US20200182469A1 - Combustor and gas turbine - Google Patents

Combustor and gas turbine Download PDF

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Publication number
US20200182469A1
US20200182469A1 US16/629,445 US201816629445A US2020182469A1 US 20200182469 A1 US20200182469 A1 US 20200182469A1 US 201816629445 A US201816629445 A US 201816629445A US 2020182469 A1 US2020182469 A1 US 2020182469A1
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United States
Prior art keywords
fuel
main
main burners
discharge holes
disposed
Prior art date
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Abandoned
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US16/629,445
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English (en)
Inventor
Mitsunori Isono
Keijiro Saito
Satoshi Takiguchi
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ISONO, Mitsunori, SAITO, KEIJIRO, TAKIGUCHI, SATOSHI
Publication of US20200182469A1 publication Critical patent/US20200182469A1/en
Abandoned legal-status Critical Current

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    • 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
    • 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
    • F02C7/228—Dividing fuel between various burners
    • 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
    • F23R3/34—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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to a combustor and a gas turbine.
  • a combustor of a gas turbine having a plurality of main burners arranged around a pilot burner at regular intervals is known.
  • this combustor there is a possibility of flames causing the same changes in a circumferential direction, that is, a possibility of combustion oscillations occurring, in a case where a change in pressure occurs in the main burners.
  • Patent Literature 1 A technique for reducing an amount of fuel supplied from some of a plurality of main premixing nozzles to curb combustion oscillations is proposed in Patent Literature 1. According to the technique of Patent Literature 1, flames of a lean fuel-air premixture supplying a small amount of fuel can be formed into longer flames than flames of a fuel-air premixture in which a concentration of fuel is not reduced.
  • Patent Literature 2 A technique for causing outlet shapes of elliptical extension tubes of some main nozzles to differ from outlet shapes of other main nozzles and shifting an ignition position to curb combustion oscillations is proposed in Patent Literature 2.
  • the combustion oscillations can be curbed by preventing generation of heat from being concentrated in a narrow region in an inner cylinder.
  • Patent Literature 3 A technique for changing a concentration of fuel of a fuel-air premixture around a central axis of each nozzle such that a flame front is made even in an axial direction even if cooling air is intermixed in order to curb generation of nitrogen oxides is disclosed in Patent Literature 3.
  • Patent Literature 2 can prevent fuel-air premixtures from all the main nozzles from being ignited and burnt at the same position, but there is still a possibility of a variation in fuel concentration distribution of the entire combustor becoming excessively large and of nitrogen oxides (NO x ) increasing.
  • Patent Literatures 1 and 2 if an attempt is made to curb the nitrogen oxides (NO x ) to reduce the variation in fuel concentration distribution, there is a possibility of an increase in combustion oscillations.
  • the invention was made in view of the above circumstances, and an object of this invention is to provide a combustor and a gas turbine capable of inhibiting an increase in nitrogen oxides and generation of combustion oscillations.
  • a combustor includes a plurality of main burners disposed at intervals in a circumferential direction.
  • the main burners include first main burners and second main burners that separately generate fuel-air mixtures.
  • the second main burners generate fuel-air mixtures that have less evenness in concentration of fuel than the fuel-air mixtures generated by the first main burners.
  • the first main burners and the second main burners are disposed in an aperiodic disposition pattern over the entire circumference in the circumferential direction.
  • the second main burners according to the first aspect may make the concentration of fuel of the fuel-air mixtures more uneven than that of the fuel-air mixtures of the first main burners in circumferential directions centered on main nozzles.
  • shapes of the flames caused by the second main burners can be slightly changed with respect to the flames caused by the first main burners in the circumferential directions of the main nozzles.
  • each of the second main burners according to the second aspect may include first fuel discharge holes that are disposed on a first side in the circumferential direction centered on the main nozzle and discharge the fuel, and second fuel discharge holes that are disposed on a second side opposite to the first side in the circumferential direction centered on the main nozzle and discharge the fuel, and the second fuel discharge holes may have larger hole diameters than the first fuel discharge holes.
  • each of the second main burners according to the second aspect may include: first fuel discharge holes that are disposed on a first side in the circumferential direction centered on the main nozzle and discharge the fuel; second fuel discharge holes that are disposed on a second side opposite to the first side in the circumferential direction centered on the main nozzle and discharge the fuel.
