US3630024A - Air swirler for gas turbine combustor - Google Patents

Air swirler for gas turbine combustor Download PDF

Info

Publication number
US3630024A
US3630024A US7947A US3630024DA US3630024A US 3630024 A US3630024 A US 3630024A US 7947 A US7947 A US 7947A US 3630024D A US3630024D A US 3630024DA US 3630024 A US3630024 A US 3630024A
Authority
US
United States
Prior art keywords
air
swirler
slots
fuel
gas
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
US7947A
Other languages
English (en)
Inventor
Edward P Hopkins
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
Application granted granted Critical
Publication of US3630024A publication Critical patent/US3630024A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel

Definitions

  • An air swirler is provided in the head end of a gas turbine combustor such that, when reducing the smoke production, the flame will be stabilized and proper mixing of the combustion air and fuel will occur.
  • the proper amount of swirl and airflow must necessarily be provided.
  • air sweeper holes which direct part of the combustion air across the face of the fuel nozzle, thereby preventing the buildup of carbon particles.
  • gaseous fuel holes such that gaseous fuel may be burned by directing the fuel into the air swirler slots so that it is properly mixed with the combustion air.
  • the present invention relates generally to gas turbine combustors and more particularly to an air swirler for the use in a gas turbine combustor.
  • the present invention in addition to the particular air swirler design, relates to a method of reducing smoke by leaning out the primary zone of the combustion chamber, i.e., an additional amount of air in relation to the fuel supplied is added at the primary zone. It is known in the art that leaning out the fuel-air mixture reduces the amount of soot and smoke produced by the combustion process. When the attempt is made to lean out the primary zone or head end of the combustor, the problem exists that flame stability is reduced and possibly may be lost altogether. By the addition of the air swirler of the present invention around the fuel nozzle a free vortex flow is provided in the combustor and the flame front is effectively stabilized.
  • gas turbine combustors where a dual fuel capacity is desired, that is, one which has provisions for the flow of both a liquid fuel and a gaseous fuel it becomes a problem to keep the gas holes clean while operating on the liquid fuel. It is desirable to keep the exit from the gas holes at a point where only clean air exists, that is, in proximity with incoming combustion air. The air passing through the slots of the swirler prevents products of combustion and oil from entering the gas side of the nozzle. It is also desirable to impart to the gaseous fuel a swirling characteristic to induce complete mixing in the combustor.
  • one object of the present invention is to stabilize the flame while leaning out the head end, thereby reducing the smoke in the gas turbine exhaust.
  • a second object of the present invention is to prevent the buildup of a carbon deposit on the face of the fuel nozzle during operation.
  • a third object of the invention is to provide an air swirler which also acts as the gaseous fuel nozzle.
  • the present invention is practiced in one form by providing an improved air swirler around the fuel nozzle of a gas turbine combustor.
  • the swirler is comprised of a body member which has slots machined therein so that a plurality of blades are formed around the circumference of the body member.
  • the blades are formed such that the trailing edge surface has a definite measurable thickness.
  • a plurality of air sweeper holes are provided in the body member such that a portion of the combustion air passing to the swirler blades is directed through the air sweeper holes and across the face of the fuel nozzle, thus preventing the buildup of carbon deposits.
  • FIG. 1 is a front view looking at the face of the swirler.
  • FIG. 2 is a partial plan view showing the relative dimensions of the air swirler blades.
  • FIG. 3 is a view, in section, taken along lines III-III of FIG. 1.
  • FIG. 4 is a view, in section, of the air swirler with its associated fuel nozzle, both positioned in the combustor cap.
  • an air swirler is generally shown at l and is comprised of a body member 2 from which are machined a plurality of individual blade members 3. It will be appreciated that when the blade members 3 are formed, there are also formed a plurality of slots 4 about the circumference of the body member 2. Although it has been mentioned that the blades 3 are machined into the body member 2, any suitable means of forming the slots 4 in blade members 3 may be utilized.
  • One criterion for forming the blade members 3 is that the trailing edge or downstream surface (trailing edge with respect to the combustion airflow through the air swirler) indicated at 5 has a definite measurable dimension as opposed to a tapered edge.
  • a fuel nozzle hole 6 is positioned generally at the geometric center of the body member 2 in order to accommodate the fuel nozzle 7.
  • the relation of the fuel nozzle 7 to air swirler 1 may be seen by reference to FIG.
  • Air sweeper holes 8 which are utilized to keep the face of fuel nozzle 7 free from the buildup of carbon particles which normally accompanied the operation of a prior art gas turbine combustor.
  • Air sweeper holes 8 extend generally at an angle from the inner face 9 of the slots 4 to the upper or downstream face 10 of the body member 2.
  • the angle of the air sweeper holes 8, which is more clearly indicated in FIG. 3, is on the order of 2535, with 30 being the preferred angle in order to reduce the most amount of carbon buildup.
  • This angle formed with a plane normal to the swirler axis is indicated as a in FIG. 3.
  • the dimensions of the slots 4 and blade members 3 are critical and present themselves to be defined as certain ratios which must be met in order to provide the proper amount of swirl air to accomplish the objects of the invention. If too much air is allowed to enter through the slots 4 by providing a distance between blades 3 which is too great, it is possible to create such a lean head end that combustion cannot be supported. Also evident, if too much air is passed through the slots 4, is inefficient mixing of the combustion air and fuel.
