WO2018038792A1 - Ensemble mélangeur carburant-air destiné à être utilisé dans une chambre de combustion d'un moteur à turbine - Google Patents

Ensemble mélangeur carburant-air destiné à être utilisé dans une chambre de combustion d'un moteur à turbine Download PDF

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Publication number
WO2018038792A1
WO2018038792A1 PCT/US2017/037374 US2017037374W WO2018038792A1 WO 2018038792 A1 WO2018038792 A1 WO 2018038792A1 US 2017037374 W US2017037374 W US 2017037374W WO 2018038792 A1 WO2018038792 A1 WO 2018038792A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
assembly
mixer
centerline
relative
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
PCT/US2017/037374
Other languages
English (en)
Inventor
Allen Michael Danis
Jagannath Ramchandra NANDURI
Nicholas Ryan OVERMAN
Arthur Wesley Johnson
Sibtosh PAL
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 CN201780051603.6A priority Critical patent/CN109563995B/zh
Publication of WO2018038792A1 publication Critical patent/WO2018038792A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F23R3/286—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
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • the present disclosure relates generally to turbine engines and, more specifically, to a fuel-air mixer assembly having axi-asymmetric characteristics for reducing combustion dynamics.
  • a combustion section of a gas turbine generally includes a plurality of combustors that are arranged in an annular array about an outer casing, such as a compressor discharge casing. Pressurized air flows from a compressor towards the compressor discharge casing, and is then channeled to each combustor. Fuel from a fuel nozzle is mixed with the pressurized air in each combustor to form a combustible mixture within a primary combustion zone of the combustor. The combustible mixture is burned to produce hot combustion gases having a high pressure and high velocity.
  • high combustion dynamics are formed when the combustible mixture is burned. High combustion dynamics adversely affect the operability and service life of the combustors. Moreover, high combustion dynamics can result in damage to components of the combustors, thereby causing service outages and increasing repair costs.
  • a fuel-air mixer assembly for use in a combustor.
  • the fuel-air mixer assembly includes a mixer portion, and a flare cup portion coupled to the mixer portion.
  • the flare cup portion includes a side wall that including an inlet opening and a discharge opening defined therein. The side wall is oriented such that the discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.
  • a combustor for use in a turbine engine.
  • the combustor includes a fuel nozzle assembly, and a fuel-air mixer assembly including a mixer portion configured to receive fuel from the fuel nozzle assembly.
  • the fuel-air mixer assembly also includes a flare cup portion coupled to the mixer portion.
  • the flare cup portion includes a side wall that including an inlet opening and a discharge opening defined therein. The side wall is oriented such that the discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.
  • a turbine engine in yet another aspect, includes a combustor including a fuel nozzle assembly and a fuel-air mixer assembly coupled to the fuel nozzle assembly.
  • the fuel-air mixer assembly includes a mixer portion configured to receive fuel from the fuel nozzle assembly, and a flare cup portion coupled to the mixer portion.
  • the flare cup portion includes a side wall that including an inlet opening and a discharge opening defined therein. The side wall is oriented such that the discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.
  • FIG. 1 is a schematic diagram of an exemplary turbine engine
  • FIG. 2 is a cross-sectional view of a portion of an exemplary combustor that may be used with the turbine engine shown in FIG. 1;
  • FIG. 3 is a cross-sectional view of an exemplary fuel-air mixer assembly that may be used in the combustor shown in FIG. 2;
  • FIG. 4 is an axial view of the fuel-air mixer assembly shown in FIG. 3;
  • FIG. 5 is a cross-sectional view of an alternative fuel -air mixer assembly that may be used in the combustor shown in FIG. 2;
  • FIG. 6 is an axial view of the fuel-air mixer assembly shown in FIG. 5;
  • FIG. 7 is an axial view of an exemplary swirl er vane assembly that may be used in the fuel-air mixer assemblies shown in FIGS. 3 and 5.
  • Approximating language may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value.
  • range limitations may be combined and/or interchanged. Such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise.
  • the terms “axial” and “axially” refer to directions and orientations that extend substantially parallel to a centerline of the turbine engine or the combustor. Moreover, the terms “radial” and “radially” refer to directions and orientations that extend substantially perpendicular to the centerline of the turbine engine or the fuel-air mixer assembly. In addition, as used herein, the terms “circumferential” and “circumferentially” refer to directions and orientations that extend arcuately about the centerline of the turbine engine or the fuel-air mixer assembly.
  • Embodiments of the present disclosure relate to a fuel-air mixer assembly having axi- asymmetric characteristics for reducing combustion dynamics. More specifically, the fuel-air mixer assembly includes one or more design features of a mixer portion, a flare cup portion, or a ferrule portion of the assembly that are implemented, either alone or in combination, to reduce combustion dynamics by disrupting symmetries within the assembly. For example, at least one of the orientation, shape, and/or design of swirl er vanes within the mixer portion, inlets and outlets of the flare cup portion, and purge holes within the ferrule portion are formed axi- asymmetrically relative to a centerline of a combustor to facilitate disrupting a swirling flow of fuel and air discharged from the fuel-air mixer assembly.
