EP0849530A2 - Ajutages de combustible et des corps au centre associés - Google Patents

Ajutages de combustible et des corps au centre associés Download PDF

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Publication number
EP0849530A2
EP0849530A2 EP97310464A EP97310464A EP0849530A2 EP 0849530 A2 EP0849530 A2 EP 0849530A2 EP 97310464 A EP97310464 A EP 97310464A EP 97310464 A EP97310464 A EP 97310464A EP 0849530 A2 EP0849530 A2 EP 0849530A2
Authority
EP
European Patent Office
Prior art keywords
passage
cylindrical passage
cylindrical
axis
coaxial
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.)
Ceased
Application number
EP97310464A
Other languages
German (de)
English (en)
Other versions
EP0849530A3 (fr
Inventor
Stephen K. Kramer
Stephen F. Hauck
Timothy S. Snyder
William A. Sowa
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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
Priority claimed from US08/771,460 external-priority patent/US5791562A/en
Priority claimed from US08/770,277 external-priority patent/US5887795A/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0849530A2 publication Critical patent/EP0849530A2/fr
Publication of EP0849530A3 publication Critical patent/EP0849530A3/fr
Ceased legal-status Critical Current

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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/23—Geometry three-dimensional prismatic
    • F05B2250/232—Geometry three-dimensional prismatic conical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/30—Arrangement of components
    • F05B2250/32—Arrangement of components according to their shape
    • F05B2250/322—Arrangement of components according to their shape tangential
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • This invention relates to low NOx premix fuel nozzles, and particularly to such nozzles for use in gas turbine engines.
  • NOx nitrous oxides
  • a fuel nozzle which so operates is shown in U.S. Pat. No. 5,307,634, which discloses a scroll swirler with a conical centerbody.
  • This type of fuel nozzle is known as a tangential entry fuel nozzle, and comprises two offset cylindrical-arc scrolls connected to two endplates. Combustion air enters the swirler through two substantially rectangular slots formed by the offset scrolls, and exits through a combustor inlet port in one endplate and flows into the combustor.
  • a linear array of orifices located on the outer scroll opposite the inner trailing edge injects fuel into the airflow at each inlet slot from a manifold to produce a uniform fuel air mixture before exiting into the combustor.
  • Premix fuel nozzles of the tangential entry type have demonstrated low emissions of NOx relative to fuel nozzles of the prior art.
  • fuel nozzles such as the one disclosed in the aforementioned patent have exhibited an unacceptably short operational life when used in gas turbine engines, due in part to attachment of flames to the nozzle centerbody.
  • tangential entry fuel nozzles of this type have not been incorporated into commercially available gas turbine engines.
  • a centerbody disclosed herein comprises a longitudinal axis and a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares toward the frustum base thereof, and a curved portion which is integral with the frustum portion and preferably defines a portion of the surface generated by rotating a circle which is tangent to the frustum portion and has a center which lies radially outward thereof about the longitudinal axis.
  • the centerbody has a base which includes at least one air supply port extending therethrough, and an internal passageway.
  • the frustum portion tapers towards a discharge orifice of the internal passageway, and terminates at the plane in which the discharge orifice is located.
  • a fuel-lance that is coaxial with the axis and extends through the base and terminates within the internal passageway provides fuel to the air flow in the centerbody.
  • a tangential air entry fuel nozzle disclosed herein has a longitudinal axis and two cylindrical-arc scrolls with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle.
  • a combustor-end endplate has a combustor inlet port to permit air and fuel to exit the nozzle into a combustor.
  • the port includes a convergent surface, a divergent surface, and a cylindrical surface extending therebetween.
  • the convergent surface extends a first distance along the longitudinal axis of the nozzle, the cylindrical surface extends a second distance along the axis, and the second distance is preferably at least 5% of the first distance.
  • another endplate blocks the nozzle flow area, and the scrolls are secured between these endplates.
  • a centerbody located between the scrolls and coaxial with the axis has a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and a cylindrical portion that is coaxial with the longitudinal axis and defines the outer surface of a cylinder.
  • the centerbody has a base which includes at least one air supply port extending therethrough, and an internal passageway.
