US3899884A - Combustor systems - Google Patents

Combustor systems Download PDF

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Publication number
US3899884A
US3899884A US094289A US9428970A US3899884A US 3899884 A US3899884 A US 3899884A US 094289 A US094289 A US 094289A US 9428970 A US9428970 A US 9428970A US 3899884 A US3899884 A US 3899884A
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US
United States
Prior art keywords
swirler
air
mixing chamber
combustion chamber
venturi
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.)
Expired - Lifetime
Application number
US094289A
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English (en)
Inventor
Edward E Ekstedt
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
Priority to US094289A priority Critical patent/US3899884A/en
Priority to CA121,071A priority patent/CA943352A/en
Priority to AU32634/71A priority patent/AU452434B2/en
Priority to CH1235971A priority patent/CH537519A/de
Priority to NL7111784A priority patent/NL7111784A/xx
Priority to GB4034571A priority patent/GB1353335A/en
Priority to DE2143012A priority patent/DE2143012C3/de
Priority to BE771990A priority patent/BE771990A/xx
Priority to NO3228/71A priority patent/NO134997C/no
Priority to FR7131637A priority patent/FR2116363B1/fr
Priority to DK431671A priority patent/DK132539C/da
Priority to JP6704971A priority patent/JPS5521250B1/ja
Application granted granted Critical
Publication of US3899884A publication Critical patent/US3899884A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to improvements in combustor systems, particularly in the generation of a hot gas stream as in gas turbine engines.
  • Combustor systems as employed in gas turbine engines, comprise a spray nozzle which injects fuel into a combustion zone. Once ignited, a continuous flame front is maintained in the combustion chamber as fuel and pressurized air flow therein and a high energy, hot gas stream is discharged therefrom.
  • the object of the invention is to reduce the temperature levels of fuel nozzles and, in so doing, minimize the buildup of carbon thereon and further, to maintain minimal smoke generation in the combustion process.
  • venturi into which the fuel spray is discharged.
  • the acceleration provided by the initial portion of the venturi tube accelerates mixing air introduced around the nozzle to an extent sufficient to prevent combustion for a predetermined distance from the nozzle. By thus displacing the flame front from the nozzle, its temperature may be reduced sufficiently to prevent undesirable carbon buildup thereon.
  • the divergent portion of the venturi tube re-expands the mixing air to discharge it into the combustion chamber at a relatively wide angle consistent with the smoke minimizing dispersion process referenced above.
  • venturi tube to the means for introducing mixing air as well as in the amount of mixing air introduced.
  • FIG. 1 is a schematic representation of a gas turbine engine employing a combustor of the type herein referenced;
  • FIG. 2 is an enlarged longitudinal section illustrating the details of the combustor referenced in FIG. 1 as they embody the present invention
  • FIG. 3 is a section taken on line IIl-IlI in FIG. 2;
  • FIG. 4 is a longitudinal section, similar to FIG. 2, illustrating another embodiment of the invention.
  • the illustrated engine comprises an axial flow compressor 10 which pressurizes air.
  • This pressurized air flows through an annular passageway 12 to an annular combustor 14 where fuel is introduced.
  • the pressurized air supports combustion of fuel within the combustor to generate a high energy level, hot gas stream.
  • This hot gas stream drives a turbine 16 which in turn powers the rotor of the compressor 10.
  • the hot gas stream is then converted to a useful output as by being discharged from a nozzle 17 to provide propulsive. thrust for an aircraft.
  • the combustor 14 as illustrated in FIG. 2, comprises outer and inner liners 18 and 20 which define an annular combustion chamber 21. These liners are joined by compositely formed dome portion 22 at their upstream ends. Cylindrical conduits or mixing chambers 24 which open into the dome portion 22 and the combustion chamber 21. Transition segments 26 blend the conduit openings into the dome portion. An axial flow swirler 28 is mounted at the upstream end of each conduit 24.
  • the swirler has a central opening which receives the discharge end 29 of a fuel spray nozzle 30.
  • the nozzle 30 may take many forms but is preferably characterized by at least one orifice outlet which produces a conical spray discharge having a relatively large included angle relative to an axis a which extends lengthwise of the mixing chamber.
  • the swirler 28 includes a row of passageways 32 annularly surrounding the axis of the nozzle discharge end 29. The passageways 32 are angled relative to the nozzle axis to produce a vortical flow field.
  • the swirler 28 may be mounted on the upstream end of the conduit 24 in the manner taught in copending US. application Ser. No. 796,391, filed Feb. 4, 1969 and of common assignment.
  • the referenced application also describes in further detail, the relationship of the swirler passageways 32 in obtaining a high degree of fuel dispersion for low smoke combustion.
  • the passageway 12 is defined by outer and inner, generally cylindrical casings 34 and 36 which extend along the lengths of the liners 18 and 20 are respectively spaced therefrom to define annular passageways 38 and 40.
  • An annular snout assembly 42 is secured to and projects upstream from the liners l8 and 20.