  • FIG. 1 is a schematic diagram of an exemplary turbine engine 10 including a fan assembly 12, a low-pressure or booster compressor assembly 14, a high-pressure compressor assembly 16, and a combustor assembly 18.
  • Fan assembly 12, booster compressor assembly 14, high-pressure compressor assembly 16, and combustor assembly 18 are coupled in flow communication.
  • Turbine engine 10 also includes a high-pressure turbine assembly 20 coupled in flow communication with combustor assembly 18 and a low-pressure turbine assembly 22.
  • Fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26.
  • Low-pressure turbine assembly 22 is coupled to fan assembly 12 and booster compressor assembly 14 through a first drive shaft 28, and high-pressure turbine assembly 20 is coupled to high-pressure compressor assembly 16 through a second drive shaft 30.
  • Turbine engine 10 has an intake 32 and an exhaust 34.
  • Turbine engine 10 further includes a centerline 36 about which fan assembly 12, booster compressor assembly 14, high-pressure compressor assembly 16, and turbine assemblies 20 and 22 rotate.
  • air entering turbine engine 10 through intake 32 is channeled through fan assembly 12 towards booster compressor assembly 14.
  • Compressed air is discharged from booster compressor assembly 14 towards high-pressure compressor assembly 16.
  • Highly compressed air is channeled from high-pressure compressor assembly 16 towards combustor assembly 18, mixed with fuel, and the mixture is combusted within combustor assembly 18.
  • High temperature combustion gas generated by combustor assembly 18 is channeled towards turbine assemblies 20 and 22. Combustion gas is subsequently discharged from turbine engine 10 via exhaust 34.
  • FIG. 2 is a cross-sectional view of a portion of an exemplary combustor 38 that may be used with turbine engine 10.
  • Combustor 38 defines a combustion chamber 40 in which the highly compressed air is mixed with fuel and combusted.
  • Combustor 38 includes an outer liner 42 and an inner liner 44.
  • Outer liner 42 defines an outer boundary of the combustion chamber 40
  • inner liner 44 defines an inner boundary of combustion chamber 40.
  • An annular dome 46 is mounted upstream from outer liner 42 and inner liner 44 defines an upstream end of combustion chamber 40.
  • One or more fuel injection systems 48 are positioned on annular dome 46.
  • each fuel injection system 48 includes a fuel nozzle assembly 50 and a fuel-air mixer assembly 52 coupled to fuel nozzle assembly 50.
  • Fuel-air mixer assembly 52 receives fuel from fuel nozzle assembly 50, receives air from high-pressure compressor assembly 16 (shown in FIG. 1) via a diffuser 54, and discharges a fuel-air mixture 56 into combustion chamber 40.
  • FIG. 3 is a cross-sectional view of fuel-air mixer assembly 52 that may be used in combustor 38 (shown in FIG. 2)
  • FIG. 4 is an axial view of fuel-air mixer assembly 52.
  • fuel-air mixer assembly 52 includes a mixer portion 58 and a flare cup portion 60 coupled to mixer portion 58.
  • Mixer portion 58 includes a first radial flow passage 62 and a second radial flow passage 64 each having a swirler vane assembly 66 positioned therein, as will be described in more detail below.
  • Flare cup portion 60 includes a side wall 68 that has an inlet opening 70 and a discharge opening 72 defined therein. Side wall 68 is oriented such that discharge opening 72 is axi-asymmetrically shaped relative to a centerline 74 of fuel-air mixer assembly 52.
  • fuel-air mixture 56 (shown in FIG. 2) is discharged from fuel-air mixer assembly 52 during operation of combustor 38. More specifically, fuel-air mixture 56 generally swirls circumferentially about centerline 74 before being discharged from fuel-air mixer assembly 52.
  • shaping discharge opening 72 axi-asymmetrically relative to centerline 74 facilitates disrupting a symmetrical flow field of fuel-air mixture 56 before being discharged from fuel-air mixer assembly 52.
  • discharge opening 72 is defined by a major axis 76 and a minor axis 78 oriented perpendicularly relative to each other.
  • Discharge opening 72 is shaped axi-asymmetrically in that major axis 76 is longer than minor axis 78.
  • fuel-air mixer assembly 52 is oriented within combustor 38 (shown in FIG. 2) such that major axis 76 is oriented tangentially relative to a circumference of turbine engine 10 (shown in FIG. 1). As such, flame propagation is enhanced and impingement of fuel-air mixture 56 and heat against outer liner and inner liner 44 (shown in FIG. 2) is reduced.
  • side wall 68 of flare cup portion 60 is divergently oriented relative to centerline 74 of fuel-air mixer assembly 52 at opposing ends of major axis 76 and minor axis 78.
  • side wall 68 is angled relative to centerline 74 at the opposing ends of major axis 76 and minor axis 78 by any angle that enables flare cup portion 60 to function as described herein.
  • side wall 68 at opposing ends of major axis 76 is oriented at an angle ⁇ equal to or less than about 60 degrees relative to centerline 74.
  • side wall 68 at opposing ends of minor axis 78 is oriented at an angle less than angle ⁇ such that a planar opening is formed at discharge opening 72.
  • mixer portion 58 includes a discharge end 80 coupled to flare cup portion 60 at inlet opening 70.
  • fuel and air are mixed within mixer portion 58 and discharged from mixer portion 58 through an outlet 82 defined at discharge end 80.
  • air enters mixer portion 58 radially and is discharged from mixer portion 58 through an annular opening 84 defined at discharge end 80.
