WO2015080131A1 - ノズル、燃焼器、及びガスタービン - Google Patents

ノズル、燃焼器、及びガスタービン Download PDF

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Publication number
WO2015080131A1
WO2015080131A1 PCT/JP2014/081186 JP2014081186W WO2015080131A1 WO 2015080131 A1 WO2015080131 A1 WO 2015080131A1 JP 2014081186 W JP2014081186 W JP 2014081186W WO 2015080131 A1 WO2015080131 A1 WO 2015080131A1
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WO
WIPO (PCT)
Prior art keywords
nozzle
water injection
circumferential direction
fuel
injection ports
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/JP2014/081186
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
田村　一生
赤松　真児
斉藤　圭司郎
宏太郎 宮内
朋 川上
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.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
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 Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Priority to US15/031,051 priority Critical patent/US10570820B2/en
Priority to KR1020167011901A priority patent/KR101752114B1/ko
Priority to CN201480060669.8A priority patent/CN105705866B/zh
Priority to EP14865587.1A priority patent/EP3076077B1/en
Publication of WO2015080131A1 publication Critical patent/WO2015080131A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F23L7/002—Supplying water
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/35—Arrangement of components rotated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/37—Arrangement of components circumferential
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

Definitions

  • the present invention relates to a nozzle, a combustor, and a gas turbine.
  • This application claims priority based on Japanese Patent Application No. 2013-247076 filed in Japan on November 29, 2013, the contents of which are incorporated herein by reference.
  • a combustor for a gas turbine there is a combustor including a pilot fuel nozzle and a plurality of main fuel nozzles provided around the pilot fuel nozzle.
  • the main premixed flame is stabilized by a diffusion flame formed by a pilot fuel nozzle.
  • Patent Document 1 discloses a configuration in which a region in which a fuel injection hole is not provided is provided in a part of the pilot fuel nozzle in the circumferential direction, and fuel to be ejected from the pilot fuel nozzle is unevenly distributed in the circumferential direction. Yes. Further, in Patent Document 1, the fuel to be ejected from the plurality of main fuel nozzles to the outer peripheral side of the pilot fuel nozzle is made uneven in the circumferential direction by varying the amount of fuel ejection among the plurality of main fuel nozzles. A distributed configuration is disclosed. With these configurations, the length of the flame formed by burning the fuel is varied in the circumferential direction, and the heat generation rate is dispersed to suppress combustion vibration.
  • Patent Document 2 discloses a configuration in which, in each of a plurality of main fuel nozzles, fuel injection holes are provided at a plurality of different positions in the axial direction.
  • Patent Document 2 discloses a configuration in which, in each of a plurality of main fuel nozzles, fuel injection holes are provided at a plurality of positions different in the axial direction, and the fuel injection angles from the fuel injection holes are made different. .
  • combustion vibration is suppressed by varying the time during which the fuel (premixed gas) ejected from the main fuel nozzle reaches the flame between the plurality of fuel ejection holes whose positions are different from each other in the axial direction.
  • the present invention provides a nozzle, a combustor, and a gas turbine that can effectively suppress combustion vibration even in a combustor that injects water into a flame.
  • the nozzle is formed with a fuel injection port for injecting fuel at the center of the tip, and a plurality of water is spaced circumferentially around the fuel injection port at the tip.
  • the injection ports are formed, and the water injection ports are formed unevenly in the circumferential direction.
  • the water injected from the water injection port is non-uniformly injected in the circumferential direction with respect to the flame generated by the fuel injected from the fuel injection port.
  • the axial position of the flame is not uniform in the circumferential direction.
  • the combustion vibration can be suppressed by varying the axial position of the flame itself or the flame of the fuel ignited by the flame in the circumferential direction to disperse the heat generation rate.
  • a part of the plurality of water injection ports has a plurality of inclination angles in the radial direction of the nozzle with respect to a central axis of the nozzle. It may be formed so as to be different from the remaining portion of the water injection port. Thereby, the injection angle of the water injected from the water injection port is different in the radial direction of the nozzle in a partial region in the circumferential direction and the remaining region. Thereby, water can be jetted unevenly in the circumferential direction.
  • a part of the plurality of water ejection ports is inclined in the circumferential direction of the nozzle with respect to a central axis of the nozzle.
  • it may be formed so as to be different from the remaining portions of the plurality of water injection ports.
  • the injection angle of the water injected from the water injection port is different in the circumferential direction of the nozzle, that is, the tangential direction at the position of the water injection port, in a part of the region in the circumferential direction and the remaining part of the region. .