  • the snout assembly has a central passageway 43 having an entrance facing the discharge passageway 12 and discharging into an annular chamber 44 surrounding the entrances to the mixing chambers, i.e., swirler passageways 32.
  • the pressurized discharge from the compressor then is split into three annular flow-paths along passageways 38, 40 and 43.
  • Air from the passageways 38 and 40 may enter the combustion chamber 21 to serve three functions. First, it may pass through relatively small holes 46 which are oriented to cool the liners 18 and 20. Second, it may enter relatively large holes 48 to penetrate the combustion chamber and supply requisite, primary air for the combustion process. Third, it may enter holes (not shown) further downstream as dilution air to reduce the temperature of the hot gas stream to a temperature compatible with the capabilities of the materials forming the turbine. The air entering holes 48 may also serve a dilution function.
  • Air entering the snout passageway 43 and chamber 44 is then metered by and injected into the mixing chamber as discrete jets by the swirler passageways 32.
  • the vortical flow of mixing air is highly effective in dispersing or mixing the fuel from the spray cone into fine droplets which support a combustion process at a flame front generally identified by the broken line in FIG. 2.
  • the flame front is primarily controlled by two factors, once ignition is had. These are the presence and degree of a combustible mixture and the velocity of that mixture. In accordance with the present invention, these factors are taken into account in maintaining a desired distance between the flame front and the discharge end 29 of the fuel nozzle to minimize the temperature of the latter.
  • a venturi tube 50 is disposed concentrically of the nozzle axis a in a surrounding relationship with the spray cone discharged by the nozzle.
  • the inlet diameter of the venturi tube approximates the mean diameter of the annular row of swirler passageways 32.
  • approximately one-third of the swirler mixing air is captured by and axially accelerated through the convergent portion of the venturi tube 50.
  • the divergent portion of the venturi tube then re-expands the mixture to approximately the original cone shape of the nozzle discharge.
  • the divergent portion of the venturi terminates at a generally tangent relationship with the spray cone.
  • venturi tube 50 While maintaining the desired low smoke characteristics, the venturi tube 50 is highly effective in maintaining the flame front at a desired downstream distance. This distance can be controlled as desired by the length of venturi tube and its contraction ratio as well as the amount of mixing air flow therethrough, all of these factors being balanced so that the spray cone angle is relatively divergent as it discharges from the venturi tube into the combustion chamber.
  • venturi tube may be expressed in another fashion in that it increases the total pressure in the core of the vortical flow field created by the axial flow swirler. Without the venturi, the low pressure of the vortical core would enable recirculating primary air to flow forwardly, as indicated by the broken arrows, and create a combustible mixture and flame front closely adjacent the nozzle discharge. With the venturi such recirculation occurs, as indicated by the solid arrows, but is more limited in the magnitude of its upstream movement.
  • venturi tube is welded or otherwise bonded to the swirler 28 intermediate the lengths of the passageways 32. In so doing, added strength and rigidity is obtained for the swirler.
  • FIG. 4 illustrates an embodiment of the invention wherein all of the mixing air flows through a venturi tube 52 which also serves as a mixing chamber for introducing the dispersed fuel mixture into the combustion zone.
  • the action of this venturi in obtaining a desired downstream displacement of the flame front and a consequent reduction in nozzle temperature is essentially the same as previously described except that the velocity factor of the venturi is more predominant in displacing the flame front since a greater amount of air enters the venturi.
  • the benefits of the broader aspects of the present invention can be attained where the amount of mixing air flow is sufficient to produce a combustible mixture in the mixing chamber.
  • a combustor system comprising:
  • a spray nozzle for discharging fuel as an atomized cone into said mixing chamber, the axis of said spray cone extending lengthwise of said mixing chamber toward said combustion chamber,
  • venturi means surrounding said spray cone and through which at least a portion of the axially flowing air passes, and wherein the air introducing means additionally provide a vortical component to the air flow field,
  • venturi means comprise a venturi tube mounted within said mixing chamber
  • said air introducing means includes an annular row of generally radially on'ented passageways angled through said swirler,
  • said axial swirler has a central opening through which the discharge end of the spray nozzle projects
  • the inlet end of the venturi tube has a diameter intermediate the minimum and maximum diameters of the annular row of swirler passageways and is bonded to said swirler.
  • a combustor as in claim 2 wherein: a pressurized plenum is provided, in combination with the upstream face of said axial swirler, and Produce a Combustible mixture thereinthe swirler passageways meter air into the mixing means are provided for introducing further pressurized air into said combustion chamber sufficient to