  • This critical ratio presents itself as the ratio of the span of the blade face indicated as A to the width of the slot indicated as B. This ratio A/B, must be within a range of from 1.15 to 1.85 when the diameter of the combustion chamber is on the order of 15 inches so that the required 5-l0 percent of combustion air will pass through slots 4.
  • angle 7 Another critical dimension associated with blade members 3 is the angle 7 at which the blades 3 are positioned from a plane normal to the swirler axis. It is this angle y which determines the amount of swirl which is imparted to the combustion air passing through slots 4. If angle 7 is too small, thus causing too much swirl, the mixture of combustion air and fuel will form a free vortex with too much strength and throw fuel on the combustor walls (not shown). Carbon will also be built up on the face of the fuel nozzle. [f the angle 7 is too large, not enough swirl will be imparted to the entering combustion air. Not enough swirl provides insufficient mixing of the combustion air and fuel. It has been found that angle y, for the proper amount of swirl, should be maintained between 55 to 65 with the desired angle at 60.
  • the air swirler may be adapted to actually become the gaseous fuel nozzle, even when the standard fuel nozzle 7 is in place.
  • a plurality of individual gas holes 11 are positioned in the body member 2 of the air swirler l and extend from the bottom or upstream face 12 of body member 2 on the inside of gas wall or mounting member 13 generally to the inside face 9 of the slot 4.
  • the gas holes 11 provide an outlet for the gaseous fuel in every other slot 4.
  • the angle B at which the gas holes 11 are positioned in the body member 2 is critical and should fall within a range of from 25 to 65 with the preferred angle measured from a plane normal to the swirler axis being 35.
  • Fuel nozzle 7 is shown in combination with the air swirler l at the head end of the gas turbine combustor, the fuel paths leading to the combustion chamber are indicated. In the head end it will be appreciated that either a liquid fuel or a gaseous fuel may be burned at any one time.
  • Fuel nozzle 7 is comprised of an outer wall 14 which, together with the mounting member or gas wall 13, forms the passage 15 which communicates with the gas holes 11 thus essentially forming the gaseous fuel nozzle.
  • the fuel nozzle 7 When it is desired to use liquid fuel alone, the fuel nozzle 7 will be operative.
  • the liquid fuel enters an inner chamber 16 and thence flows through nozzle 17 where it is atomized by the flow of atomizing air (when used) which flows up through a circumferential sleeve 18 formed by the outer wall 14 and an inner wall 19.
  • the atomizing air finely atomizes the liquid fuel as it enters into the gas turbine combustor as indicated on FIG. 4.
  • FIG. 4 Also indicated in FIG. 4 is a portion of the combustor cap 20 which in actuality extends further outward until it meets the combustor liner (not shown) which is usually in the form of a cylindrical tube with combustion air holes disposed therealong.
  • the combustor cap 20 is mounted on a circumferential mounting ring 21 which, during operation, is juxtaposed against the outer faces of blade members 3 such that the slots 4 provide the only entry for the 5 to 10 percent of combustion air which passes through the air swirler l.
  • the core is a free vortex with the pressure being lower towards the fuel nozzle, thereby allowing the other combustion air which enters through the liner (not shown) to interact with the vortex, thus sweeping out the fuel rich pockets and providing complete mixing of the atomized fuel and combustion air.
  • An air swirler for directing and metering a generally axial flow of combustion air in the head end of a gas turbine combustor, comprising:
  • annular body portion including an upstream face and a downstream face normal to the swirler axis, and defining a central hole for accommodation therein of a fuel nozzle;
  • a plurality of angled blade members disposed about the circumference of said body and forming slots therebetween, the ratio of the span of the blade face to the width of the slot being within the range of 1.15 to 1.85.
  • the air swirler as recited in claim I further including a plurality of gas holes extending generally both in a radial and axial direction relative to the swirler axis, and communicating the upstream face of said annular body with the slots, and, arranged so that when operating on gaseous fuel, the gas is directed radially into the slots where it is swept by the combustion air thereby maintaining the slots free from residue buildup.
  • An air swirler for directing a generally axial flow of combustion air in the head end of a gas turbine combustor, comprising:
  • annular body portion including an upstream face and a downstream face normal to the swirler axis and defining a central hole for accommodation therein of a fuel nozzle
  • a plurality of angled blade members having an angle of from between 55 to 65 measured from a plane normal to the swirler axis, disposed about the circumference of said body and forming slots therebetween, the ratio of the span of the blade face to the width of the slot being within the range of 1.15 to 1.85,
  • a plurality of gas holes extending generally both in a radial and axial direction relative to the swirler axis, and communicating the upstream face of said annular body with 5 the slots, and, arranged so that when operating on gaseous fuel, the gas is directed radially into the slots where it is swept by the combustion air thereby maintaining the slots free from residue buildup.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
US7947A 1970-02-02 1970-02-02 Air swirler for gas turbine combustor Expired - Lifetime US3630024A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US794770A 1970-02-02 1970-02-02