  • the combustor may further include a first fuel supply system that supplies the fuel to the first fuel discharge holes; and a second fuel supply system that supplies the fuel to the second fuel discharge holes at a pressure different from that of the first fuel supply system.
  • the amount of the fuel injected from the first fuel discharge holes can be made different from that injected from the second fuel discharge holes without changing the hole diameters of the first fuel discharge holes and the second fuel discharge holes. Therefore, the concentration of the fuel around the main nozzles can be easily made uneven in the second main burners.
  • a gas turbine includes the combustor according to any one of the first to fourth aspects.
  • FIG. 1 is a view illustrating a schematic constitution of a gas turbine in a first embodiment of this invention.
  • FIG. 2 is a view illustrating a schematic constitution of a combustor in the first embodiment of this invention.
  • FIG. 3 is a view illustrating disposition of main burners in the first embodiment of this invention.
  • FIG. 4 is a front view illustrating a schematic constitution of a first main burner in the first embodiment of this invention.
  • FIG. 5 is a front view illustrating a schematic constitution of a second main burner in the first embodiment of this invention.
  • FIG. 6 is a front view illustrating disposition of the first main burners and the second main burners in the first embodiment of this invention.
  • FIG. 7 is a front view equivalent to FIG. 6 in a modification of the first embodiment of this invention.
  • FIG. 8 is a view equivalent to FIG. 6 in a second embodiment of this invention.
  • FIG. 9 is a view equivalent to FIG. 6 in a third embodiment of this invention.
  • FIG. 10 is a front view equivalent to FIG. 6 in a fourth embodiment of this invention.
  • FIG. 1 is a view illustrating a schematic constitution of a gas turbine in a first embodiment of this invention.
  • a gas turbine 1 includes a compressor 2 , combustors 3 , and a turbine 4 .
  • the compressor 2 compresses air A to generate compressed air.
  • the combustors 3 burns a fuel F in the compressed air generated by the compressor 2 , and generates a high-temperature high-pressure combustion gas.
  • the turbine 4 is driven by the combustion gas generated by the combustor 3 and converts energy of the combustion gas into rotation energy.
  • the compressor 2 includes a compressor rotor 6 and a compressor casing 7 .
  • the turbine 4 includes a turbine rotor 8 and a turbine casing 9 .
  • the compressor rotor 6 and the turbine rotor 8 are disposed in series and rotate about a rotation axis Ar.
  • the turbine rotor 8 and the compressor rotor 6 are integrally connected, and a gas turbine rotor 10 is made up of the compressor rotor 6 and the turbine rotor 8 .
  • a rotor of an electric generator GEN is connected to the gas turbine rotor 10 .
  • the compressor casing 7 covers and rotatably supports the compressor rotor 6 .
  • the turbine casing 9 covers and rotatably supports the turbine rotor 8 .
  • the compressor casing 7 and the turbine casing 9 are connected, and a gas turbine casing 11 is made up of the compressor casing 7 and the turbine casing 9 .
  • the combustor 3 is fixed to the gas turbine casing 11 .
  • FIG. 2 is a view illustrating a schematic constitution of a combustor in the first embodiment of this invention.
  • FIG. 3 is a view illustrating disposition of main burners in the first embodiment of this invention.
  • the combustor 3 includes a combustion liner (or a transition piece) 13 and a fuel injector 14 A.
  • the combustion liner 13 burns the fuel F therein, and sends a combustion gas generated by the combustion of the fuel F to the turbine 4 .
  • the fuel injector 14 A ejects the fuel F and the compressed air A into the combustion liner 13 .
  • the fuel injector 14 A includes a pilot burner 15 , main burners 16 , and a burner holding cylinder 17 .
  • the pilot burner 15 is disposed on a combustor axis Ac, and diffuses and burns the fuel.
  • the pilot burner 15 includes a pilot nozzle 18 , a pilot burner shell 19 , and pilot swirlers (not illustrated).
  • the pilot nozzle 18 is formed to extend in an axial direction Da centered on the combustor axis Ac.
  • the pilot nozzle 18 has, for example, an injection hole 18 a for fuel injection at a downstream side end thereof.