  • Outlet 82 is defined by a first side wall 86 and annular opening 84 is defined by a second side wall 88.
  • first side wall 86 and second side wall 88 are both shaped axi-symmetrically relative to centerline 74.
  • side wall 68 of flare cup portion 60 at inlet opening 70 is shaped axi-symmetrically relative to centerline 74.
  • flare cup portion 60 is retrofittable onto an existing cylindrical discharge end 80 of mixer portion 58.
  • Fuel-air mixer assembly 52 also includes a ferrule portion 90 coupled to mixer portion 58.
  • Ferrule portion 90 includes a fuel inlet 92 and a plurality of purge holes defined therein.
  • the plurality of purge holes direct axial airflow into mixer portion 58.
  • the plurality of purge holes include first purge holes 94 and second purge holes 96 defined in ferrule portion 90 and arranged circumferentially relative to centerline 74.
  • First purge holes 94 are sized smaller than second purge holes 96. More specifically, first purge holes 94 and second purge holes 96 are arranged axi-asymmetrically based on the size of first purge holes 94 and second purge holes 96 relative to centerline 74.
  • sets of first purge holes 94 and sets of second purge holes 96 are alternatingly arranged relative to centerline 74.
  • first purge holes 94 and second purge holes 96 are individually alternatingly arranged relative to centerline 74.
  • flare cup portion 60 includes a transition section 93 defined between a cylindrical section 95 and a flared section 97 of flare cup portion 60.
  • Transition section 93 has any shape that enables fuel-air mixer assembly 52 to function as described herein.
  • transition section 93 may be defined by a sharp corner or have a radius of less than or equal to about 0.15 inches.
  • flared section 97 has either a flat surface or a curved surface. When curved, flared section 97 curves outwardly relative to centerline 74 from transition section 93 by an angular increase of less than or equal to about 50 degrees.
  • FIG. 5 is a cross-sectional view of an alternative fuel -air mixer assembly 98 that may be used in combustor 38 (shown in FIG. 2)
  • FIG. 6 is an axial view of fuel-air mixer assembly 98.
  • mixer portion 58 includes a discharge end 100 coupled to flare cup portion 60 at an inlet opening 102.
  • fuel and air are mixed within mixer portion 58 and discharged from mixer portion 58 through an outlet 104 defined at discharge end 100.
  • air enters mixer portion 58 radially and is discharged from mixer portion 58 through an annular opening 106 defined at discharge end 100.
  • Outlet 104 is defined by first side wall 86 and annular opening 106 is defined by second side wall 88.
  • first side wall 86 and second side wall 88 are both shaped axi-asymmetrically relative to centerline 74.
  • side wall 68 of flare cup portion 60 at inlet opening 102 is shaped axi-asymmetrically relative to centerline 74 to facilitate coupling between mixer portion 58 and flare cup portion 60.
  • Axi-asymmetrically shaping outlet 104 and annular opening 106 further facilitates disrupting a symmetrical flow field of fuel-air mixture 56 (shown in FIG. 2) before being discharged from fuel-air mixer assembly 52.
  • FIG. 7 is an axial view of an exemplary swirler vane assembly 66 that may be used in mixer portion 58 of fuel-air mixer assemblies 52 and 98 (shown in FIGS. 3 and 5).
  • swirler vane assembly 66 includes first swirler vanes 108 and second swirler vanes 110 arranged circumferentially within mixer portion 58 relative to centerline 74.
  • First swirler vanes 108 direct airflow into mixer portion 58 in a different direction than second swirler vanes 110. More specifically, first swirler vanes 108 and second swirler vanes 110 are angled differently relative to a radial axis 112 of fuel-air mixer assembly 52.
  • an angle a defined between radial axis 112 and first swirler vanes 108 is less than an angle ⁇ defined between radial axis 112 and second swirler vanes 110.
  • sets of first swirler vanes 108 and sets of second swirler vanes 110 are alternatingly arranged relative to centerline 74 (shown in FIG. 3).
  • first swirler vanes 108 and second swirler vanes 110 are individually alternatingly arranged relative to centerline 74.
  • An exemplary technical effect of the systems and methods described herein includes at least one of: (a) improving combustion dynamics in a combustor of a turbine engine; (b) forming a fuel-air mixer assembly with axi-asymmetric design features; and (c) improving the service life and operability of the turbine engine.
  • Exemplary embodiments of a turbine engine and related components are described above in detail.
  • the system is not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein.
  • the configuration of components described herein may also be used in combination with other processes, and is not limited to practice with only turbofan assemblies and related methods as described herein.
  • the exemplary embodiment can be implemented and utilized in connection with many applications where reducing combustion dynamics is desired.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un ensemble mélangeur carburant-air (52) qui comprend une partie mélangeur et une partie coupelle évasée (60) couplée à la partie mélangeur. La partie coupelle évasée comprend une paroi latérale (68) dans laquelle une ouverture d'admission et une ouverture d'évacuation (72) sont définies. La paroi latérale est orientée de sorte que l'ouverture d'évacuation soit de forme axi-asymétrique par rapport à une ligne centrale (74) de l'ensemble mélangeur carburant-air.
PCT/US2017/037374 2016-08-23 2017-06-14 Ensemble mélangeur carburant-air destiné à être utilisé dans une chambre de combustion d'un moteur à turbine Ceased WO2018038792A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201780051603.6A CN109563995B (zh) 2016-08-23 2017-06-14 用于涡轮发动机的燃烧器中的燃料-空气混合器组件

