US6026644A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
Assignee: Hitachi Ltd
•
Filing: 1996-08-21
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Granted: 2000-02-22
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Expires: 2016-08-21
Abstract
Abstract A gas turbine combustor has a premixing burner for jetting out a premixed gas of fuel and air. A stabilizer forms a circulation of combustion gas generated by combustion of the premixed gas at the downstream side of the stabilizer to stabilize flame formed by the combustion of the premixed gas. Before the operation of the combustor, a relationship between a temperature of the stabilizer and combustion conditions of the premixed gas is checked. Thereafter during operation of the combustor, the temperature of the stabilizer is measured during combustion and the combustion conditions are checked according to only the measured temperature of the stabilizer and the aforesaid relationship. The stabilizer has a heat receiving surface at the most downstream side thereof. The temperature of a portion of the stabilizer around the heat receiving surfaces measured to allow an accurate assessment of the combustion conditions.
Inventors
- 👤 Kazuyuki Ito
- 👤 Tadayoshi Murakami
- 👤 Kazuhiko Kawaike
- 👤 Shigeru Azuhata
- 👤 Michio Kuroda
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 07:47
CPC Classifications
F; F23; F23N; F23N5/00; F23N5/24; F23N5/242; F02; F02C; F02C9/00; F02C9/26; F02C9/28; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/16; F23R3/18; F05; F05D; F05D2240/00; F05D2240/10; F05D2240/12; F05D2240/127; F23N2241/00; F23N2241/20
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
227 words
A gas turbine combuster comprising: a plurality of premixing burners, each for jetting out a premixed gas of fuel and air; a plurality of premixing fuel lines connected to said Plurality of premixing burners, respectively, each said premixing fuel line having a fuel flow adjusting device; a stabilizer for forming a circulation of combustion gas generated through combustion of said premixed gas, said stabilizer having an annular shape and a heating surface at a most downstream portion of said stabilizer, said stabilizer being disposed so that at a downstream side of said stabilizer the premixed gas jetted from each said premixing burner flows downstream of said stabilizer through inner and outer sides of said stabilizer; means for setting, before a practical operation of said combustor, a relationship between a temperature of said stabilizer and combustion conditions of a premixed gas; a plurality of thermometers arranged in said stabilizer close to said heating surface to be circumferentially distant from each other; means for adjusting a fuel flow rate to each said premixing burner according to said relationship and a detected temperature of said stabilizer at a position corresponding to each said premixing burner; and means for stopping fuel supply to all of said plurality of premixing burners when a temperature of said stabilizer detected by any one of said plurality of thermometers is a preset value or larger.
Claim 2
Dependent Claim
227 words
A gas turbine combuster comprising: a plurality of premixing burners, each for jetting out a premixed gas of fuel and air; a plurality of premixing fuel lines connected to said Plurality of premixing burners, respectively, each said premixing fuel line having a fuel flow adjusting device; a stabilizer for forming a circulation of combustion gas generated through combustion of said premixed gas, said stabilizer having an annular shape and a heating surface at a most downstream portion of said stabilizer, said stabilizer being disposed so that at a downstream side of said stabilizer the premixed gas jetted from each said premixing burner flows downstream of said stabilizer through inner and outer sides of said stabilizer; means for setting, before a practical operation of said combustor, a relationship between a temperature of said stabilizer and combustion conditions of a premixed gas; a plurality of thermometers arranged in said stabilizer close to said heating surface to be circumferentially distant from each other; means for adjusting a fuel flow rate to each said premixing burner according to said relationship and a detected temperature of said stabilizer at a position corresponding to each said premixing burner; and means for stopping fuel supply to all of said plurality of premixing burners when a temperature of said stabilizer detected by any one of said plurality of thermometers is a preset value or larger.
