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EP0526152A1 - Vormischmehrstufenbrennkammer mit Einrichtung zur Verminderung von Flammenrückschlag - Google Patents

Vormischmehrstufenbrennkammer mit Einrichtung zur Verminderung von Flammenrückschlag Download PDF

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Publication number
EP0526152A1
EP0526152A1 EP92306854A EP92306854A EP0526152A1 EP 0526152 A1 EP0526152 A1 EP 0526152A1 EP 92306854 A EP92306854 A EP 92306854A EP 92306854 A EP92306854 A EP 92306854A EP 0526152 A1 EP0526152 A1 EP 0526152A1
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EP
European Patent Office
Prior art keywords
fuel
air
combustor
tubes
combustion chamber
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.)
Withdrawn
Application number
EP92306854A
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English (en)
French (fr)
Inventor
Gary Lee Leonard
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.)
General Electric Co
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0526152A1 publication Critical patent/EP0526152A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Definitions

  • This invention relates to premixed combustion systems which employ flashback resistant and highly efficient and compact premixing tubes. This system also achieves low emissions of oxides of nitrogen (NO x ), carbon monoxide (CO) and unburned hydrocarbons (UHC) over a large portion of the operating range of the engine.
  • NO x oxides of nitrogen
  • CO carbon monoxide
  • UHC unburned hydrocarbons
  • the invention provides a combustor system comprising : a combustion chamber for combusting a mixture of fuel and air; premixing combustor tubes for premixing said fuel and air before said fuel and air enter said combustion chamber, said tubes having first and second ends with holes located along said first end and said second end being substantially located within said combustion chamber; a fuel introduction means connected to said first end of said premixing combustor tubes; an air introduction means for introducing air into said premixing combustor tubes; and control means for controlling said fuel and said air while maintaining low emissions and a low flame temperature in said combustion chamber.
  • the invention provides a method for operating a low emissions, low flame temperature combustor having a combustion chamber for combusting a fuel and air mixture, a fuel introduction means, an air introduction means, an air assist fuel nozzle means, premixing combustor tubes for creating said fuel and air mixture before said fuel and air mixture enter said combustion chamber, and a control means, the steps of which are comprised of : flowing air into said combustor and said combustor tubes by means of said air introduction means to said combustion chamber; flowing fuel said combustion tubes by means of said fuel introduction means to said combustion chamber; flowing fuel and air through said air assist nozzle means; combusting said fuel and air mixture in said combustion chamber; and controlling said air introduction means and said fuel introduction means to create low emissions and a low flame temperature.
  • this invention fulfills these needs by providing a combustor system, comprising a combustion chamber for combusting a mixture of fuel and air, premixing combustor tubes for premixing said fuel and air before said fuel and air enter said combustion chamber, said tubes having first and second ends with holes located along said first end and said second end being substantially located within said combustion chamber, a fuel introduction means connected to said first end of said premixing combustor tubes; an air introduction means for introducing air into said premixing combustion tubes; and control means for controlling the fuel and air introduction means.
  • the fuel and air are mixed in the premixing combustor tubes such that the fuel and air are substantially completely mixed before they enter the combustion chamber.
  • the control means allows the system to be run at substantially less than 100% of its maximum load operation.
  • the combustor system can be operated with gaseous or liquid fuels.
  • the likelihood of an increase in CO and UHC emissions is minimized when the combustor system is run at substantially less than 100% of its maximum load operation.
  • the combustor system of this invention comprises a combustion chamber, 42 premixing tubes with their ends arranged in a staggered orientation within the combustion chamber, a fuel/air controller which controls the fuel and air being introduced into the premixing tubes and the combustor such that the combustor system can be run at substantially less than 100% of its maximum load operation while still reducing the likelihood of increased CO and UHC emissions.
  • the preferred combustor system offers the following advantages: easy assembly and repair, good stability; excellent economy; improved load operation performance; high strength for safety; reduced likelihood of an occurrence of flashback; and good fuel efficiency.
  • these factors of excellent economy, improved load operation and reduced likelihood of an occurrence of flashback are optimized to an extent considerably higher than heretofore achieved in prior, known combustor systems.