  • the frustum portion tapers towards a discharge orifice of the internal passageway, and the cylindrical portion is located between the frustum portion and the plane in which the discharge orifice is located.
  • a fuel-lance that is coaxial with the axis and extends through the base and terminates within the internal passageway provides fuel to the air flow in the centerbody.
  • Figure 1 is a cross-sectional view of a fuel nozzle of the present invention, taken along line 1-1 of Figure 2.
  • Figure 2 is a cross-sectional view looking down the longitudinal axis of the nozzle of the present invention.
  • Figure 3 is a cross-sectional view of the fuel nozzle of the present invention, taken along line 3-3 of Figure 2.
  • Figure 4 is a longitudinal cross-sectional view of a centerbody embodying the present invention.
  • Figure 5 is a cross-sectional view taken along line 5-5 of Figure 4.
  • Figure 6 is a longitudinal cross-sectional view of the centerbody of the present invention taken along line 6-6 of Figure 5.
  • a low NOx premix fuel nozzle 10 embodying the present invention includes a centerbody 12 within a scroll swirler 14.
  • the scroll swirler 14 includes first and second endplates 16,18, and the first endplate is connected to the centerbody 12 and is in spaced relation to the second endplate 18, which has a combustor inlet port 20 extending therethrough.
  • a plurality, and preferably two, cylindrical-arc scroll members 22, 24 extend from the first endplate 16 to the second endplate 18.
  • the scroll members 22, 24 are spaced uniformly about the longitudinal axis 26 of the nozzle 10 thereby defining a mixing zone 28 therebetween, as shown in Figure 2.
  • Each scroll member 22, 24 has a radially inner surface which faces the longitudinal axis 26 and defines a surface of partial revolution about a centerline 32, 34.
  • surface of partial revolution means a surface generated by rotating a line less than one complete revolution about one of the centerlines 32, 34.
  • Each scroll member 22 is in spaced relation to the other scroll member 24, and the centerline 32, 34 of each of the scroll members 22, 24 is located within the mixing zone 28, as shown in Figure 2.
  • each of the centerlines 32, 34 is parallel, and in spaced relation, to the longitudinal axis 26, and all of the centerlines 32, 34 are located equidistant from the longitudinal axis 26, thereby defining inlet slots 36, 38 extending parallel to the longitudinal axis 26 between each pair of adjacent scroll members 22, 24 for introducing combustion air 40 into the mixing zone 28.
  • Combustion supporting air 42 from the compressor passes through the inlet slots 36, 38 formed by the overlapping ends 44, 50, 48, 46 of the scroll members 22, 24 with offset centerlines 32, 34.
  • Each of the scroll members 22, 24 further includes a fuel conduit 52, 54 for introducing fuel into the combustion air 40 as it is introduced into the mixing zone 28 through one of the inlet slots 36, 38.
  • a first fuel supply line (not shown), which may supply either a liquid or gas fuel, but preferably gas, is connected to the each of the fuel conduits 52, 54.
  • the combustor inlet port 20, which is coaxial with the longitudinal axis 26, is located immediately adjacent the combustor 56 to discharge the fuel and combustion air from the present invention into the combustor 56, where combustion of the fuel and air takes place.
  • the centerbody 12 has a base 58 that has at least one, and preferably a plurality, of air supply ports 60, 62 extending therethrough, and the base 58 is perpendicular to the longitudinal axis 26 extending therethrough.
  • the centerbody 12 also has an internal passageway 64 that is coaxial with the longitudinal axis 26.
  • the internal passageway 64 includes a first cylindrical passage 66 having a first end 68 and a second end 70, and a second cylindrical passage 72 of greater diameter than the first cylindrical passage 66 and likewise having a first end 74 and a second end 76.
  • the second cylindrical passage 72 communicates with the first cylindrical passage 66 through a tapered passage 78 having a first end 80 that has a diameter equal to the diameter of the first cylindrical passage 66, and a second end 82 that has a diameter equal to the diameter of the second cylindrical passage 72.
  • Each of the passages 66, 72, 78 is coaxial with the longitudinal axis 26, and the first end-80 of the tapered passage 78 is integral with the second end 70 of the first cylindrical passage 66, while the second end 82 of the tapered passage 78 is integral with the first end 74 of the second cylindrical passage 72.
  • the first cylindrical passage 66 includes a discharge orifice 68 that is circular and coaxial with the longitudinal axis 26, and is located at the first end 68 of the first cylindrical passage 66.
  • the radially outer surface 84 of the centerbody 12 includes a frustum portion 86, which defines the outer surface of a frustum that is coaxial with the longitudinal axis 26 and flares toward the base 58, and a curved portion 88 which is integral with the frustum portion 86 and preferably defines a portion of the surface generated by rotating a circle, which is tangent to the frustum portion 86 and has a center which lies radially outward thereof, about the longitudinal axis 26.