  • water can be jetted unevenly in the circumferential direction.
  • a part of the plurality of water injection ports has a plurality of the water diameters. You may form so that it may differ from the remainder of a jet nozzle. Thereby, the injection amount of the water injected from the water injection port differs between a partial region in the circumferential direction and the remaining region. Thereby, water can be jetted unevenly in the circumferential direction.
  • a part of the plurality of water injection ports has a position in the radial direction of the nozzle, It may be formed so as to be different from the remaining portions of the plurality of water injection ports.
  • the water injected from the water injection port reaches the flame generated by the fuel injected from the fuel injection port in the central part in a part of the circumferential direction and the remaining part of the region. The distance to is different. Thereby, water can be jetted unevenly in the circumferential direction.
  • a part of the plurality of water injection ports has an installation interval in the circumferential direction of the nozzle. Further, it may be formed different from the remaining portions of the plurality of water injection ports. Thereby, the injection quantity (injection density) of the water injected from the water injection port differs between a partial area in the circumferential direction and the remaining area. Thereby, water can be jetted unevenly in the circumferential direction.
  • the combustor includes a main nozzle that injects fuel, and a pilot nozzle that generates a flame for igniting the fuel injected from the main nozzle, the pilot nozzle
  • the nozzle of any one of the first to sixth aspects may be used.
  • generated with a pilot nozzle can be made uneven in the circumferential direction.
  • the flame by the fuel injected from the main nozzle also becomes uneven in the circumferential direction.
  • the pilot nozzle is disposed in a central portion, and a plurality of the main nozzles are provided in the circumferential direction on the outer peripheral side of the pilot nozzle. Also good.
  • a gas turbine may include the combustor according to the seventh or eighth aspect, and a turbine body driven by the combustion gas generated by the combustor. According to such a gas turbine, combustion vibration due to a flame in the combustor can be suppressed.
  • combustion vibration can be effectively suppressed even in a combustor that injects water into a flame.
  • It is side sectional drawing which shows schematic structure of a combustor.
  • It is a sectional side view which shows the structure of the principal part of a combustor.
  • It is a front view which shows the front end surface of the combustor in 1st embodiment.
  • It is a sectional side view which shows the fuel injection port and water injection port which were formed in the front end surface of a combustor.
  • It is a front view which shows the front end surface of the combustor in 2nd embodiment.
  • the gas turbine 1 of the present embodiment combusts by mixing a fuel with a compressor 2 that takes in a large amount of air and compresses it, and compressed air A compressed by the compressor 2. And a turbine body 4 that converts thermal energy of the combustion gas G introduced from the combustor 3 into rotational energy.
  • the compressor 2 and the turbine body 4 are each provided with a rotor 5 connected so as to rotate integrally and a stator 6 surrounding the outer periphery of the rotor 5.
  • the rotor 5 has a rotating shaft 7 and a plurality of annular blade groups 8 fixed at intervals in the axial direction.
  • Each annular moving blade group 8 is configured to have a plurality of moving blades fixed on the outer periphery of the rotating shaft 7 at intervals in the circumferential direction.
  • the stator 6 includes a casing 9 and a plurality of annular stator blade groups 10 that are fixed in the casing 9 at intervals in the axial direction.
  • the annular stationary blade group 10 has a plurality of stationary blades fixed to the inner surface of each casing 9 at intervals in the circumferential direction.
  • the annular stator blade groups 10 are alternately arranged with the plurality of annular rotor blade groups 8 in the axial direction.
  • the combustor 3 of the present embodiment includes a cylindrical inner cylinder 31 and an outer cylinder 32 provided concentrically on the outer peripheral side of one end side in the central axis direction of the inner cylinder 31. ing. One end side 32 a of the outer cylinder 32 is closed, and the other end side 32 b is opened on the outer peripheral side of the inner cylinder 31.
  • the compressed air A that has flowed into the combustor 3 from between the inner peripheral surface of the other end 32b of the outer cylinder 32 and the outer peripheral surface of the inner cylinder 31 turns 180 ° at one end 32a of the outer cylinder 32, 31 is supplied to the inside.
  • a plurality of pilot burners 33 provided at the center of the inner cylinder 31 and a plurality of outer peripheral sides of the pilot burner 33 are provided in the inner cylinder 31 at intervals in the circumferential direction.
  • the main burner 34 is provided.