Publications (1)

Publication Number Publication Date
US3630024A true US3630024A (en) 1971-12-28

Family

ID=21728974

Family Applications (1)

Application Number Title Priority Date Filing Date
US7947A Expired - Lifetime US3630024A (en) 1970-02-02 1970-02-02 Air swirler for gas turbine combustor

Country Status (5)

Country Link
US (1) US3630024A (de)
JP (1) JPS506888B1 (de)
CH (1) CH529972A (de)
DE (1) DE2104145C2 (de)
GB (1) GB1320263A (de)

Cited By (56)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3741483A (en) * 1971-12-10 1973-06-26 Mitsubishi Heavy Ind Ltd Combustion air supply arrangement for gas turbines
US3763650A (en) * 1971-07-26 1973-10-09 Westinghouse Electric Corp Gas turbine temperature profiling structure
US3775039A (en) * 1971-01-22 1973-11-27 Gen Chauffage Ind Pillard Frer Burners for liquid or gaseous fuels
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3788067A (en) * 1971-02-02 1974-01-29 Secr Defence Fuel burners
US3826079A (en) * 1971-12-15 1974-07-30 Phillips Petroleum Co Combustion method with selective cooling and controlled fuel mixing
US3831854A (en) * 1973-02-23 1974-08-27 Hitachi Ltd Pressure spray type fuel injection nozzle having air discharge openings
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
DE2456837A1 (de) * 1973-12-04 1975-06-05 France Etat Brennkammer fuer systeme zur speisung von verbrennungsmotoren mit vorverdichtung
US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
JPS5625607A (en) * 1979-08-01 1981-03-12 Rolls Royce Duplex fufl injection device for gas turbine engine
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4373325A (en) * 1980-03-07 1983-02-15 International Harvester Company Combustors
US4429538A (en) 1980-03-05 1984-02-07 Hitachi, Ltd. Gas turbine combustor
US4470262A (en) * 1980-03-07 1984-09-11 Solar Turbines, Incorporated Combustors
US4726760A (en) * 1985-06-10 1988-02-23 Stubinen Utveckling Ab Method of and apparatus for burning liquid and/or solid fuels in pulverized form
US4850194A (en) * 1986-12-11 1989-07-25 Bbc Brown Boveri Ag Burner system
US4854127A (en) * 1988-01-14 1989-08-08 General Electric Company Bimodal swirler injector for a gas turbine combustor
US4936090A (en) * 1988-07-15 1990-06-26 Sundstrand Corporation Assuring reliable starting of turbine engines
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US5288021A (en) * 1992-08-03 1994-02-22 Solar Turbines Incorporated Injection nozzle tip cooling
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5365738A (en) * 1991-12-26 1994-11-22 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
US5423132A (en) * 1992-09-30 1995-06-13 Graber; David A. Dryer apparatus using hot gases in free standing vortex
US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
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
US6405536B1 (en) * 2000-03-27 2002-06-18 Wu-Chi Ho Gas turbine combustor burning LBTU fuel gas
US6418726B1 (en) 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
US6474071B1 (en) 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US6484489B1 (en) 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6487861B1 (en) * 2001-06-05 2002-12-03 General Electric Company Combustor for gas turbine engines with low air flow swirlers
US20030079520A1 (en) * 2001-08-06 2003-05-01 Ingalls Melvin N. Method and apparatus for testing catalytic converter durability
US20030145580A1 (en) * 1999-12-22 2003-08-07 Wolfgang Ripper Device and method for generating a mixture of reducing agent and air
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US20040028588A1 (en) * 2001-08-06 2004-02-12 Webb Cynthia C. Method for accelerated aging of catalytic converters incorporating injection of volatilized lubricant
US20040025580A1 (en) * 2002-08-06 2004-02-12 Webb Cynthia C. Method for accelerated aging of catalytic converters incorporating engine cold start simulation
US20050039524A1 (en) * 2002-08-06 2005-02-24 Southwest Research Institute Testing using a non-engine based test system and exhaust product comprising alternative fuel exhaust
US20050050950A1 (en) * 2002-08-06 2005-03-10 Southwest Research Institute Component evaluations using non-engine based test system
US20060042254A1 (en) * 2004-09-02 2006-03-02 Shouhei Yoshida Combustor, gas turbine combustor, and air supply method for same
US7007864B2 (en) * 2002-11-08 2006-03-07 United Technologies Corporation Fuel nozzle design
US20060234174A1 (en) * 2005-03-17 2006-10-19 Southwest Research Institute. Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US20070039381A1 (en) * 2005-08-05 2007-02-22 Timmons Suzanne A Secondary Air Injector For Use With Exhaust Gas Simulation System
US7299137B2 (en) 2002-08-06 2007-11-20 Southwest Research Institute Method for drive cycle simulation using non-engine based test system
US20070289290A1 (en) * 2001-08-06 2007-12-20 Bartley Gordon J J System and method for producing diesel exhaust for testing diesel engine aftertreatment devices
US20090120094A1 (en) * 2007-11-13 2009-05-14 Eric Roy Norster Impingement cooled can combustor
US20090165435A1 (en) * 2008-01-02 2009-07-02 Michal Koranek Dual fuel can combustor with automatic liquid fuel purge
US20110072823A1 (en) * 2009-09-30 2011-03-31 Daih-Yeou Chen Gas turbine engine fuel injector
US8365534B2 (en) 2011-03-15 2013-02-05 General Electric Company Gas turbine combustor having a fuel nozzle for flame anchoring
US8425224B2 (en) 2005-03-17 2013-04-23 Southwest Research Institute Mass air flow compensation for burner-based exhaust gas generation system
US20130219903A1 (en) * 2012-02-28 2013-08-29 Hitachi, Ltd. Gas Turbine Combustor and Method for Operating Same
US8806848B2 (en) * 2012-09-05 2014-08-19 Hitachi, Ltd. Gas turbine combustor
US9500369B2 (en) 2011-04-21 2016-11-22 General Electric Company Fuel nozzle and method for operating a combustor
CN113544434A (zh) * 2019-03-25 2021-10-22 三菱动力株式会社 燃烧器及燃气轮机

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3684186A (en) * 1970-06-26 1972-08-15 Ex Cell O Corp Aerating fuel nozzle
US9347378B2 (en) 2013-05-13 2016-05-24 Solar Turbines Incorporated Outer premix barrel vent air sweep