  • the frustum portion 86 terminates at the plane within which the discharge orifice 68 is located, the diameter of the base (not to be confused with the base 58 of the centerbody) of the frustum portion 86 is 2.65 times greater than the diameter of the frustum portion 86 at the apex thereof, and the height 90 of the frustum portion 86 (the distance between the plane in which the base of the frustum portion 86 is located and the plane in which the apex of the frustum portion 86 is located) is approximately 1.90 times the diameter of the frustum portion 86 at the base thereof.
  • the curved portion 88 which is located between the base 58 and the frustum portion 86, provides a smooth transitional surface that directs combustion air 40 entering the tangential entry nozzle 10 adjacent the base 58.
  • the internal passageway 64 is located radially inward from the radially outer surface 84 of the centerbody 12, the frustum portion 86 is coaxial with the longitudinal axis 26, and the centerbody 12 is connected to the base 58 such that the frustum portion 86 tapers toward, and terminates at the discharge orifice 68 of the first cylindrical passage 66.
  • the base of the frustum portion 86 fits within a circle 92 inscribed in the mixing zone 28 and having its center 94 on the longitudinal axis 26.
  • the curved portion 88 must be cut to fit therein.
  • a ramp portion 96, 98 is left on the curved portion 88 where the curved portion 88 extends into each inlet slot 36, 38, and this portion is machined to form an aerodynamically shaped ramp 96, 98 that directs the air entering the inlet slot 36, 38 away from the base 58 and onto the curved portion 88 within the mixing zone 28.
  • an internal chamber 100 is located within the centerbody 12 between the base 58 and the second end 76 of the second cylindrical passage 72, which terminates at the chamber 100.
  • Air 102 is supplied to the chamber 100 through the air supply ports 60, 62 in the base 58 which communicate therewith, and the chamber 100, in turn, supplies air to the internal passageway 64 through the second end 76 of the second cylindrical passage 72.
  • the first endplate 16 has openings 104, 106 therein that are aligned with the air supply ports 60, 62 of the base 58 so as not to interfere with the flow of combustion air 102 from the compressor of the gas turbine engine.
  • a swirler 108 preferably of the radial inflow type known in the art, is coaxial with the longitudinal axis 26 and is located within the chamber 100 immediately adjacent the second end 76 of the second cylindrical passage 72 such that all air entering the internal passageway 64 from the chamber 100 must pass through the swirler 108.
  • a fuel lance 110 which likewise is coaxial with the longitudinal axis 26, extends through the base 58, the chamber 100, and the swirler 108, and into the second cylindrical passage 72 of the internal passageway 64.
  • the larger diameter of the second cylindrical passage 72 accommodates the cross-sectional area of the fuel-lance 110, so that the flow area within the second cylindrical passage 72 is essentially equal to the flow area of the first cylindrical passage 66.
  • a second fuel supply line (not shown), which may supply either a liquid or gas fuel, is connected to the fuel lance 110 to supply fuel to an inner passage 112 within the fuel lance 110.
  • Fuel jets 114 are located in the fuel lance 110, and provide a pathway for fuel to exit from the fuel lance 110 into the internal passageway 64.
  • the combustor inlet port 20 is coaxial with the longitudinal axis 26 and includes a convergent surface 116 and a cylindrical surface 118 that defines the throat of the inlet port.
  • the convergent surface 116 and the cylindrical surface 118 are likewise coaxial with the longitudinal axis 26, and the convergent surface 116 is located between the first endplate 16 and the cylindrical surface 118.
  • the convergent surface 116 is substantially conical in shape and tapers toward the cylindrical surface 118.
  • the cylindrical surface 118 extends between the throat plane 120 and the combustor surface 122 of the combustor port inlet 20, which is perpendicular to the longitudinal axis 26, and defines the exit plane 124 of the fuel nozzle 10 of the present invention.
  • the combustion air flowing therethrough must encounter the minimum flow area, or throat area, at the combustor inlet port 20.
  • the cylindrical surface 118 is located at a predetermined radius from the longitudinal axis 26 that is at least 10% less than the radius of the base of the frustum portion 86.
  • the convergent surface 116 terminates at the throat plane 120, where the diameter of the convergent surface 116 is equal to the diameter of the cylindrical surface 118.
  • the throat plane 120 is located between the exit plane 124 and the discharge orifice 68 of the internal passageway 64, and the convergent surface 116 is located between the cylindrical surface 118 and the first endplate 16.