  • the flame temperature In order to achieve extremely low emissions of NO x it is known that the flame temperature must be maintained below 2800°F. To achieve low emissions of CO and UHC the flame temperature must be kept above 2500°F. Thus, to simultaneously achieve low emissions of NO x , CO and UHC, the flame temperature must be maintained between 2500° and 2800°F.
  • the velocity of the fuel/air mixture passing through the premixing tube be maintained at a sufficiently high value to keep flames from anchoring to the upstream end of the mixing tube in the event of, for example, a momentary flashback.
  • air flow through the gas turbine is momentarily interrupted, by compressor stall, for example, and the fame fashes back into the premixing tube, it is blown out as soon as the airflow through the gas turbine is restored to normal levels and damage to the premixer is thus avoided.
  • Combustor 2 includes outer shell 4, diffuser 5, liner 6, combustion chamber 7, premixing tubes 8,10,12,16,18,20, pilot nozzle 14, inlet air 22, fuel stage 50, and fuel manifolds 24,26,28,30,32,34,36.
  • liner 6 Located within outer shell 4, which is, preferably, constructed of any suitable steel is liner 6.
  • Liner 6, preferably, is constructed of Hastelloy®X, manufactured by International Nickel Company located in Huntington, West Virginia.
  • a thin heat resistant ceramic coating 120 (Fig. 5), preferably, of partially stabilized zirconia having a thickness of approximately 0.030 inches is applied to the inside surface of liner 6 by conventional coating techniques, for example, plasma spraying ( Figure 5). Coating 120 helps protect liner 6 from the adverse heating affects of the combustion that takes place in chamber 7.
  • Liner 6 encloses combustion chamber 7.
  • Combustion chamber 7 is where the fuel and air 22 are combusted.
  • Tubes 8,10,12,16,18,20 are positioned within combustion chamber 7 in order to substantially reduce the likelihood of an increase in CO and UHC as engine power is reduced.
  • Tube 8 preferably, is 15 inches long along the 1.50 inches diameter and 0.25 inches in diameter along extension 66. It is to be understood that tube 8 must have a length-to-diameter ratio of about 10 to assure good air and fuel mixing before entering chamber 7.
  • Tube 8 also contains approximately 36 holes 68, preferably, having a diameter of 0.375 inches which are formed in tube 8 by conventional hole forming techniques, for example, metal punching. Holes 68 allow air 22 to enter tube 8.
  • Tube 8 also includes extension 66 and threads 64. Extension 66 can be of varying lengths in order to provide the proper stagger engagement with tubes 8,20 having the longest extensions 66 and tubes 10,16 having the shortest extensions 66 ( Figure 1).
  • fuel stage 50 preferably, is constructed of any suitable metallic substance, such as steel.
  • inlets 52,54,56,58,60,62 which are connected to threads 64 and extensions 66 of tubes 8,10,12,16,18,20, respectively.
  • Conventional manifold inlets 38,40,42,44,46,48 are connected by conventional connectors to inlets 52,54,56,58,60,62, respectively.
  • Conventional fuel manifolds 24,26,28,32,34,36 are connected by conventional connectors to manifold inlets 38,40,42,44,46,48, respectively.
  • Fuel control system 80 consists of fuel manifolds 24,26,28,30,32,34,36, inlet lines 81,82,84,86,88,90,92, valves 94,96,98,99,100,102,104, conduit lines 106,110, control valve 112, line 114, shut off valve 116, fuel inlet line 118.
  • gaseous fuel from a fuel source preferably, a natural gas source (not shown) enters fuel inlet line 118 and proceeds past shut off valve 116 to line 114. fuel in line 114 proceeds to control valve 112.
  • the fuel proceeds along conduit line 106 to valves 94,96,98,99 and along conduit line 110 to valves 100,102,104. Fuel then can enter inlet lines 81,82,84 and 86,88,90,92 from valves 94,96,98,99,100,102,104, respectively. Finally, fuel from inlet lines 81,82,84,86,88,90,92 enters fuel manifolds 24,26,28,30,32,34,36, and ultimately, tubes 8,10,12,16,18,20 and pilot nozzle 14.
  • Figure 4 shows how tubes 8,10,12,16,18,20 are arranged in a circular bundle.
