US20030037549A1 - Gas turbine combustor - Google Patents

Gas turbine combustor

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Publication number
US20030037549A1
US20030037549A1 US10198368 US19836802A US2003037549A1 US 20030037549 A1 US20030037549 A1 US 20030037549A1 US 10198368 US10198368 US 10198368 US 19836802 A US19836802 A US 19836802A US 2003037549 A1 US2003037549 A1 US 2003037549A1
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US
Grant status
Application
Patent type
Prior art keywords
pre
combustor
cylindrical member
outer
inner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US10198368
Inventor
Shigemi Mandai
Keijirou Saitoh
Katsunori Tanaka
Wataru Akizuki
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46Details, e.g. noise reduction means
    • F23D14/72Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78Cooling burner parts
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46Details, e.g. noise reduction means
    • F23D14/72Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74Preventing flame lift-off
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283Attaching or cooling of fuel injecting means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Abstract

A gas turbine combustor is improved to enhance a cooling effect and a flame holding ability to thereby reduce NOx generation. A combustor 13 comprises a double structure of an inner cylindrical member 13 a and an enlarged outer cylindrical member 13 b to thereby enlarge a diameter of a combustion zone. A pre-mixing nozzle 11 comprises an outer sleeve 23 of which front end is projected beyond a base plate 17 and a pre-mixing nozzle portion 21 of the inner side. Air flows between the outer sleeve 23 and the pre-mixing nozzle portion 21 for enhancing the cooling effect of the pre-mixing nozzle 11. High temperature gas inner and outer circulating flows 15, 16 are formed in the combustion zone to enhance the flame holding ability. Pilot fuel quantity, as so far necessitated for flame holding, is reduced and NOx quantity generated of the pilot fuel is reduced. The base plate 17 exposed to the high temperature gas is prevented from being overheated by the projected front portion of the pre-mixing nozzle 11.