  • the pilot burner shell 19 includes a main body 21 and a cone 22 .
  • the main body 21 covers an outer circumference of the pilot nozzle 18 .
  • the cone 22 is disposed on a downstream side of the main body 21 , and is formed to gradually increase in diameter toward the downstream side.
  • the pilot swirlers are disposed on an upstream side in the axial direction Da relative to a position at which the injection hole of the pilot nozzle 18 is formed.
  • the pilot swirlers (not illustrated) swirl compressed air (primary air) A flowing from the upstream side with the combustor axis Ac as a swirling center.
  • the pilot swirlers (not illustrated) extend inward from an inner circumferential surface of the main body 21 of the pilot burner shell 19 in a radial direction.
  • the plurality of pilot swirlers are formed at intervals in a circumferential direction.
  • the compressed air A compressed by the compressor 2 flows into the pilot burner shell 19 from the upstream side. Further, a fuel is injected from the injection hole of the pilot nozzle 18 . The fuel is ejected from the pilot burner shell 19 toward the combustion liner 13 along with the compressed air A to which a swirling component is given by the pilot swirlers (not illustrated), and diffused and burned in the combustion liner 13 .
  • the plurality of main burners 16 are provided, are disposed to surround an outer circumference of the pilot burner 15 , and premix and burn the fuel. These main burners 16 are disposed at intervals, more particularly, at regular intervals in a circumferential direction centered on the combustor axis Ac.
  • the main burners 16 in this embodiment include first main burners 16 A and second main burners 16 B. In the following description, in a case where there is no need to distinguish the first main burners 16 A and the second main burners 16 B, they may be referred to simply as the main burners 16 . Further, in the first and second main burners 16 A and 16 B, common portions are given the same reference signs, and a duplicate description thereof is omitted.
  • Each of the first main burner 16 A and the second main burner 16 B includes a main nozzle 23 , a main burner shell 24 , and main swirlers 25 .
  • the main nozzles 23 extend parallel to the combustor axis Ac.
  • Each of the main nozzles 23 includes a fuel channel (not illustrated) in which a fuel flows.
  • the main burner shell 24 covers an outer circumference of the main nozzle 23 .
  • a portion thereof disposed inside in a radial direction centered on the combustor axis Ac serves as a part of the pilot burner shell 19 .
  • the main swirlers 25 swirl the compressed air (the primary air) A flowing from the upstream side with the main nozzle 23 as a swirling center.
  • the main swirlers 25 extend from an outer circumferential surface of the main nozzle 23 toward an inner circumferential surface of the main burner shell 24 .
  • the plurality of main swirlers 25 are provided at intervals in a circumferential direction centered on the main nozzle 23 that is provided on each of the plurality of main burners 16 .
  • the burner holding cylinder 17 holds the pilot burner 15 and the main burners 16 described above. To be more specific, the burner holding cylinder 17 holds the pilot burner 15 and the main burners 16 such that the plurality of main burners 16 surround the outer circumference of the pilot burner 15 .
  • FIG. 4 is a front view illustrating a schematic constitution of a first main burner in the first embodiment of this invention.
  • FIG. 5 is a front view illustrating a schematic constitution of a second main burner in the first embodiment of this invention.
  • each of the main swirlers 25 of a first main burner 16 A includes fuel discharge parts 26 and 27 .
  • Each of the fuel discharge parts 26 and 27 is made up of a pair of fuel discharge holes 28 formed in pressure and suction sides 25 a and 25 b of each of the main swirlers 25 .
  • the fuel discharge part 26 is formed at a position adjacent to an outward end of the main swirler 25 in a radial direction, and the fuel discharge part 27 is formed inside the fuel discharge part 26 in a radial direction.
  • the fuel discharge holes 28 communicate with the fuel channel of each of the main nozzles 23 . These fuel discharge holes 28 are configured such that, in the fuel discharge parts 26 and 27 , the fuel discharge hole 28 formed in the pressure side 25 a is offset outside the fuel discharge hole 28 , which is formed in the suction side 25 b , in a radial direction.
  • the fuel discharge holes 28 formed in the first main burner 16 A are formed around a nozzle central axis P 3 of the main nozzle 23 such that the concentration of the fuel F mixed with the compressed air A is made substantially even.