  • tubes 8a-8j ten tubes 8
  • ten tubes 20 numbered 20a-20j
  • seven tubes 10 numbered 10a-10g
  • seven tubes 10 numbered 18a-18g
  • four tubes 12 numbered 12a-12d
  • four tubes 16 numbered 16a-16d
  • tubes 8a-8j and 20a-20j are located in an outer ring of the bundle.
  • tubes 10a-10g and 18a-18g are located in the intermediate ring and tubes 12a-12d and 16a-16d are located in the inner most ring.
  • nozzle 14 is located at substantially the center of the bundle.
  • Tubes 8a-8j are connected to inlet 52a in that, preferably, inlet 52a is preferably a semi-circular enclosed shape with separate outlet ports connecting each of extensions 66 of tubes 8a-8j to create a fuel inlet apparatus from the gas soure (not shown) to each tube 8a-8j.
  • Tubes 20a-20j are connected to inlet 62a in substantially the same manner as tubes 8a-8j are connected to inlet 52a.
  • tubes 10a-10g and 18a-18j are connected to inlets 54a and 60a, respectively, in the same manner as tubes 8a-8j are connected to inlet 52a.
  • tubes 12a-12d and 16a-16d are connected to inlets 56a and 58a, respectively, in the same manner as tubes 8a-8j are connected to inlet 52a.
  • tubes 8,10,12 are rigidly fastened by conventional fastening techniques, such as welding, to liner 6 such that tube 8 projects further into chamber 7 than tube 10 which, in turn, projects further into chamber 7 than tube 12.
  • liner 6 is coated with a heat resistant coating 120 along its inner surface where it forms combustion chamber 7.
  • liner 6 contains holes 122 which are formed, preferably, by metal punching. It is to be understood that liner 6 is not treated with coating 120 at the area where holes 122 are located because coating 120 would not properly adhere the areas around holes 122. Holes 122 allows air 22 to enter into chamber 7 and interact with nozzle 14.
  • Wall 72 Located away from the outer wall liner 6, is cooling wall 72.
  • Wall 72 preferably, is constructed of any suitable heat resistant stainless steel. Holes 124 art formed in wall 72 by conventional hole forming techniques, such as metal punching. Holes 124 allow air 22 to cool the back side of liner 6. In particular, as air 22 rushes over the gap between wall 72 and liner 6, the velocity of the air creates a well known low pressure region in the space between wall 72 and liner 6. This low pressure zone then causes air to be drawn in through holes 124, along the outer wall of liner 6 and out between wall 72 and liner 6 which cools liner 6 near the area where tubes 8,10,12 art located within liner 6.
  • combustor 2 In operation of combustor 2, the gas from the natural gas source (not shown) has already been turned such that it is flowing through fuel manifolds 24,26,28,32,34,36. Also, fuel and air are being premixed in premixing tubes 8,10,12,16,18,20 such that the mixture is flowing along tubes 8,10,12,16,18,20, preferably, at around 180 ft/s. The velocity of 180 ft/s is employed because this fuel/air mixture velocity should also keep the flame in chamber 7 from going into the tubes thus, creating flashback. Finally, air 22 is entering combustor 2 near the exit area of chamber 7, preferably, at around 100-200 ft/s.
  • Figure 6 shows the fuel schedule for the fuel/air mixtures in tubes 8,10,12,16,18,20.
  • the fuel-to-air ratio divided by the stoichiometric fuel/air ratio (this normalized fuel-to-air ratio will be referred to as the equivalence ratio) for tubes 8,10,12,16,18,20 are shown along with the diffusion fraction from tube pilot 14, the percentage of fuel being introduced into fuel manifolds 24,26,28,32,34,36, the fraction of air flowing through tubes 8, 10, 12, 16, 18,20 and the air split and amount of total air in combustor 2.
  • Tubes 8,10,12 (or 20,18,16) are shown staggered. In this manner, the air flowing from tube 8 (or 20) during part load operation in which no fuel is added to tube 8 (or 20) does not interact with the fuel/air mixture from tubes 10 and 12 (or 16 and 18) and quench the flame thus causing high levels of CO and UHC. Similarly, when fuel is shut off to tube 10 (or 18) the air from this tube does not quench the flame from tube 12 (or 16).
  • Figure 7 is another embodiment of the present invention.
