Patent US3004581A successfully refreshed from Google Patents.
Patent US5685139A successfully refreshed from Google Patents.
US5685139A
Expired / Lapsed
US
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Diffusion-premix nozzle for a gas turbine combustor and related method
Assignee: General Electric Co
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Filing: 1996-03-29
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Granted: 1997-11-11
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Expires: 2016-03-29
Abstract
Abstract A fuel nozzle for a gas turbine includes a nozzle body having a tip portion, the nozzle body including an inner tube defining an axially extending air passage; an intermediate tube concentrically arranged and radially spaced from the inner tube and defining a diffusion fuel passage therebetween; and an outer tube concentrically arranged and radially spaced from the intermediate tube and defining a premix fuel passage therebetween. The outer tube has a plurality of radially extending injectors in communication with the premix fuel passage. The premix fuel passage is further defined in part by an outer tube wall portion formed with at least one weakened region adapted to burn through in the event of a flashback, thereby causing a substantial portion of premix fuel to bypass the injectors and to exit the nozzle body at the at least one weakened region. A related method is also disclosed.
Inventors
- 👤 Warren J. Mick
- 👤 L. Berkley Davis, Jr.
- 👤 Michael B. Sciocchetti
- 👤 David O. Fitts
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 19:03
CPC Classifications
F; F23; F23D; F23D14/00; F23D14/20; F23D14/22; F23D14/02; F23D14/46; F23D14/48; F23D14/72; F23D14/82; F23D2211/00; F23D2900/00; F23D2900/00008
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
142 words
A fuel nozzle for a gas turbine comprising: a nozzle body having a tip portion, said nozzle body including an inner tube defining an axially extending air passage; an intermediate tube concentrically arranged and radially spaced from said inner tube and defining a diffusion fuel passage therebetween; and an outer tube concentrically arranged and radially spaced from said intermediate tube and defining a premix fuel passage therebetween; said outer tube having a plurality of radially extending injectors in communication with said premix fuel passage; and wherein said premix fuel passage is further defined in part by an outer tube wall portion formed with at least one weakened region adapted to burn through in the event of a flashback, thereby causing a portion of premix fuel to bypass said injectors and to exit the nozzle body at said at least one weakened region.
Claim 2
Dependent Claim
142 words
A fuel nozzle for a gas turbine comprising: a nozzle body having a tip portion, said nozzle body including an inner tube defining an axially extending air passage; an intermediate tube concentrically arranged and radially spaced from said inner tube and defining a diffusion fuel passage therebetween; and an outer tube concentrically arranged and radially spaced from said intermediate tube and defining a premix fuel passage therebetween; said outer tube having a plurality of radially extending injectors in communication with said premix fuel passage; and wherein said premix fuel passage is further defined in part by an outer tube wall portion formed with at least one weakened region adapted to burn through in the event of a flashback, thereby causing a portion of premix fuel to bypass said injectors and to exit the nozzle body at said at least one weakened region.
Claim 3
Dependent Claim
29 words
The fuel nozzle of claim 1 wherein a plurality of weakened regions including said at least one region are located in an annular array within said outer tube wall.
Claim 4
Dependent Claim
16 words
The fuel nozzle of claim 2 wherein said weakened regions are formed by reduced wall thickness.
Claim 5
Dependent Claim
20 words
The fuel nozzle of claim 1 wherein said at least one weakened wall region is formed in said tip portion.
Claim 6
Dependent Claim
19 words
The fuel nozzle of claim 4 wherein said tip portion is rigidly fixed to said intermediate and outer tubes.
Claim 7
Dependent Claim
24 words
The fuel nozzle of claim 5 wherein said intermediate tube incorporates a bellows portion to accommodate differential thermal expansion relative to said outer tube.
Claim 8
Dependent Claim
19 words
The fuel nozzle of claim 6 wherein said inner tube is clearance fit into said fuel nozzle tip portion.
Claim 9
Dependent Claim
18 words
The fuel nozzle of claim 1 wherein premix passage is normally closed downstream of said plurality of injectors.
Claim 10
Dependent Claim
23 words
The fuel nozzle of claim 4 wherein said tip portion includes a plurality of discharge orifices in communication with said diffusion fuel passage.
Claim 11
Dependent Claim
186 words
In a gas turbine, a plurality of combustors, each having a plurality of fuel nozzles arranged about a longitudinal axis of the combustor, and a combustion zone, each fuel nozzle having a diffusion gas passage connected to a diffusion gas inlet and a premix gas passage connected to a premix gas inlet, the premix gas passage communicating with a plurality of premix fuel injectors extending radially away from said premix gas passage, and located within a dedicated premix tube adapted to mix premix fuel and combustion air prior to entry into the combustion zone located downstream of the premix tube, and wherein said diffusion gas passage terminates at a forward discharge end of said fuel nozzle downstream of said premix fuel injectors but within said dedicated premix tube, and wherein said plurality of premix fuel injectors are located upstream of said forward end; and further wherein said diffusion gas passage is defined in part by a forward wall portion of the fuel nozzle, said forward wall portion formed with a circumferential array of regions of lesser wall thickness than remaining regions of said forward wall portion.