  • the convergent surface 116 extends a predetermined distance 126 along the longitudinal axis 26 and the cylindrical surface -118 extends a second distance 128 along the longitudinal axis 26 that is at least 30% of the predetermined distance 126.
  • combustion air from the compressor of the gas turbine engine flows through the openings 104, 106 and the air supply ports 60, 62 in the base 58 and into the chamber 100 of the centerbody 12.
  • the combustion air exits the chamber 100 through the radial inflow swirler 108 and enters the internal passageway 64 with a substantial tangential velocity, or swirl, relative to the longitudinal axis 26.
  • this swirling combustion air passes the fuel lance 110, fuel, preferably in gaseous form, is sprayed from the fuel lance 110 into the internal passage 64 and mixes with the swirling combustion air.
  • the mixture of fuel and combustion air then flows from the second cylindrical passage 72 into the first cylindrical passage 66 through the tapered passage 78.
  • the mixture then proceeds down the length of the first cylindrical passage 66, exiting the first cylindrical passage 66 just short of, or at, the throat plane 120 of the combustor inlet port 20, providing a central stream of fuel air mixture.
  • Additional combustion air from the compressor of the gas turbine engine enters the mixing zone 28 through each of the inlet slots 36, 38.
  • Air entering the inlet slots 36, 38 immediately adjacent the base 58 is directed by the ramps 96, 98 onto the curved portion 88 within the mixing zone 28 of the scroll swirler 14.
  • Fuel, preferably gaseous fuel, supplied to the fuel conduits 52, 54 is sprayed into the combustion air passing through the inlet slots 36, 38 and begins mixing therewith. Due to the shape of the scroll members 22, 24, this mixture establishes an annular stream swirling about the centerbody 12, and the fuel/air mixture continues to mix as it swirls thereabout while progressing along the longitudinal axis 26 toward the combustor inlet port 20.
  • the swirl of the annular stream produced by the scroll swirler 14 is preferably co-rotational with the swirl of the fuel/air mixture in the first cylindrical passage 66, and preferably has an angular velocity at least as great as the angular velocity of the of the fuel/air mixture in the first cylindrical passage 66. Due to the shape of the centerbody 12, the axial velocity of the annular stream is maintained at speeds which prevent the combustor flame from migrating into the scroll swirler 14 and attaching to the outer surface 84 of the centerbody 12.
  • the swirling fuel/air mixture of the central stream Upon exiting the first cylindrical passage 66, the swirling fuel/air mixture of the central stream is surrounded by the annular stream of the scroll swirler 14, and the two streams enter the throat 120 of the combustor inlet port 20 and flow radially inward of the cylindrical surface 118 until reaching the exit plane 124 of the combustion inlet port 20 downstream of the mixing zone 28.
  • the fuel nozzle 10 described substantially reduces the flow oscillations and attendant heat release rates resulting therefrom, which caused excessive combustor pressure fluctuations and an acoustic tone.
  • the present invention eliminates the aforementioned interaction between the combustion process and the exit plane 124, resulting in significantly lower acoustic fluctuations. Consequently, the present invention provides a solution to the problem of excessive pressure fluctuations in the tangential entry fuel nozzle 10 while achieving the low emissions performance thereof.
  • the centerbody 10 has a significantly increased operational life as compared to the prior art when used in gas turbine engines by reducing the tendency of flames to attach to the centerbody 10. Consequently, the present invention also provides a solution to the problem that has prevented widespread use of tangential entry nozzles in gas turbine engines.
  • the invention provides a low NOx fuel nozzle which significantly increases the operational life thereof over the prior art when used in gas turbine engines and a tangential entry fuel nozzle that significantly reduces the tendency of flames to attach to the centerbody thereof while maintaining acceptably low levels of NOx production.
  • the centerebody may be used with other scroll swirler constructions, for example one in which instead of having a cylindrical surface 118, the combustor inlet port 20 may comprise a divergent surface 118 connecting the convergent surface to the combustion surface 122.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
EP97310464A 1996-12-20 1997-12-22 Ajutages de combustible et des corps au centre associés Ceased EP0849530A3 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US770277 1985-08-28
US771460 1985-08-30
US08/771,460 US5791562A (en) 1996-12-20 1996-12-20 Conical centerbody for a two stream tangential entry nozzle
US08/770,277 US5887795A (en) 1996-12-20 1996-12-20 Premix fuel injector with low acoustics