  • the same numbers found in Figures 1 and 7 represent like parts.
  • Figure 7 illustrates a premixed liquid fuel combustor 2.
  • liquid fuel preferably, #2 fuel oil is pumped by a conventional apparatus (not shown) to fuel valve 150.
  • the liquid fuel is then transported from control valve 150 along conduit lines 186, 188, 190, 192, 194, 196, to staging valves 172,170,168,184,182,180, respectively.
  • valves 172,170,168,184,180 are opened so fuel can flow through inlet lines 166,164,162,183,176,174 respectively, to liquid fuel manifolds 154, 152, 151, 156, 158, 160, respectively.
  • inlet lines 166,164,162,183,176,174 respectively, to liquid fuel manifolds 154, 152, 151, 156, 158, 160, respectively.
  • air is being transported through manifolds 24,26,28,32,34,36 and inlets 52,54,56,58,60,62.
  • inlet 62 As air is fed through inlet 62, preferably, at a pressure which is 50% higher than the pressure in chamber 7, typically, 150-600 psi.
  • the liquid fuel flows into inlet 62, the high velocity air atomizes the liquid fuel prior to it being introduced into tube 20.
  • the liquid fuel is modulated or staged in a manner similar to the gaseous fuel operation to achieve reduced load operation while maintainin low emissions of UHC and CO.
  • nozzle 14 is used to inject a mixture of oil and water thus providing dual fuel capability with low emissions of NOx.
  • the water suppresses the flame temperature.
  • nozzle 14 consists of gas inlet tube 74, fuel inlet tube 76, outlets 78 and end cap 79.
  • this mixture is transported from fuel manifold 130 to fuel inlet tube 76 where the fuel is sprayed out of outlets 78.
  • the water is mixed with the fuel oil to create the advantageous lower flame temperature in chamber 7. It is preferred that there be at least 6-12 outlets attached by conventional attachment means, such as welding, to the end of tube 76 near end cap 79.
  • air is introduced along manifold 30 ( Figure 3) to gas inlet tube 74.
  • the air flowing in tube 74 should be, preferably, at a pressure which is 20% higher than the pressure in chamber 7 which is preferably, between 150 and 600 psi.
  • the air in tube 74 interacts with the fuel that flows out of outlets 78 to create an atomized liquid fuel mist which can be combusted in chamber 7. It is to be understood that if a steam source is readily available as is the case with a conventional combined cycle gas turbine, the steam would be transported through tube 74 while only unmixed #2 fuel oil would be transported through tube 76. In this manner, as the oil leaves outlets 78 the oil can be atomized by the high velocity steam which also serves to reduce the flame temperature in zone 7.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP92306854A 1991-08-01 1992-07-28 Vormischmehrstufenbrennkammer mit Einrichtung zur Verminderung von Flammenrückschlag Withdrawn EP0526152A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US73899091A 1991-08-01 1991-08-01
US738990 2000-12-19

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JP (1) JPH05196232A (de)

Cited By (14)

* Cited by examiner, † Cited by third party
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EP0620402A1 (de) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Vormischbrennkammer mit konzentrischen Ringkanälen
EP0687865A1 (de) * 1994-06-13 1995-12-20 Westinghouse Electric Corporation Nachrüstungs-Gasturbinenbrenner mit niedrigem NOx-Ausstoss
WO1997040316A1 (en) * 1996-04-19 1997-10-30 Westinghouse Electric Corporation Premixed combustor with flashback arrestors
WO1999047859A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Fuel/air mixing disks for dry low-nox combustors
EP0935097A3 (de) * 1998-02-09 2000-01-19 Mitsubishi Heavy Industries, Ltd. Brennkammer
EP2216600A3 (de) * 2009-02-04 2010-09-01 Gas Turbine Efficiency Sweden AB Brennerdüse