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Nozzles (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
US094289A 1970-12-02 1970-12-02 Combustor systems Expired - Lifetime US3899884A (en)

Priority Applications (12)

Application Number Priority Date Filing Date Title
US094289A US3899884A (en) 1970-12-02 1970-12-02 Combustor systems
CA121,071A CA943352A (en) 1970-12-02 1971-08-23 Combustor systems
AU32634/71A AU452434B2 (en) 1970-12-02 1971-08-23 Combustor systems
CH1235971A CH537519A (de) 1970-12-02 1971-08-24 Verbrennungseinrichtung, insbesondere für Gasturbinentriebwerke
NL7111784A NL7111784A (de) 1970-12-02 1971-08-26
DE2143012A DE2143012C3 (de) 1970-12-02 1971-08-27 Brenneranordnung bei einer Gasturbinen-Brennkammer
GB4034571A GB1353335A (en) 1970-12-02 1971-08-27 Combustion equipment
BE771990A BE771990A (fr) 1970-12-02 1971-08-31 Perfectionnements a des systemes de combustion
NO3228/71A NO134997C (de) 1970-12-02 1971-08-31
FR7131637A FR2116363B1 (de) 1970-12-02 1971-09-01
DK431671A DK132539C (da) 1970-12-02 1971-09-02 Forbrendersystem
JP6704971A JPS5521250B1 (de) 1970-12-02 1971-09-02

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US094289A US3899884A (en) 1970-12-02 1970-12-02 Combustor systems

Publications (1)

Publication Number Publication Date
US3899884A true US3899884A (en) 1975-08-19

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Family Applications (1)

Application Number Title Priority Date Filing Date
US094289A Expired - Lifetime US3899884A (en) 1970-12-02 1970-12-02 Combustor systems

Country Status (12)

Country Link
US (1) US3899884A (de)
JP (1) JPS5521250B1 (de)
AU (1) AU452434B2 (de)
BE (1) BE771990A (de)
CA (1) CA943352A (de)
CH (1) CH537519A (de)
DE (1) DE2143012C3 (de)
DK (1) DK132539C (de)
FR (1) FR2116363B1 (de)
GB (1) GB1353335A (de)
NL (1) NL7111784A (de)
NO (1) NO134997C (de)