  • the pilot burner 33 includes a pilot nozzle 35 and a pilot cone 36.
  • the pilot nozzle 35 is provided along the central axis O of the inner cylinder 31 from one end side 32 a of the outer cylinder 32.
  • the pilot nozzle 35 injects the fuel supplied from the one end side 32a of the outer cylinder 32 via a fuel supply path (not shown) from the front end portion 35a, and generates a flame by igniting the fuel.
  • the pilot cone 36 has a cylindrical shape and is provided on the outer peripheral side of the tip 35 a of the pilot nozzle 35.
  • the pilot cone 36 has a tapered cone portion 36c whose inner diameter gradually increases from the vicinity of the tip portion 35a of the pilot nozzle 35 in the flame generation direction, and regulates the diffusion range and direction of the flame, thereby improving the flame holding property. It is increasing.
  • the main burner 34 includes a main nozzle 37 and a main swirler 38.
  • a cylindrical outer peripheral cone 39 is provided on the outer peripheral side of the pilot cone 36.
  • a plurality of main nozzles 37 are provided in the region between the outer peripheral surface of the outer peripheral cone 39 and the inner peripheral surface of the inner cylinder 31 with an interval in the circumferential direction.
  • Each main nozzle 37 is provided in parallel to the central axis O of the inner cylinder 31 from one end side 32 a of the outer cylinder 32.
  • the main swirler 38 is provided at the tip of each main nozzle 37.
  • fuel main fuel
  • fuel On the upstream side of the air flow of the main swirler 38, fuel (main fuel) is jetted from a fuel nozzle nozzle (not shown) to the outer peripheral surface side of the main nozzle 37.
  • the fuel is mixed with the compressed air A in the inner cylinder 31 in the main burner 34 by the action of the main swirler 38 to generate a premixed gas.
  • the pilot nozzle 35 of the present embodiment injects water toward the flame in order to lower the flame temperature and reduce Nox.
  • the configuration of the pilot nozzle 35 will be described in detail.
  • the pilot nozzle 35 has a fuel injection port 41 for injecting fuel at the center of the tip surface (tip) 35 s.
  • Fuel is supplied to the fuel injection port 41 from a fuel supply source (not shown) through a fuel flow path formed in the pilot nozzle 35.
  • a plurality of water injection ports 42 are formed around the fuel injection ports 41 on the front end surface 35 s of the pilot nozzle 35 at intervals in the circumferential direction. Water is supplied to the water injection port 42 from a water supply source (not shown) through a water channel formed in the pilot nozzle 35.
  • Each water injection port 42 is formed to be inclined with respect to the center axis O of the pilot nozzle 35 toward the inner peripheral side in the pilot nozzle radial direction and in the circumferential direction. Thereby, the water injected from each water injection port 42 has an envelope with respect to the outer edge portion of the flame F1 by the fuel injected from the fuel injection ports 41 located on the inner peripheral side of the plurality of water injection ports 42. It is sprayed so that it may overlap.
  • the plurality of water injection ports 42 are formed unevenly in the circumferential direction.
  • the water injection ports 42 ⁇ / b> A in a partial region in the circumferential direction are inclined to the inner peripheral side in the radial direction of the pilot nozzle 35 with respect to the central axis O of the pilot nozzle 35.
  • it is formed so as to be different from the inclination angle ⁇ 2 of the water injection port 42B in the remaining other region.
  • the inclination angle ⁇ 1 of some of the water injection ports 42A is formed to be smaller than the inclination angle ⁇ 2 of the other remaining water injection ports 42B (remaining portions of the water injection ports).
  • the water injected toward the inner peripheral side of the pilot nozzle 35 from each water injection port 42 is more water-injecting ports 42A in a partial region in the circumferential direction than the other water-injecting ports 42B. Injected toward the outer periphery. Therefore, the water injected from the plurality of water injection ports 42 of the pilot nozzle 35 is unevenly injected in the circumferential direction with respect to the flame F ⁇ b> 1 generated by the fuel injected from the central fuel injection port 41.
  • the smaller the inclination angle of the water injection port 42 toward the radially inner peripheral side the more water is injected from the water injection port 42 at a position farther downstream in the water injection direction from the water injection port 42. Reach the outer edge.
  • the axial direction position of the flame F1 becomes uneven in the circumferential direction.
  • the position where the fuel ejected from the main burner 34 ignites that is, the generation position of the main flame
  • the generation position of the main flame differs in the direction along the central axis O in the circumferential direction due to the flame F1 having a different axial position in the circumferential direction.