EP2327933A1 (de) * 2009-11-30 2011-06-01 Siemens Aktiengesellschaft Brenneranordnung
CN102121699A (zh) * 2011-02-27 2011-07-13 江西中船航海仪器有限公司 一种部分预混式燃气燃烧头
EP2415993A3 (de) * 2010-08-05 2013-03-06 Hitachi Ltd. Kraftstoffregelungsvorrichtung und Kraftstoffregelungsverfahren für verbesserte Feuchtluftturbinen
CN102374533B (zh) * 2010-08-05 2015-11-25 通用电气公司 带具有内燃料回路与外燃料回路的燃料喷嘴的涡轮燃烧器
EP2213944A3 (de) * 2009-02-02 2018-01-03 General Electric Company Brennstoff-Einspritzeinrichtung für eine Gasturbine
CN113108314A (zh) * 2021-05-13 2021-07-13 中国联合重型燃气轮机技术有限公司 值班燃料喷嘴头、燃料喷嘴和燃气轮机
CN115451433A (zh) * 2022-09-22 2022-12-09 中国联合重型燃气轮机技术有限公司 一种用于燃气轮机燃烧室的燃料喷嘴预混系统
CN115523511A (zh) * 2022-09-02 2022-12-27 哈尔滨工程大学 一种基于对冲扩散火焰的氢燃料高效稳定低排放燃烧室

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JPH04118023A (ja) * 1990-06-07 1992-04-20 Kawasaki Steel Corp みみずの糞土を使用した脱臭方法及びその装置
US5836164A (en) * 1995-01-30 1998-11-17 Hitachi, Ltd. Gas turbine combustor
EP1125087B1 (de) * 1998-08-31 2005-05-18 Siemens Aktiengesellschaft Brenneranordnung
GB9929601D0 (en) * 1999-12-16 2000-02-09 Rolls Royce Plc A combustion chamber
US6755024B1 (en) * 2001-08-23 2004-06-29 Delavan Inc. Multiplex injector
US8147121B2 (en) * 2008-07-09 2012-04-03 General Electric Company Pre-mixing apparatus for a turbine engine
US8230687B2 (en) * 2008-09-02 2012-07-31 General Electric Company Multi-tube arrangement for combustor and method of making the multi-tube arrangement
US8424311B2 (en) * 2009-02-27 2013-04-23 General Electric Company Premixed direct injection disk
WO2010128882A1 (en) * 2009-05-07 2010-11-11 General Electric Company Multi-premixer fuel nozzle
US8261555B2 (en) * 2010-07-08 2012-09-11 General Electric Company Injection nozzle for a turbomachine
JP5721447B2 (ja) * 2011-01-17 2015-05-20 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器、これを備えたガスタービン、これを備えたガスタービンプラントおよびこの制御方法
US20120180487A1 (en) * 2011-01-19 2012-07-19 General Electric Company System for flow control in multi-tube fuel nozzle
US9134023B2 (en) * 2012-01-06 2015-09-15 General Electric Company Combustor and method for distributing fuel in the combustor
US9134030B2 (en) * 2012-01-23 2015-09-15 General Electric Company Micromixer of turbine 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
JP6159145B2 (ja) * 2013-05-14 2017-07-05 三菱日立パワーシステムズ株式会社 燃焼器
JP6522747B2 (ja) * 2014-10-06 2019-05-29 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 高周波数燃焼ダイナミックスのもとで振動モードを減衰するための燃焼器及び方法
CN104566466B (zh) * 2014-12-31 2017-12-01 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种防回火型燃料喷注装置、喷嘴
CN110579022B (zh) * 2018-06-07 2022-03-18 芜湖美的厨卫电器制造有限公司 燃气热水器及其防回火控制方法
JP7379265B2 (ja) * 2020-04-22 2023-11-14 三菱重工業株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン

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US3024607A (en) * 1949-08-19 1962-03-13 David A Washburn Sustained operation igniter for ram-jet missiles
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
GB2060436A (en) * 1979-09-22 1981-05-07 Rolls Royce Method of applying a ceramic coating to a metal workpiece
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GB2107448A (en) * 1980-10-21 1983-04-27 Rolls Royce Gas turbine engine combustion chambers
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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0620402A1 (de) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Vormischbrennkammer mit konzentrischen Ringkanälen
EP0766045A1 (de) * 1993-04-15 1997-04-02 Westinghouse Electric Corporation Arbeitsweise einer Vormischbrennkammer
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EP0687865A1 (de) * 1994-06-13 1995-12-20 Westinghouse Electric Corporation Nachrüstungs-Gasturbinenbrenner mit niedrigem NOx-Ausstoss
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