 further comprising premixing said fuel to individual ones of said catalytically supported combustion sections before contacting a catalyst in said catalytically supported combustion sections.
Claim 4
Dependent Claim
74 words
A method according to claim 1 further comprising further heating said catalyst toward its operating temperature during the step of further accelerating said gas turbine and burning unburned fuel from said catalytically supported combustion sections in said single pilot zone during the step of further accelerating at least until said catalyst attains an operating temperature which is capable of enabling said catalyst to substantially completely combust said fuel fed to said catalytic combustion zone.
References Cited (Backward Citations)
US3797231A
Cited
US3938326A
Cited
US3943705A
Cited
US4054407A
Cited
US4197701A
Cited
US4072007A
Cited
US4047877A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-08-12 | 1989-02-11 | 1989-08-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-08-12 | 1993-02-11 | 1993-08-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-08-12 | 1997-02-11 | 1997-08-13 | $7700.00 | Window Closed / Lapsed |