Claim 12
Dependent Claim
186 words
In a gas turbine, a plurality of combustors, each having a plurality of fuel nozzles arranged about a longitudinal axis of the combustor, and a combustion zone, each fuel nozzle having a diffusion gas passage connected to a diffusion gas inlet and a premix gas passage connected to a premix gas inlet, the premix gas passage communicating with a plurality of premix fuel injectors extending radially away from said premix gas passage, and located within a dedicated premix tube adapted to mix premix fuel and combustion air prior to entry into the combustion zone located downstream of the premix tube, and wherein said diffusion gas passage terminates at a forward discharge end of said fuel nozzle downstream of said premix fuel injectors but within said dedicated premix tube, and wherein said plurality of premix fuel injectors are located upstream of said forward end; and further wherein said diffusion gas passage is defined in part by a forward wall portion of the fuel nozzle, said forward wall portion formed with a circumferential array of regions of lesser wall thickness than remaining regions of said forward wall portion.
Claim 13
Dependent Claim
28 words
The fuel nozzle of claim 10 wherein said forward wall portion is provided with a plurality of annularly arranged discharge orifices in communication with said diffusion fuel passage.
Claim 14
Dependent Claim
32 words
The fuel nozzle of claim 10 wherein an intermediate tube defining the diffusion and premix gas passages incorporates a bellows portion to accommodate differential thermal expansion relative to said dedicated premix tube.
Claim 15
Dependent Claim
21 words
The fuel nozzle of claim 12 wherein an inner tube is press fit into said forward discharge end of said nozzle.
Claim 16
Dependent Claim
19 words
The fuel nozzle of claim 10 wherein said premix passage is normally closed downstream of said plurality of injectors.
Claim 17
Independent Claim
230 words
A method of minimizing flashback damage in a gas turbine combustor which includes a plurality of combustors, each of which includes a premix zone, a combustion zone and a plurality of nozzles, each nozzle having a diffusion gas passage connected to a diffusion gas inlet and a premix gas passage connected to a premix gas inlet, the premix gas passage communicating with a plurality of premix fuel injectors extending radially away from said premix gas passage, and located within a dedicated premix tube adapted to mix premix fuel and combustion air prior to entry into the single combustion zone located downstream of the premix tube, and wherein said diffusion gas passage terminates at a forward discharge end of said fuel nozzle downstream of said premix fuel injectors but within said dedicated premix tube, and wherein said premix fuel injectors are located upstream of said forward end; and further wherein said diffusion gas passage is defined in part by a forward wall portion of the fuel nozzle, the method including the step of providing weakened regions in a wall partially defining said premix passage so that, in the event of a flashback of flame into the premix zone, said weakened regions will burn through, allowing a substantial portion of premix fuel to bypass said premix fuel injectors, such that any premix fuel exiting said injectors is insufficient to sustain a flame.
Claim 18
Independent Claim
230 words
A method of minimizing flashback damage in a gas turbine combustor which includes a plurality of combustors, each of which includes a premix zone, a combustion zone and a plurality of nozzles, each nozzle having a diffusion gas passage connected to a diffusion gas inlet and a premix gas passage connected to a premix gas inlet, the premix gas passage communicating with a plurality of premix fuel injectors extending radially away from said premix gas passage, and located within a dedicated premix tube adapted to mix premix fuel and combustion air prior to entry into the single combustion zone located downstream of the premix tube, and wherein said diffusion gas passage terminates at a forward discharge end of said fuel nozzle downstream of said premix fuel injectors but within said dedicated premix tube, and wherein said premix fuel injectors are located upstream of said forward end; and further wherein said diffusion gas passage is defined in part by a forward wall portion of the fuel nozzle, the method including the step of providing weakened regions in a wall partially defining said premix passage so that, in the event of a flashback of flame into the premix zone, said weakened regions will burn through, allowing a substantial portion of premix fuel to bypass said premix fuel injectors, such that any premix fuel exiting said injectors is insufficient to sustain a flame.
Claim 19
Dependent Claim
80 words
In a fuel nozzle for a gas turbine combustor having a nozzle body defining a fuel-air passage and an injector in fluid communication with said passage for injecting a fuel-air mixture from said passage into a burning zone, the improvement comprising a weakened region of the nozzle body adapted to burn through in the event of combustion flashback, thereby permitting a portion of said fuel-air mixture to bypass said injector and to exit said nozzle body at said weakened region.
Claim 20
Dependent Claim
80 words
In a fuel nozzle for a gas turbine combustor having a nozzle body defining a fuel-air passage and an injector in fluid communication with said passage for injecting a fuel-air mixture from said passage into a burning zone, the improvement comprising a weakened region of the nozzle body adapted to burn through in the event of combustion flashback, thereby permitting a portion of said fuel-air mixture to bypass said injector and to exit said nozzle body at said weakened region.
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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) | 2000-11-10 | 2001-05-12 | 2001-11-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2004-11-10 | 2005-05-12 | 2005-11-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2008-11-10 | 2009-05-12 | 2009-11-11 | $7700.00 | Window Closed / Lapsed |