Description

    BACKGROUND OF THE INVENTION
  • 1. Field of the Invention [0001]
  • The present invention relates to a gas turbine combustor that realizes a low NOx combustion. [0002]
  • 2. Description of the Prior Art [0003]
  • FIGS. [0004] 4(a) and (b) schematically show a prior art gas turbine combustor, wherein FIG. 4(a) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 4(b) is a front view of a half portion of the combustor. In FIGS. 4(a) and (b), main fuel 40 flows into eight pre-mixing nozzles 31, that are arranged within a combustor body 36 around a central axis thereof, and is pre-mixed with air, as will be described next, to form a main pre-mixture to be supplied into a combustion zone of a combustor 33. The air is supplied from a compressor (not shown) to be fed into the combustor 33 flowing through an inner peripheral space portion of the combustor body 36, as shown by arrows 50 in FIG. 4(a). On the other hand, pilot fuel 41 flows into a pilot nozzle 32, that is arranged on the central axis of the combustor body 36, to be jetted into the combustor 33. Thus, the pilot fuel 41 burns with the main pre-mixture there to effect a combustion. A flame holding cone 34 is provided on the pilot nozzle 32 and flame of the pilot fuel 41 is maintained by a high temperature gas circulating flow 35, that is formed by the flame holding cone 34. Such a combustor having the pre-mixing nozzles and being constructed as described above is generally known as a low NOx combustor.
  • In the above described pre-mixed flame type low NOx combustor in the prior art, the flame of the pilot nozzle [0005] 32 is maintained by a diffused flame, that is, the high temperature gas circulating flow 35, formed by the flame holding cone 34 and NOx quantity generated by the pre-mixing nozzles 31 is reduced. However, NOx quantity generated by the diffused flame of the pilot nozzle 32 cannot be suppressed and realization of a low NOx generation as a whole is limited by that extent.
  • SUMMARY OF THE INVENTION
  • It is, therefore, an object of the present invention to provide a gas turbine combustor that is constructed so as to improve a flame holding ability by the high temperature gas circulating flow as well as to improve cooling of the pre-mixing nozzles to thereby reduce pilot fuel quantity as well as to reduce NOx quantity generated of the pilot fuel. [0006]
  • In order to achieve the mentioned object, the present invention provides means of the following (1) to (4): [0007]
  • (1) A gas turbine combustor comprising a pilot nozzle arranged on a central axis of the combustor and a plurality of pre-mixing nozzles arranged around the pilot nozzle, characterized in that a diameter of a combustion zone of the combustor is set such that, where an area is taken on a radial directional plane of the combustor, the area inside of the combustion zone and outside of a pitch circle that is defined as a circle on which all central axes of the plurality of pre-mixing nozzles are arranged, less the area taken by the plurality of pre-mixing nozzles outside of the pitch circle, is a half or more of the area of all of-the plurality of pre-mixing nozzles. [0008]
  • (2) A gas turbine combustor as mentioned in the means (1) above, characterized in that each of the plurality of pre-mixing nozzles has its front end projected beyond a base plate that supports the pre-mixing nozzle and a projecting distance of such projected front end is set to one third or more of an outer diameter of the pre-mixing nozzle. [0009]
  • (3) A gas turbine combustor as mentioned in the means (1) above, characterized in that each of the plurality of pre-mixing nozzles has its front portion made in a double structure having inner and outer members with a predetermined gap being maintained between the inner and outer members and air is flowable in the gap. [0010]
  • (4) A gas turbine combustor as mentioned in the means (1) above, characterized in that a combustor body as an outer casing of the combustor comprises therein an inner cylindrical member and an outer cylindrical member, the inner cylindrical member is arranged surrounding the plurality of pre-mixing nozzles and the outer cylindrical member has its inner diameter made larger than an outer diameter of the inner cylindrical member and is arranged surrounding a front end portion of the inner cylindrical member and extending downstream of the inner cylindrical member so as to cover the combustion zone to thereby enable to enlarge the diameter of the combustion zone beyond an inner diameter of the inner cylindrical member. [0011]
  • In the means (1) of the present invention, the diameter of the combustion zone in which a high temperature combustion gas is generated is set such that the cross sectional area inside of the combustion zone and outside of the pitch circle, less the cross sectional area of the pre-mixing nozzles outside of the pitch circle, is a half or more of the cross sectional area of all the pre-mixing nozzles. By this structure, the outer peripheral space portion of the combustion zone is enlarged and a gas stagnation area is formed in this space portion, that is, in the outer peripheral space portion in front of the pre-mixing nozzles. An outer circulating flow of the high temperature gas generated by combustion of the pre-mixture coming from the pre-mixing nozzles is formed in this gas stagnation area. Also, an inner circulating flow of a high temperature gas generated of the pilot fuel is formed in the central space portion of the combustion zone in front of the pilot nozzle by a flame holding cone. Thus, by the inner and outer circulating flows of the high temperature gas, the flame holding ability of the combustor can be greatly enhanced. Thereby, the pilot fuel quantity, as so far necessitated for the flame holding, can be reduced, the NOx quantity generated by combustion of the pilot fuel can be reduced and a very low NOx generation can be realized as a whole. [0012]
  • In the means (2) of the present invention, each of the pre-mixing nozzles has its front end projected beyond the base plate so that the base plate may not be directly exposed to the high temperature gas circulating flows. Thereby, the base plate is prevented from being overheated and the effect of the means (1) of the present invention can be realized more securely. [0013]
  • In the means (3) of the present invention, each of the pre-mixing nozzles has its front portion made in the double structure having the predetermined gap therein and air is flowable in the gap for cooling the pre-mixing nozzle. Thus, the pre-mixing nozzle is prevented from being overheated and the effect of the means (1) of the present invention is further ensured. [0014]
  • In the means (4) of the present invention, the combustor body as the outer casing of the combustor comprises therein the inner cylindrical member and the outer cylindrical member. The outer cylindrical member has its inner diameter made larger than the outer diameter of the inner cylindrical member. Thus, the diameter of the combustion zone is enlarged outwardly so that the gas stagnation area is easily formed in the outer peripheral space portion of the combustion zone in front of the pre-mixing nozzles. The outer circulating flow of the high temperature combustion gas generated by combustion of the pre-mixture coming from the pre-mixing nozzles is formed in the gas stagnation area and the flame holding ability is enhanced. Hence, the effect to realize the low NOx generation by the means (1) of the present invention can be further ensured.[0015]
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIGS. [0016] 1(a) and (b) schematically show a gas turbine combustor of an embodiment according to the present invention, wherein FIG. 1(a) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 1(b) is a front view of a half portion of the combustor.
  • FIG. 2 is an enlarged longitudinal cross sectional view of one of pre-mixing nozzles. [0017]
  • FIG. 3 is the same view as FIG. 1([0018] a) in which a hatched portion is added.