  • all the fuel discharge holes 28 of the fuel discharge parts 26 provided on the first main burner 16 A have the same hole diameter.
  • all the fuel discharge holes 28 of the fuel discharge parts 27 provided on the first main burner 16 A have the same hole diameter.
  • the embodiment is not limited to the case where the hole diameters of the fuel discharge holes 28 are made the same as described above.
  • each of the main swirlers 25 of a second main burner 16 B includes fuel discharge parts 30 and 31 .
  • Each of the fuel discharge parts 30 and 31 is made up of a pair of fuel discharge holes 32 formed in the pressure and suction sides 25 a and 25 b of each of the main swirlers 25 .
  • the fuel discharge part 30 is formed at a position adjacent to an outward end of the main swirler 25 in a radial direction, and the fuel discharge part 31 is formed inside the fuel discharge part 30 in a radial direction.
  • the fuel discharge holes 32 communicate with the fuel channel of each of the main nozzles 23 . These fuel discharge holes 32 are configured such that, in the fuel discharge parts 30 and 31 , the fuel discharge hole 32 formed in the pressure side 25 a is offset outside the fuel discharge hole 32 , which is formed in the suction side 25 b , in a radial direction.
  • the second main burners 16 B change a concentration of fuel around a nozzle central axis P 3 compared to the first main burners 16 A, and supply fuel-air premixtures to the combustion liner 13 .
  • the second main burners 16 B change the concentration of the fuel around the nozzle central axis P 3 , and supply the fuel-air premixtures to the combustion liner.
  • the second main burners 16 B generate the fuel-air premixtures that have less evenness in the concentration of fuel than those generated by the first main burners 16 A.
  • the plurality of fuel discharge holes 32 formed in the second main burner 16 B are divided into a first group G 1 and a second group G 2 .
  • the fuel discharged from each of the fuel discharge holes 32 of the first group G 1 reaches an inside first range S 1 (see FIG. 3 ) in the radial direction centered on the combustor axis Ac.
  • the fuel discharged from each of the fuel discharge holes 32 of the second group G 2 reaches an outside second range S 2 (see FIG. 3 ) in the radial direction centered on the combustor axis Ac.
  • the second main burner 16 B has the first group G 1 made up of the fuel discharge parts 30 of two main swirlers 25 located on an inner side (a second side in the circumferential direction) in the radial direction centered on the combustor axis Ac (see FIG. 3 ) and the fuel discharge part 30 of one main swirler 25 adjacent to these two main swirlers 25 in a swirling direction. Furthermore, the second main burner 16 B has the second group G 2 made up of the fuel discharge parts 30 of the remaining three main swirlers 25 including the two main swirlers 25 located on an outer side (a first side in the circumferential direction) in the radial direction centered on the combustor axis Ac (see FIG. 3 ).
  • the fuel discharge holes 32 of the fuel discharge parts 30 belonging to the first group G 1 differ in opening areas (hole diameters) from those of the fuel discharge parts 30 belonging to the second group G 2 .
  • Each of the fuel discharge parts 31 of the six main swirlers 25 includes the fuel discharge holes 32 which are all the same size.
  • the opening areas (the hole diameters) of the fuel discharge holes 32 of the first embodiment for example when the fuel discharge holes 32 in the fuel discharge parts 31 are set to “1,” the fuel discharge holes 32 of the fuel discharge parts 30 belonging to the first group G 1 are set to “0.9,” and the fuel discharge holes 32 of the fuel discharge parts 30 belonging to the second group G 2 are set to “1.1.”
  • the fuel discharge holes 32 of the fuel discharge parts 30 belonging to the second group G 2 are set to “1.1.”
  • a discharged amount of fuel of the fuel discharge holes 32 disposed on the outer side in the radial direction centered on the nozzle central axis P 3 of the main nozzle 23 is different from that of the fuel discharge holes 32 disposed on the inner side in the radial direction. Furthermore, a discharged amount of fuel of each of the fuel discharge parts 30 of the six main swirlers 25 is divided into two types around the nozzle central axis P 3 of the main nozzle 23 .
  • FIG. 6 is a front view illustrating disposition of the first main burners and the second main burners in the first embodiment of this invention.