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US15/244,797 US20180058696A1 (en) 2016-08-23 2016-08-23 Fuel-air mixer assembly for use in a combustor of a turbine engine
US15/244,797 2016-08-23

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WO2018038792A1 true WO2018038792A1 (fr) 2018-03-01

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CN (1) CN109563995B (fr)
WO (1) WO2018038792A1 (fr)

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GB201802251D0 (en) * 2018-02-12 2018-03-28 Rolls Royce Plc An air swirler arrangement for a fuel injector of a combustion chamber
JP7446077B2 (ja) * 2019-10-04 2024-03-08 三菱重工業株式会社 ガスタービン用燃焼器、ガスタービン及び油燃料の燃焼方法
CN116147016B (zh) * 2021-11-22 2025-09-19 通用电气公司 用于燃料-空气混合器组件的套圈
US11747018B2 (en) * 2022-01-05 2023-09-05 General Electric Company Combustor with dilution openings
US11994295B2 (en) * 2022-02-18 2024-05-28 General Electric Company Multi pressure drop swirler ferrule plate
CN117366627B (zh) * 2022-07-01 2026-03-24 中国航发商用航空发动机有限责任公司 涡流器、混合器、燃烧室及燃油雾化方法
FR3142533A1 (fr) * 2022-11-28 2024-05-31 Safran Aircraft Engines Chambre de combustion pour turbomachine

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Also Published As

Publication number Publication date
CN109563995B (zh) 2021-07-09
US20180058696A1 (en) 2018-03-01
CN109563995A (zh) 2019-04-02

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