  • FIGS. [0019] 4(a) and (b) schematically show a prior art gas turbine combustor, wherein FIG. 4(a) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 4(b) is a front view of a half portion of the combustor.
  • DESCRIPTION OF THE PREFERRED EMBODIMENT
  • Herebelow, an embodiment according to the present invention will be described with reference to the appended drawings. [0020]
  • FIGS. [0021] 1(a) and (b) schematically show a gas turbine combustor of the embodiment, wherein FIG. 1(a) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 1(b) is a front view of a half portion of the combustor. In FIGS. 1(a) and (b), numeral 10 designates a combustor body as an outer casing of the combustor and eight pre-mixing nozzles 11 are provided therein being connected to each other around a central axis of the combustor body 10. The pre-mixing nozzles 11 are constructed so as to have their front ends projected beyond a base plate 17, that will be described later. Numeral 12 designates a pilot nozzle, that is arranged on the central axis of the combustor body 10. Numeral 13 designates a combustor, that includes the combustor body 10 and other components arranged therein. The combustor body 10 comprises therein an inner cylindrical member 13 a and an outer cylindrical member 13 b. The outer cylindrical member 13 b has its inner diameter made larger than an outer diameter of the inner cylindrical member 13 a as well as larger than an outer diameter of a cylindrical member of the prior art combustor. The outer cylindrical member 13 b is arranged surrounding a front end portion of the inner cylindrical member 13 a and extending downstream of the inner cylindrical member 13 a so as to cover a combustion zone of the combustor 13. Numeral 14 designates a flame holding cone, that has its front end portion eliminated to be made shorter than the prior art flame holding cone. Numeral 17 designates the base plate, that is a member supporting the eight pre-mixing nozzles 11 to an inner circumferential wall surface of the inner cylindrical member 13 a.
  • FIG. 2 is an enlarged longitudinal cross sectional view of one of the pre-mixing nozzles [0022] 11. The pre-mixing nozzle 11 has its front portion made in a double structure having a pre-mixing nozzle portion 21 of the inner side and an outer sleeve 23 of the outer side. While illustration is omitted, the outer sleeve 23 is supported to the pre-mixing nozzle portion 21 via a plurality of rib members. While the pre-mixing nozzle in the prior art has its front end cut at the position of its base plate without projecting further, the pre-mixing nozzle 11 of the present invention has its front end projected beyond the base plate 17. That is, a front end of the outer sleeve 23 projects frontward beyond the position of the base plate 17. Numeral 14 designates a flame holding cone, that has its front end portion cut by the projection of the outer sleeve 23 to be made shorter. Numeral 22 designates a swirler vane, construction of which is the same as that of the prior art one.
  • In the combustor described above with reference to FIGS. 1 and 2, main fuel [0023] 40 flows into the eight pre-mixing nozzles 11 and is pre-mixed with air to form a pre-mixture for combustion in the combustion zone of the combustor 13. The air is supplied from a compressor (not shown) to be fed into the combustor 13 flowing through an inner peripheral space portion of the combustor body 10, as shown by arrows 50 in FIG. 1(a), and further flowing through the pre-mixing nozzle portion 21 as well as through an outer peripheral space portion of the pre-mixing nozzle portion 21, as shown by arrows 51 in FIG. 2. On the other hand, pilot fuel 41 is supplied into the combustor 13 through the pilot nozzle 12 of the-combustor central position and burns there together with the pre-mixture.
  • In a front central space portion of the flame holding cone [0024] 14 of the pilot nozzle 12, a high temperature gas inner circulating flow 15 is generated by the pilot fuel. Also, in an inner peripheral space portion of the outer cylindrical member 13 b in front of the pre-mixing nozzle 11, a high temperature gas outer circulating flow 16 is generated by the pre-mixture coming from the pre-mixing nozzle 11. Thus, by these two circulating flows 15, 16, the flame holding is securely effected. A gas stagnation area is formed in the inner peripheral space portion of the outer cylindrical member 13 b in front of the pre-mixing nozzle 11 by the construction of the combustor 13 comprising the inner cylindrical member 13 a and the outer cylindrical member 13 b and having the inner diameter of the outer cylindrical member 13 b made larger. Thus, the high temperature gas outer circulating flow 16 is formed in this gas stagnation area as a circulating flow of a high temperature combustion gas generated by combustion of the main pre-mixture.
  • As the flame holding effected by the high temperature gas inner circulating flow [0025] 15 generated by the flame holding cone 14 is added, the flame holding ability is greatly enhanced by the construction of the high temperature gas inner and outer circulating flows 15, 16. Thus, the pilot fuel quantity, as so far necessitated for the flame holding, can be reduced and thereby the NOx quantity generated of the pilot fuel can be reduced and a very low NOx combustion can be realized.
  • As described with reference to FIG. 2, the pre-mixing nozzle [0026] 11 comprises the swirler vane 22, the pre-mixing nozzle portion 21 and the outer sleeve 23. The outer sleeve 23 is arranged with a predetermined gap being maintained from the pre-mixing nozzle portion 21 of the inner side thereof and the air, as shown by the arrows 51, flows into the gap, so that the pre-mixing nozzle portion 21 and the outer sleeve 23 that are heated by the high temperature gas can be sufficiently cooled.
  • Moreover, the front end of the pre-mixing nozzle [0027] 11, that is formed by the front end of the outer sleeve 23, projects beyond the base plate 17. By this projecting portion, the base plate 17, that is directly exposed to the high temperature gas outer circulating flow 16, is prevented from being overheated. In FIG. 2, where L is a projecting distance of the projecting portion, that is, a distance between a front side surface of the base plate 17 and the front end of the pre-mixing nozzle 11, and D is an outer diameter of the pre-mixing nozzle 11, that is, an outer diameter of the outer sleeve 23, if L is set to D/3 or more (L≧D/3), then the effect to prevent the overheat of the base plate 17 can be enhanced.
  • FIG. 3 is the same view as FIG. 1([0028] b) in which a hatched portion is added. In FIG. 3, letter P is defined as a pitch circle that is a circle on which central axes of all of the pre-mixing nozzles 11 are arranged. An inner diameter of the outer cylindrical member 13 b, that corresponds to a diameter of the combustion zone in the combustor, is set such that, where an area is taken on a radial directional plane of the combustor, the area inside of the outer cylindrical member 13 b and outside of the pitch circle P, less the area taken by the pre-mixing nozzles 11 outside of the pitch circle P, that is, the area shown by the hatched portion in FIG. 3, is a half or more of the area of all the pre-mixing nozzles 11. By so selecting the diameter of the combustion zone in the combustor, the abovementioned gas stagnation area is effectively formed in the front outer side space portion of the pre-mixing nozzles 11 and the flame holding ability can be greatly enhanced.
  • According to the gas turbine combustor constructed as described above, a remarkable NOx reduction effect can be obtained. For example, NOx quantity of 25 PPM in the prior art can be reduced to 10 PPM or less. [0029]
  • While the preferred form of the present invention has been described, it is to be understood that the invention is not limited to the particular construction and arrangement herein illustrated and described but embraces such modified forms thereof as come within the scope of the appended claims. [0030]