Claim 3
Dependent Claim
226 words
A gas turbine combustor comprising: a plurality of premixing burners, each for jetting out a premixed gas of fuel and air; a plurality of premixing fuel lines connected to said plurality of premixing burners, respectively; a stabilizer for forming a circulation of combustion gas generated through combustion of said premixed gas, said stabilizer having an annular shape and a heating surface at a most downstream portion of said stabilizer, said stabilizer being disposed so that at a downstream side of said stabilizer the premixed gas jetted from said plurality of premixing burners flows downstream of said stabilizer through inner and outer sides of said stabilizer; means provided close to said heating surface of said stabilizer for detecting a temperature of said stabilizer, said temperature detecting means including a plurality of thermometers arranged in said stabilizer to be circumferentially distant from each other; and a control system for controlling and adjusting a fuel quantity to each said premixing burner relative to the other burners through each said premixing fuel line on the basis of temperature of said stabilizer detected by each said thermometer at a position corresponding to each said burner, wherein said control system changes fuel quantities of said premixing fuel lines to a preset control value when any one of said stabilizer temperatures detected by said plurality of thermometers reaches a predetermined value or more.
Claim 4
Dependent Claim
226 words
A gas turbine combustor comprising: a plurality of premixing burners, each for jetting out a premixed gas of fuel and air; a plurality of premixing fuel lines connected to said plurality of premixing burners, respectively; a stabilizer for forming a circulation of combustion gas generated through combustion of said premixed gas, said stabilizer having an annular shape and a heating surface at a most downstream portion of said stabilizer, said stabilizer being disposed so that at a downstream side of said stabilizer the premixed gas jetted from said plurality of premixing burners flows downstream of said stabilizer through inner and outer sides of said stabilizer; means provided close to said heating surface of said stabilizer for detecting a temperature of said stabilizer, said temperature detecting means including a plurality of thermometers arranged in said stabilizer to be circumferentially distant from each other; and a control system for controlling and adjusting a fuel quantity to each said premixing burner relative to the other burners through each said premixing fuel line on the basis of temperature of said stabilizer detected by each said thermometer at a position corresponding to each said burner, wherein said control system changes fuel quantities of said premixing fuel lines to a preset control value when any one of said stabilizer temperatures detected by said plurality of thermometers reaches a predetermined value or more.
Claim 5
Dependent Claim
48 words
The gas turbine combustor according to claim 2, wherein said control system has a relationship input therein of combustion conditions of said premixed gas to temperatures of said stabilizer, and said control system judges the combustion conditions according to the measured temperature of said stabilizer and said relationship.
Claim 6
Dependent Claim
36 words
The gas turbine combustor described in claim 3, wherein said relationship indicates whether the combustion condition is normal or abnormal according to whether or not the temperature of said stabilizer is within a preset temperature range.
Claim 7
Dependent Claim
26 words
The gas turbine combustor described in claim 3, wherein said relationship indicates the relationship between said stabilizer temperature and an air-fuel ratio of said premixed gas.
Claim 8
Dependent Claim
26 words
The gas turbine combustor described in claim 3, wherein said relationship indicates the relationship between said stabilizer temperature and a NOx concentration in said combustion gas.
Claim 9
Dependent Claim
18 words
The gas turbine combustor described in claim 2, wherein there is provided means for displaying said combustion conditions.
Claim 10
Dependent Claim
40 words
The gas turbine combustor according to claim 2, wherein said control system controls said combustor so that when the detected temperature is beyond the predetermined set value, fuel supply to all of said premixed burners is stopped, whereby preventing flash-back.
Claim 11
Dependent Claim
50 words
The gas turbine combustor according to claim 2, wherein said control system controls so as to close a main adjusting valve for adjusting a quantity of fuel for all of said premixed burners when the temperature detected by at least one of said thermometers is beyond the predetermined set value.
Claim 12
Dependent Claim
18 words
The gas turbine combustor according to claim 2, wherein each of said thermometers is embedded in said stabilizer.
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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) | 2003-02-21 | 2003-08-23 | 2004-02-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2007-02-21 | 2007-08-23 | 2008-02-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2011-02-21 | 2011-08-23 | 2012-02-22 | $7700.00 | Window Closed / Lapsed |