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US4215535A (en) * 1978-01-19 1980-08-05 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
FR2529954A1 (fr) * 1982-07-06 1984-01-13 Gen Electric Ensemble de carburation et procede de commande de l'ensemble
US4445338A (en) * 1981-10-23 1984-05-01 The United States Of America As Represented By The Secretary Of The Navy Swirler assembly for a vorbix augmentor
US4458479A (en) * 1981-10-13 1984-07-10 General Motors Corporation Diffuser for gas turbine engine
US4693074A (en) * 1983-11-26 1987-09-15 Rolls-Royce Plc Combustion apparatus for a gas turbine engine
WO1988006231A1 (en) * 1987-02-19 1988-08-25 Hi-Tech International Laboratory Company Limited Combustion system for internal combustion engine and combustor used therefor
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
US4974416A (en) * 1987-04-27 1990-12-04 General Electric Company Low coke fuel injector for a gas turbine engine
US4982564A (en) * 1988-12-14 1991-01-08 General Electric Company Turbine engine with air and steam cooling
US5117637A (en) * 1990-08-02 1992-06-02 General Electric Company Combustor dome assembly
US5123248A (en) * 1990-03-28 1992-06-23 General Electric Company Low emissions combustor
US5209067A (en) * 1990-10-17 1993-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Gas turbine combustion chamber wall structure for minimizing cooling film disturbances
US5261239A (en) * 1991-02-28 1993-11-16 Societe Nationale D'etude Et De Construction De Motors D'aviation Lean premixture combustion-chamber comprising a counterflow enclosure to stabilize the premixture flame
US5274995A (en) * 1992-04-27 1994-01-04 General Electric Company Apparatus and method for atomizing water in a combustor dome assembly
US5477671A (en) * 1993-07-07 1995-12-26 Mowill; R. Jan Single stage premixed constant fuel/air ratio combustor
US5490388A (en) * 1992-09-28 1996-02-13 Asea Brown Boveri Ltd. Gas turbine combustion chamber having a diffuser
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5592819A (en) * 1994-03-10 1997-01-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Pre-mixing injection system for a turbojet engine
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
JP2641551B2 (ja) * 1987-02-19 1997-08-13 有限会社ハイ・テク・インターナショナル研究所 内燃機関の燃焼方式及びその燃焼装置
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
US6021635A (en) * 1996-12-23 2000-02-08 Parker-Hannifin Corporation Dual orifice liquid fuel and aqueous flow atomizing nozzle having an internal mixing chamber
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
EP1106919A1 (de) * 1999-12-10 2001-06-13 General Electric Company Verfahren und Vorrichtung zur Verminderung der Emissionen in einer Brennkammer
US6363726B1 (en) 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
US6367262B1 (en) 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6381964B1 (en) 2000-09-29 2002-05-07 General Electric Company Multiple annular combustion chamber swirler having atomizing pilot
US6418726B1 (en) 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
US6460344B1 (en) 1999-05-07 2002-10-08 Parker-Hannifin Corporation Fuel atomization method for turbine combustion engines having aerodynamic turning vanes
US6474071B1 (en) 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
WO2002088602A1 (en) * 2001-04-25 2002-11-07 Pratt & Whitney Canada Corp. Turbine premixing combustor
US6484489B1 (en) 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6543233B2 (en) * 2001-02-09 2003-04-08 General Electric Company Slot cooled combustor liner
US6550251B1 (en) 1997-12-18 2003-04-22 General Electric Company Venturiless swirl cup
US6564555B2 (en) * 2001-05-24 2003-05-20 Allison Advanced Development Company Apparatus for forming a combustion mixture in a gas turbine engine
US20030196440A1 (en) * 1999-05-07 2003-10-23 Erlendur Steinthorsson Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
US20070119177A1 (en) * 2005-11-30 2007-05-31 General Electric Company Turbine engine fuel nozzles and methods of assembling the same
US20070227150A1 (en) * 2006-03-31 2007-10-04 Pratt & Whitney Canada Corp. Combustor
US20090212139A1 (en) * 2008-02-21 2009-08-27 Delavan Inc Radially outward flowing air-blast fuel injector for gas turbine engine
US20100162713A1 (en) * 2008-12-31 2010-07-01 Shui-Chi Li Cooled flameholder swirl cup
US20100199684A1 (en) * 2008-12-31 2010-08-12 Edward Claude Rice Combustion liner assembly support
US7779636B2 (en) 2005-05-04 2010-08-24 Delavan Inc Lean direct injection atomizer for gas turbine engines
US20110067403A1 (en) * 2009-09-18 2011-03-24 Delavan Inc Lean burn injectors having multiple pilot circuits
EP2592351A1 (de) 2011-11-09 2013-05-15 Delavan, Inc. Gestufte Pilotbrenner in reinen Drucklufteinspritzdüsen für Gasturbinenmotoren
CN103836647A (zh) * 2014-02-27 2014-06-04 中国科学院工程热物理研究所 一种文丘里管流道壁面结构
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9046039B2 (en) 2008-05-06 2015-06-02 Rolls-Royce Plc Staged pilots in pure airblast injectors for gas turbine engines
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160209038A1 (en) * 2013-08-30 2016-07-21 United Technologies Corporation Dual fuel nozzle with swirling axial gas injection for a gas turbine engine
US11371711B2 (en) * 2018-11-28 2022-06-28 General Electric Company Rotating detonation combustor with offset inlet
FR3142533A1 (fr) * 2022-11-28 2024-05-31 Safran Aircraft Engines Chambre de combustion pour turbomachine