Claims (4)

    What is claimed is:
  1. 1. A gas turbine combustor comprising a pilot nozzle arranged on a central axis of said combustor and a plurality of pre-mixing nozzles arranged around said pilot nozzle, wherein a diameter of a combustion zone of said combustor is set such that, where an area is taken on a radial directional plane of said combustor, the area inside of said combustion zone and outside of a pitch circle that is defined as a circle on which all central axes of said plurality of pre-mixing nozzles are arranged, less the area taken by said plurality of pre-mixing nozzles outside of said pitch circle, is a half or more of the area of all of said plurality of pre-mixing nozzles.
  2. 2. A gas turbine combustor as claimed in claim 1, wherein each of said plurality of pre-mixing nozzles has its front end projected beyond a base plate that supports said pre-mixing nozzle and a projecting distance of such projected front end is set to one third or more of an outer diameter of said pre-mixing nozzle.
  3. 3. A gas turbine combustor as claimed in claim 1, wherein each of said plurality of pre-mixing nozzles has its front portion made in a double structure having inner and outer members with a predetermined gap being maintained between said inner and outer members and air is flowable in said gap.
  4. 4. A gas turbine combustor as claimed in claim 1, wherein a combustor body as an outer casing of said combustor comprises therein an inner cylindrical member and an outer cylindrical member, said inner cylindrical member is arranged surrounding said plurality of pre-mixing nozzles and said outer cylindrical member has its inner diameter made larger than an outer diameter of said inner cylindrical member and is arranged surrounding a front end portion of said inner cylindrical member and extending downstream of said inner cylindrical member so as to cover said combustion zone to thereby enable to enlarge the diameter of said combustion zone beyond an inner diameter of said inner cylindrical member.
US10198368 2001-08-24 2002-07-19 Gas turbine combustor Abandoned US20030037549A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2001-254360 2001-08-24
JP2001254360A JP2003065537A (en) 2001-08-24 2001-08-24 Gas turbine combustor