  • the generation position of the main flame by the fuel ejected from the main burner 34 shifts downstream in the flame generation direction along the central axis O direction.
  • generated in the combustor 3 differs in the position in the central-axis O direction in the circumferential direction. Then, as shown in FIG. 6, the dispersion of the heat generation rate in the combustor 3 is widened along the central axis O direction. Therefore, it is possible to suppress the exciting force due to the flame F1 or one vibration mode due to the main flame. As a result, combustion vibration can be effectively suppressed.
  • the water injection ports 42 are made uneven in the circumferential direction by changing the inclination angle of the water injection ports 42 in the radial direction of the pilot nozzle 35.
  • the present invention is not limited to this. is not.
  • a plurality of embodiments in which the plurality of water injection ports 42 are formed unevenly in the circumferential direction will be described.
  • the overall configuration of the gas turbine 1 and the combustor 3 is common to the first embodiment. Therefore, in the following description, the same components as those in the first embodiment are denoted by the same reference numerals in the drawing, the description thereof is omitted, and the description will be focused on the configuration of the water injection port 42 in the pilot nozzle 35. .
  • the pilot nozzle 35 of the combustor 3 As shown in FIG. 7, in the pilot nozzle 35 of the combustor 3 according to the present embodiment, one of the plurality of water injection ports 42 formed around the fuel injection port 41 at intervals in the circumferential direction.
  • the inclination angle of the water injection port 42C in the area of the portion is formed to be different from the inclination angle of the water injection port 42D. That is, the water injection port in which the inclination angle of the water injection port 42C in the circumferential direction of the pilot nozzle 35 with respect to the central axis O of the pilot nozzle 35 (the tangential direction at the position where the water injection port 42C is provided) is in the remaining remaining region. It is formed to be different from the inclination angle of 42D. For example, the inclination angle of some of the water injection ports 42C is formed to be larger than the inclination angle of the remaining other water injection ports 42D.
  • the water injected from the water injection port 42 is more upstream in the generation direction of the flame F1 in the water injection port 42C in a partial region in the circumferential direction than in the other water injection ports 42D. Be injected.
  • the water injected from the water injection port 42 toward the outer peripheral side of the flame F1 generated by the fuel injected from the central fuel injection port 41 is in the circumferential direction. It is sprayed unevenly. Then, the axial direction position of the flame F1 is not uniform in the circumferential direction. Thereby, the flame F1 propagates to the fuel ejected from the main burner 34, and the position where the fuel ignites differs in the direction along the central axis O. Then, as shown in FIG. 6, in the combustor 3, the heat generation rate due to the main flame is dispersed along the central axis O direction in the circumferential direction. As a result, it is possible to suppress the excitation force due to the flame F1 or one vibration mode due to the main flame. As a result, combustion vibration can be effectively suppressed.
  • the opening diameter D1 of the water injection port 42E in the part area is formed to be different from the opening diameter D2 of the water injection port 42F in the remaining other area.
  • the opening diameter D1 of some of the water injection ports 42E is formed to be larger than the opening diameter D2 of the remaining other water injection ports 42F.
  • the amount of water jetted from the water jet port 42 is larger at the water jet port 42E in a partial region in the circumferential direction than at the other water jet ports 42F.
  • the water injected from the water injection port 42 toward the outer peripheral side of the flame F1 generated by the fuel injected from the central fuel injection port 41 is in the circumferential direction. It is sprayed unevenly. Then, the axial direction position of the flame F1 is not uniform in the circumferential direction. Thereby, the flame F1 propagates to the fuel ejected from the main burner 34, and the position where the fuel ignites differs in the direction along the central axis O. Then, as shown in FIG. 6, in the combustor 3, the heat generation rate due to the main flame is dispersed along the central axis O direction in the circumferential direction. As a result, it is possible to suppress the excitation force due to the flame F1 or one vibration mode due to the main flame. As a result, combustion vibration can be effectively suppressed.
  • the opening of the water injection port 42G in the area of the portion is formed to be different from the opening of the water injection port 42H.
  • the opening of the water injection port 42G is formed such that the position of the pilot nozzle 35 in the radial direction is different from the opening of the water injection port 42H in the remaining other region.
  • the openings of some of the water injection ports 42G are arranged on the radially outer peripheral side of the pilot nozzle 35 with respect to the remaining openings of the other water injection ports 42H.