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB704082A (en) * 1950-12-13 1954-02-17 Ransomes Sims & Jefferies Ltd Improvements in medium pressure oil burning furnaces for green crop and grain driers
US2825398A (en) * 1953-05-08 1958-03-04 Lucas Industries Ltd Liquid fuel injection nozzles
US3030773A (en) * 1959-01-22 1962-04-24 Gen Electric Vortex type combustion with means for supplying secondary air
FR1302273A (fr) * 1961-10-03 1962-08-24 Maschf Augsburg Nuernberg Ag Chambre pour la combustion simultanée de combustibles gazeux et non gazeux, en particulier pour installations de turbines à gaz
US3483700A (en) * 1967-09-27 1969-12-16 Caterpillar Tractor Co Dual fuel injection system for gas turbine engine
US3498055A (en) * 1968-10-16 1970-03-03 United Aircraft Corp Smoke reduction combustion chamber

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2976920A (en) * 1957-09-04 1961-03-28 Bell & Gossett Co Oil burner with air directing means
GB904142A (en) * 1959-04-17 1962-08-22 Rolls Royce Improvements in or relating to gas-turbine engines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB704082A (en) * 1950-12-13 1954-02-17 Ransomes Sims & Jefferies Ltd Improvements in medium pressure oil burning furnaces for green crop and grain driers
US2825398A (en) * 1953-05-08 1958-03-04 Lucas Industries Ltd Liquid fuel injection nozzles
US3030773A (en) * 1959-01-22 1962-04-24 Gen Electric Vortex type combustion with means for supplying secondary air
FR1302273A (fr) * 1961-10-03 1962-08-24 Maschf Augsburg Nuernberg Ag Chambre pour la combustion simultanée de combustibles gazeux et non gazeux, en particulier pour installations de turbines à gaz
US3483700A (en) * 1967-09-27 1969-12-16 Caterpillar Tractor Co Dual fuel injection system for gas turbine engine
US3498055A (en) * 1968-10-16 1970-03-03 United Aircraft Corp Smoke reduction combustion chamber