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US20030037549A1 true true US20030037549A1 (en) 2003-02-27

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EP (1) EP1288576A3 (en)
JP (1) JP2003065537A (en)
CN (1) CN1172116C (en)
CA (1) CA2394118A1 (en)

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US20040020210A1 (en) * 2001-06-29 2004-02-05 Katsunori Tanaka Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20080078179A1 (en) * 2004-11-09 2008-04-03 Siemens Westinghouse Power Corporation Extended flashback annulus in a gas turbine combustor
US20080131824A1 (en) * 2006-10-26 2008-06-05 Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. Burner device and method for injecting a mixture of fuel and oxidant into a combustion space
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US20140109587A1 (en) * 2012-08-21 2014-04-24 General Electric Company System and method for reducing modal coupling of combustion dynamics
US20140338338A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
US9255711B2 (en) * 2012-08-21 2016-02-09 General Electric Company System for reducing combustion dynamics by varying fuel flow axial distances
CN105423342A (en) * 2016-01-12 2016-03-23 西北工业大学 Cavity wall evaporating pipe of combustion chamber of mini-sized engine
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9618333B2 (en) 2012-09-24 2017-04-11 Mitsubishi Hitachi Power Systems, Ltd. Clearance measurement device and clearance measurement method for combustor
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors

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US7007477B2 (en) 2004-06-03 2006-03-07 General Electric Company Premixing burner with impingement cooled centerbody and method of cooling centerbody
US20100192582A1 (en) 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
US8613187B2 (en) * 2009-10-23 2013-12-24 General Electric Company Fuel flexible combustor systems and methods
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US8991187B2 (en) 2010-10-11 2015-03-31 General Electric Company Combustor with a lean pre-nozzle fuel injection system
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US7171813B2 (en) * 2001-06-29 2007-02-06 Mitsubishi Heavy Metal Industries, Ltd. Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20040020210A1 (en) * 2001-06-29 2004-02-05 Katsunori Tanaka Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20080078179A1 (en) * 2004-11-09 2008-04-03 Siemens Westinghouse Power Corporation Extended flashback annulus in a gas turbine combustor
US7370466B2 (en) * 2004-11-09 2008-05-13 Siemens Power Generation, Inc. Extended flashback annulus in a gas turbine combustor
US20080131824A1 (en) * 2006-10-26 2008-06-05 Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. Burner device and method for injecting a mixture of fuel and oxidant into a combustion space
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US9151502B2 (en) * 2012-08-21 2015-10-06 General Electric Company System and method for reducing modal coupling of combustion dynamics
US20140109587A1 (en) * 2012-08-21 2014-04-24 General Electric Company System and method for reducing modal coupling of combustion dynamics
US9255711B2 (en) * 2012-08-21 2016-02-09 General Electric Company System for reducing combustion dynamics by varying fuel flow axial distances
US9618333B2 (en) 2012-09-24 2017-04-11 Mitsubishi Hitachi Power Systems, Ltd. Clearance measurement device and clearance measurement method for combustor
US20140338338A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
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US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9765973B2 (en) * 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
CN105423342A (en) * 2016-01-12 2016-03-23 西北工业大学 Cavity wall evaporating pipe of combustion chamber of mini-sized engine

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CN1403745A (en) 2003-03-19 application
CA2394118A1 (en) 2003-02-24 application
JP2003065537A (en) 2003-03-05 application
EP1288576A2 (en) 2003-03-05 application
EP1288576A3 (en) 2004-01-07 application
CN1172116C (en) 2004-10-20 grant

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