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CH577627A5 (de) * 1974-04-03 1976-07-15 Bbc Sulzer Turbomaschinen
DE2641605C2 (de) * 1975-12-24 1986-06-19 General Electric Co., Schenectady, N.Y. Vorrichtung zur Zufuhr von Luft und Brennstoff
AT351131B (de) * 1976-07-05 1979-07-10 Henkel Kgaa Textilwaschmittel
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
JPS5634550A (en) * 1979-08-28 1981-04-06 Fuji Heavy Ind Ltd Fluid-pressure holding device for car brake
JPS58448A (ja) * 1981-06-22 1983-01-05 Kazuichi Tsukamoto ２系統式ブレ−キ油圧保持装置
JPS58100160U (ja) * 1981-12-28 1983-07-07 富士重工業株式会社 自動車用ブレ−キの制動液圧保持装置
DE3564024D1 (en) * 1984-02-29 1988-09-01 Lucas Ind Plc Combustion equipment
FR2673454B1 (fr) * 1991-02-28 1995-01-13 Snecma Chambre de combustion comportant une paroi de fond comprenant une pluralite de troncs de cones partiels.
GB2398375A (en) * 2003-02-14 2004-08-18 Alstom A mixer for two fluids having a venturi shape

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Cited By (76)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4215535A (en) * 1978-01-19 1980-08-05 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
US4458479A (en) * 1981-10-13 1984-07-10 General Motors Corporation Diffuser for gas turbine engine
US4445338A (en) * 1981-10-23 1984-05-01 The United States Of America As Represented By The Secretary Of The Navy Swirler assembly for a vorbix augmentor
FR2529954A1 (fr) * 1982-07-06 1984-01-13 Gen Electric Ensemble de carburation et procede de commande de l'ensemble
US4584834A (en) * 1982-07-06 1986-04-29 General Electric Company Gas turbine engine carburetor
US4693074A (en) * 1983-11-26 1987-09-15 Rolls-Royce Plc Combustion apparatus for a gas turbine engine
WO1988006231A1 (en) * 1987-02-19 1988-08-25 Hi-Tech International Laboratory Company Limited Combustion system for internal combustion engine and combustor used therefor
JP2641551B2 (ja) * 1987-02-19 1997-08-13 有限会社ハイ・テク・インターナショナル研究所 内燃機関の燃焼方式及びその燃焼装置
US4974416A (en) * 1987-04-27 1990-12-04 General Electric Company Low coke fuel injector for a gas turbine engine
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
US4982564A (en) * 1988-12-14 1991-01-08 General Electric Company Turbine engine with air and steam cooling
US5123248A (en) * 1990-03-28 1992-06-23 General Electric Company Low emissions combustor
US5117637A (en) * 1990-08-02 1992-06-02 General Electric Company Combustor dome assembly
US5209067A (en) * 1990-10-17 1993-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Gas turbine combustion chamber wall structure for minimizing cooling film disturbances
US5261239A (en) * 1991-02-28 1993-11-16 Societe Nationale D'etude Et De Construction De Motors D'aviation Lean premixture combustion-chamber comprising a counterflow enclosure to stabilize the premixture flame
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Also Published As

Publication number Publication date
AU452434B2 (en) 1974-09-05
DE2143012B2 (de) 1974-10-31
DE2143012A1 (de) 1972-06-15
DK132539C (da) 1976-05-24
GB1353335A (en) 1974-05-15
NO134997B (de) 1976-10-11
CH537519A (de) 1973-05-31
AU3263471A (en) 1973-03-01
NL7111784A (de) 1972-06-06
FR2116363A1 (de) 1972-07-13
JPS5521250B1 (de) 1980-06-09
DE2143012C3 (de) 1975-06-12
BE771990A (fr) 1971-12-31
CA943352A (en) 1974-03-12
FR2116363B1 (de) 1974-12-20
DK132539B (da) 1975-12-22
NO134997C (de) 1977-01-19

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