Cited By (77)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775039A (en) * 1971-01-22 1973-11-27 Gen Chauffage Ind Pillard Frer Burners for liquid or gaseous fuels
US3788067A (en) * 1971-02-02 1974-01-29 Secr Defence Fuel burners
US3763650A (en) * 1971-07-26 1973-10-09 Westinghouse Electric Corp Gas turbine temperature profiling structure
US3741483A (en) * 1971-12-10 1973-06-26 Mitsubishi Heavy Ind Ltd Combustion air supply arrangement for gas turbines
US3826079A (en) * 1971-12-15 1974-07-30 Phillips Petroleum Co Combustion method with selective cooling and controlled fuel mixing
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
US3831854A (en) * 1973-02-23 1974-08-27 Hitachi Ltd Pressure spray type fuel injection nozzle having air discharge openings
DE2456837A1 (de) * 1973-12-04 1975-06-05 France Etat Brennkammer fuer systeme zur speisung von verbrennungsmotoren mit vorverdichtung
US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
JPS5625607A (en) * 1979-08-01 1981-03-12 Rolls Royce Duplex fufl injection device for gas turbine engine
US4429538A (en) 1980-03-05 1984-02-07 Hitachi, Ltd. Gas turbine combustor
US4373325A (en) * 1980-03-07 1983-02-15 International Harvester Company Combustors
US4470262A (en) * 1980-03-07 1984-09-11 Solar Turbines, Incorporated Combustors
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US4726760A (en) * 1985-06-10 1988-02-23 Stubinen Utveckling Ab Method of and apparatus for burning liquid and/or solid fuels in pulverized form
US4850194A (en) * 1986-12-11 1989-07-25 Bbc Brown Boveri Ag Burner system
US4854127A (en) * 1988-01-14 1989-08-08 General Electric Company Bimodal swirler injector for a gas turbine combustor
US4936090A (en) * 1988-07-15 1990-06-26 Sundstrand Corporation Assuring reliable starting of turbine engines
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5365738A (en) * 1991-12-26 1994-11-22 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
US5288021A (en) * 1992-08-03 1994-02-22 Solar Turbines Incorporated Injection nozzle tip cooling
US5423132A (en) * 1992-09-30 1995-06-13 Graber; David A. Dryer apparatus using hot gases in free standing vortex
US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
US20030145580A1 (en) * 1999-12-22 2003-08-07 Wolfgang Ripper Device and method for generating a mixture of reducing agent and air
US6848251B2 (en) * 1999-12-22 2005-02-01 Robert Bosch Gmbh Device and method for producing a reducing agent air-mixture
US6405536B1 (en) * 2000-03-27 2002-06-18 Wu-Chi Ho Gas turbine combustor burning LBTU fuel gas
US6381964B1 (en) 2000-09-29 2002-05-07 General Electric Company Multiple annular combustion chamber swirler having atomizing pilot
US6474071B1 (en) 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US6367262B1 (en) 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6363726B1 (en) 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
US6609377B2 (en) 2000-09-29 2003-08-26 General Electric Company Multiple injector combustor
US6418726B1 (en) 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
US6484489B1 (en) 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6487861B1 (en) * 2001-06-05 2002-12-03 General Electric Company Combustor for gas turbine engines with low air flow swirlers
US20040028588A1 (en) * 2001-08-06 2004-02-12 Webb Cynthia C. Method for accelerated aging of catalytic converters incorporating injection of volatilized lubricant
US7625201B2 (en) 2001-08-06 2009-12-01 Southwest Research Institute Method and apparatus for testing catalytic converter durability
US7347086B2 (en) 2001-08-06 2008-03-25 Southwest Research Institute System and method for burner-based accelerated aging of emissions control device, with engine cycle having cold start and warm up modes
US20030079520A1 (en) * 2001-08-06 2003-05-01 Ingalls Melvin N. Method and apparatus for testing catalytic converter durability
US20070289290A1 (en) * 2001-08-06 2007-12-20 Bartley Gordon J J System and method for producing diesel exhaust for testing diesel engine aftertreatment devices
US20070283749A1 (en) * 2001-08-06 2007-12-13 Southwest Research Institute System and method for burner-based accelerated aging of emissions control device, with engine cycle having cold start and warm up modes