  • the water jetted from the water jets 42 in the water jets 42G in a partial region in the circumferential direction is more downstream of the flame F1 in the generation direction of the flame F1 than the other water jets 42H. Reach the outer edge.
  • the water injected from the water injection port 42 toward the outer peripheral side of the flame F1 generated by the fuel injected from the central fuel injection port 41 is in the circumferential direction. It is sprayed unevenly. Then, the axial direction position of the flame F1 is not uniform in the circumferential direction. Thereby, the flame F1 propagates to the fuel ejected from the main burner 34, and the position where the fuel ignites differs in the direction along the central axis O. Then, as shown in FIG. 6, in the combustor 3, the heat generation rate due to the main flame is dispersed along the central axis O direction in the circumferential direction. As a result, it is possible to suppress the excitation force due to the flame F1 or one vibration mode due to the main flame. As a result, combustion vibration can be effectively suppressed.
  • the installation interval of the water injection ports 42J in the area of the portion is formed to be different from the installation interval of the water injection ports 42K. That is, the installation interval of the water injection ports 42J in the circumferential direction of the pilot nozzle 35 is formed so as to be different from the installation interval of the water injection ports 42K in other remaining areas.
  • the installation interval P1 in the circumferential direction of the water injection port 42J in a part of the region is formed to be smaller than the installation interval P2 of the water injection port 42K in the remaining other region.
  • the amount of water (injection density) of the water injected from the water injection port 42 is larger at the water injection port 42J in the partial region in the circumferential direction than at the other water injection ports 42K.
  • the water injected from the water injection port 42 toward the outer peripheral side of the flame F1 generated by the fuel injected from the central fuel injection port 41 is in the circumferential direction. It is sprayed unevenly. Then, the axial direction position of the flame F1 is not uniform in the circumferential direction. Thereby, the flame F1 propagates to the fuel ejected from the main burner 34, and the position where the fuel ignites differs in the direction along the central axis O. Then, as shown in FIG. 6, in the combustor 3, the heat generation rate due to the main flame is dispersed along the central axis O direction in the circumferential direction. As a result, it is possible to suppress the excitation force due to the flame F1 or one vibration mode due to the main flame. As a result, combustion vibration can be effectively suppressed.
  • the present invention is not limited to the above-described embodiments described with reference to the drawings, and various modifications are conceivable within the technical scope thereof.
  • the water injection ports 42A, 42C, 42E, 42G, and 42J in a partial region in the circumferential direction, and the circumferential direction
  • the water injection ports 42B, 42D, 42F, 42H, and 42K in the remaining regions are not limited to this.
  • the water injection ports 42 may be formed unevenly by dividing into more sections.
  • the inclination angle, opening diameter, radial position, and installation interval of the plurality of water injection ports 42 are formed in two stages, with a partial area in the circumferential direction and the remaining other areas, but in three or more stages. It may be formed.
  • the first to fifth embodiments can be combined as appropriate.
  • the water injection ports 42 are formed in the pilot nozzle 35 together with the fuel injection ports 41, but the water injection ports 42 may be provided on the outer peripheral side separately from the pilot nozzle 35.
  • the combustor 3 has the pilot nozzle 35 in the center and the plurality of main nozzles 37 on the outer peripheral side.
  • the combustor 3 has at least one nozzle constituting the combustor 3.
  • the combustor 3 may have any configuration.
  • the configuration described in the above embodiment can be selected or changed to another configuration as appropriate without departing from the gist of the present invention.
  • This nozzle can effectively suppress combustion vibration even in a combustor that injects water into a flame.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
PCT/JP2014/081186 2013-11-29 2014-11-26 ノズル、燃焼器、及びガスタービン Ceased WO2015080131A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US15/031,051 US10570820B2 (en) 2013-11-29 2014-11-26 Nozzle, combustion apparatus, and gas turbine
KR1020167011901A KR101752114B1 (ko) 2013-11-29 2014-11-26 노즐, 연소기, 및 가스 터빈
CN201480060669.8A CN105705866B (zh) 2013-11-29 2014-11-26 喷嘴、燃烧器以及燃气轮机
EP14865587.1A EP3076077B1 (en) 2013-11-29 2014-11-26 Nozzle, combustion apparatus, and gas turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013247076A JP6086860B2 (ja) 2013-11-29 2013-11-29 ノズル、燃焼器、及びガスタービン
JP2013-247076 2013-11-29

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Publication Number Publication Date
WO2015080131A1 true WO2015080131A1 (ja) 2015-06-04

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