Publications (2)

Publication Number Publication Date
EP0849530A2 true EP0849530A2 (fr) 1998-06-24
EP0849530A3 EP0849530A3 (fr) 1999-06-09

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EP97310464A Ceased EP0849530A3 (fr) 1996-12-20 1997-12-22 Ajutages de combustible et des corps au centre associés

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EP (1) EP0849530A3 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0924463A3 (fr) * 1997-12-15 1999-12-08 United Technologies Corporation Injecteur de combustible avec un corps perturbateur et procédé pour prémélanger du combustible et de l'air
WO2000039504A1 (fr) * 1998-12-24 2000-07-06 Luminis Pty. Ltd. Dispositif pour le melange de fluides
EP1293725A1 (fr) * 2001-09-14 2003-03-19 United Technologies Corporation Injecteur de carburant
GB2432655A (en) * 2005-11-26 2007-05-30 Siemens Ag Combustion apparatus
CN101285591B (zh) * 2008-04-22 2010-06-09 北京航空航天大学 一种一体化燃油喷射径向旋流器预混预蒸发低污染燃烧室
EP2703721A1 (fr) * 2012-08-31 2014-03-05 Alstom Technology Ltd Brûleur à prémélange
CN103776060A (zh) * 2012-10-25 2014-05-07 阿尔斯通技术有限公司 再热喷燃器布置
CN104913340A (zh) * 2014-03-12 2015-09-16 通用电气公司 用于控制燃烧系统中的燃烧动力的系统及方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5307634A (en) 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
US5671597A (en) * 1994-12-22 1997-09-30 United Technologies Corporation Low nox fuel nozzle assembly
DE19545310B4 (de) * 1995-12-05 2008-06-26 Alstom Vormischbrenner

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5307634A (en) 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1340942A2 (fr) * 1997-12-15 2003-09-03 United Technologies Corporation Injecteur de carburant équipé d'un corps perturbateur et procédé de prémélange de carburant et d'air
EP0924463A3 (fr) * 1997-12-15 1999-12-08 United Technologies Corporation Injecteur de combustible avec un corps perturbateur et procédé pour prémélanger du combustible et de l'air
US6176087B1 (en) 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
EP1340942A3 (fr) * 1997-12-15 2003-09-10 United Technologies Corporation Injecteur de carburant équipé d'un corps perturbateur et procédé de prémélange de carburant et d'air
US7410288B1 (en) 1998-12-24 2008-08-12 Luminis Pty. Ltd. Fluid mixing device
WO2000039504A1 (fr) * 1998-12-24 2000-07-06 Luminis Pty. Ltd. Dispositif pour le melange de fluides
EP1293725A1 (fr) * 2001-09-14 2003-03-19 United Technologies Corporation Injecteur de carburant
US6625971B2 (en) 2001-09-14 2003-09-30 United Technologies Corporation Fuel nozzle producing skewed spray pattern
GB2432655A (en) * 2005-11-26 2007-05-30 Siemens Ag Combustion apparatus
CN101285591B (zh) * 2008-04-22 2010-06-09 北京航空航天大学 一种一体化燃油喷射径向旋流器预混预蒸发低污染燃烧室
EP2703721A1 (fr) * 2012-08-31 2014-03-05 Alstom Technology Ltd Brûleur à prémélange
US9400105B2 (en) 2012-08-31 2016-07-26 General Electric Technology Gmbh Premix burner
CN103776060A (zh) * 2012-10-25 2014-05-07 阿尔斯通技术有限公司 再热喷燃器布置
US9976744B2 (en) 2012-10-25 2018-05-22 Ansaldo Energia Switzerland AG Reheat burner arrangement having an increasing flow path cross-section
CN104913340A (zh) * 2014-03-12 2015-09-16 通用电气公司 用于控制燃烧系统中的燃烧动力的系统及方法
CN104913340B (zh) * 2014-03-12 2019-11-19 通用电气公司 用于控制燃烧系统中的燃烧动力的系统及方法

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