US7277801B2 (en) 2001-08-06 2007-10-02 Southwest Research Institute Method for testing catalytic converter durability
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US7175422B2 (en) 2001-08-06 2007-02-13 Southwest Research Institute Method for accelerated aging of catalytic converters incorporating injection of volatilized lubricant
US20060201239A1 (en) * 2001-08-06 2006-09-14 Webb Cynthia C Method for Testing Catalytic Converter Durability
US7741127B2 (en) 2001-08-06 2010-06-22 Southwest Research Institute Method for producing diesel exhaust with particulate material for testing diesel engine aftertreatment devices
US7140874B2 (en) 2001-08-06 2006-11-28 Southwest Research Institute Method and apparatus for testing catalytic converter durability
US7412335B2 (en) 2002-08-06 2008-08-12 Southwest Research Institute Component evaluations using non-engine based test system
US7212926B2 (en) 2002-08-06 2007-05-01 Southwest Research Institute Testing using a non-engine based test system and exhaust product comprising alternative fuel exhaust
US6983645B2 (en) 2002-08-06 2006-01-10 Southwest Research Institute Method for accelerated aging of catalytic converters incorporating engine cold start simulation
US7299137B2 (en) 2002-08-06 2007-11-20 Southwest Research Institute Method for drive cycle simulation using non-engine based test system
US20050050950A1 (en) * 2002-08-06 2005-03-10 Southwest Research Institute Component evaluations using non-engine based test system
US20050039524A1 (en) * 2002-08-06 2005-02-24 Southwest Research Institute Testing using a non-engine based test system and exhaust product comprising alternative fuel exhaust
US20040025580A1 (en) * 2002-08-06 2004-02-12 Webb Cynthia C. Method for accelerated aging of catalytic converters incorporating engine cold start simulation
US7007864B2 (en) * 2002-11-08 2006-03-07 United Technologies Corporation Fuel nozzle design
US7891191B2 (en) * 2004-09-02 2011-02-22 Hitachi, Ltd. Combustor, gas turbine combustor, and air supply method for same
US20110011092A1 (en) * 2004-09-02 2011-01-20 Shouhei Yoshida Combustor, gas turbine combustor, and air supply method for same
US20060042254A1 (en) * 2004-09-02 2006-03-02 Shouhei Yoshida Combustor, gas turbine combustor, and air supply method for same
US8047003B2 (en) 2004-09-02 2011-11-01 Hitachi, Ltd. Combustor, gas turbine combustor, and air supply method for same
US8425224B2 (en) 2005-03-17 2013-04-23 Southwest Research Institute Mass air flow compensation for burner-based exhaust gas generation system
US20060234174A1 (en) * 2005-03-17 2006-10-19 Southwest Research Institute. Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US7748976B2 (en) 2005-03-17 2010-07-06 Southwest Research Institute Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US20070039381A1 (en) * 2005-08-05 2007-02-22 Timmons Suzanne A Secondary Air Injector For Use With Exhaust Gas Simulation System
US7617684B2 (en) 2007-11-13 2009-11-17 Opra Technologies B.V. Impingement cooled can combustor
US20090120094A1 (en) * 2007-11-13 2009-05-14 Eric Roy Norster Impingement cooled can combustor
US20090165435A1 (en) * 2008-01-02 2009-07-02 Michal Koranek Dual fuel can combustor with automatic liquid fuel purge
US20110072823A1 (en) * 2009-09-30 2011-03-31 Daih-Yeou Chen Gas turbine engine fuel injector
US8365534B2 (en) 2011-03-15 2013-02-05 General Electric Company Gas turbine combustor having a fuel nozzle for flame anchoring
US9500369B2 (en) 2011-04-21 2016-11-22 General Electric Company Fuel nozzle and method for operating a combustor
US20130219903A1 (en) * 2012-02-28 2013-08-29 Hitachi, Ltd. Gas Turbine Combustor and Method for Operating Same
US9115899B2 (en) * 2012-02-28 2015-08-25 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and method for operating same
US8806848B2 (en) * 2012-09-05 2014-08-19 Hitachi, Ltd. Gas turbine combustor
CN113544434A (zh) * 2019-03-25 2021-10-22 三菱动力株式会社 燃烧器及燃气轮机
CN113544434B (zh) * 2019-03-25 2022-08-23 三菱重工业株式会社 燃烧器及燃气轮机
US12222105B2 (en) 2019-03-25 2025-02-11 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine

Also Published As

Publication number Publication date
DE2104145A1 (de) 1971-08-19
DE2104145C2 (de) 1987-01-22
GB1320263A (en) 1973-06-13
JPS506888B1 (de) 1975-03-19
CH529972A (de) 1972-10-31

Similar Documents

Publication Publication Date Title
US3630024A (en) Air swirler for gas turbine combustor
EP0895024B1 (de) Wirbelmischvorrichtung für eine Brennkammer
US3608309A (en) Low smoke combustion system
US5402633A (en) Premix gas nozzle
US4265615A (en) Fuel injection system for low emission burners
CN100557317C (zh) 一种航空发动机贫油预混预蒸发低污染燃烧室
US5680766A (en) Dual fuel mixer for gas turbine combustor
US4807541A (en) Apparatus for low concentration NOx combustion
US4271674A (en) Premix combustor assembly
US5987889A (en) Fuel injector for producing outer shear layer flame for combustion
EP1413830B1 (de) Druckluftinjektor für Kraftstoff mit verbessertem Luftverteiler und Pilot
US3648457A (en) Combustion apparatus
US6178752B1 (en) Durability flame stabilizing fuel injector with impingement and transpiration cooled tip
US5778676A (en) Dual fuel mixer for gas turbine combustor
CN102200291B (zh) 一种采用气动主级分级的低污染燃烧室
US4463568A (en) Fuel injector for gas turbine engines
US6571559B1 (en) Anti-carboning fuel-air mixer for a gas turbine engine combustor
US4941617A (en) Airblast fuel nozzle
EP1193447B1 (de) Brennkammer mit mehreren Einspritzdüsen
JPS6233490B2 (de)
JPH08505217A (ja) 燃料噴射装置
CN101799174A (zh) 主燃级切向供油的预混预蒸发燃烧室
RU2166695C2 (ru) Форсунка и способ предварительного смешения с использованием этой форсунки
US5896739A (en) Method of disgorging flames from a two stream tangential entry nozzle
CN107013941A (zh) 燃烧室燃油喷嘴装置