  • the fuel injector 14 A includes five first main burners 16 A that are continuously arranged in the circumferential direction centered on the combustor axis Ac and three second main burners 16 B that are continuously arranged in the circumferential direction as well.
  • the fuel injector 14 A illustrated in FIG. 6 includes the eight main burners 16 is illustrated.
  • the number of main burners 16 may be nine or more or seven or fewer as long as there are a plurality of main burners 16 .
  • the number of first main burners 16 A and the number of second main burners 16 B are not limited to the above numbers.
  • the fuel injector 14 A may include both the first main burners 16 A and the second main burners 16 B.
  • positions of the eight main burners 16 arranged in the circumferential direction are indicated by disposition numbers “1” to “8.”
  • the fuel injector 14 A in the first embodiment has the first and second main burners 16 A and 16 B disposed in an aperiodic disposition pattern over the entire circumference in the circumferential direction.
  • periodic disposition pattern means that a pattern of the order in which the first and second main burners 16 A and 16 B are disposed is repeated only in the same pattern around the combustor axis Ac once in the circumferential direction. Examples of periodic patterns may include a case where the first and second main burners 16 A and 16 B are alternately disposed in the circumferential direction, a case where only the first main burners 16 A are disposed, a case where only the second main burners 16 B are disposed, and so on.
  • the disposition pattern of the main burners 16 in the fuel injector 14 A in the first embodiment is configured such that the pattern of the order in which the first and second main burners 16 A and 16 B are disposed is not repeated only in the same pattern around the combustor axis Ac once in the circumferential direction.
  • first and second main burners 16 A and 16 B of the fuel injector 14 A in the first embodiment are disposed in an asymmetric disposition pattern in the circumferential direction centered on the combustor axis Ac.
  • “Asymmetric disposition pattern in the circumferential direction” means that the first and second main burners 16 A and 16 B are not disposed in an order that has so-called rotational symmetry.
  • the second main burners 16 B of the fuel injector 14 A are disposed such that the first group G 1 and the second group G 2 are divided into the inner side and the outer side in the radial direction centered on the combustor axis Ac. That is, the concentration of the fuel of the fuel-air premixtures is made uneven in the radial direction centered on the combustor axis Ac in places in which the second main burners 16 B of the fuel injector 14 A are disposed. In other words, the concentration of the fuel of the fuel-air premixtures of the second main burners 16 B is made uneven in the circumferential directions centered on the main nozzles 23 .
  • the case where the first group G 1 is disposed on the inner side in the radial direction and the second group G 2 is disposed on the outer side in the radial direction is given by way of example.
  • flames caused by the first main burners 16 A can be made slightly different from flames caused by the second main burners 16 B.
  • the fuel concentration distribution can be inhibited from becoming uniform in the circumferential direction of the fuel injector 14 A in which the main burners 16 are disposed.
  • the fuel concentration distribution can be inhibited from excessively varying in the entire combustor 3 .
  • an increase in nitrogen oxides (NO x ) and generation of combustion oscillations can be separately curbed.
  • the fuel concentration distribution can be inhibited from becoming uniform in the circumferential direction.
  • shapes of the flames caused by the second main burners 16 B can be slightly changed with respect to the flames caused by the first main burners 16 A in the circumferential direction centered on the nozzle central axis P 3 .
  • the hole diameters (the opening areas) of the fuel discharge holes 32 (the second fuel discharge holes) of the second group G 2 are made larger than those of the fuel discharge holes 32 (the first fuel discharge holes) of the first group G 1 .
  • the amount of the fuel discharged from the fuel discharge holes 32 of the second group G 2 can be made more than that discharged from the fuel discharge holes 32 of the first group G 1 .
  • the concentration of the fuel around each of the main nozzles 23 (in other words, around each of the nozzle central axes P 3 ) can be easily made uneven in the second main burners 16 B.
  • FIG. 7 is a front view equivalent to FIG. 6 in a modification of the first embodiment of this invention.
  • the disposition of the first and second groups G 1 and G 2 in each of the second main burners 16 B is not limited to the disposition exemplified in the first embodiment.
  • the first and second groups G 1 and G 2 in each of the second main burners 16 B may be separately divided and disposed in the circumferential direction centered on the combustor axis Ac.
  • the case where the first group G 1 is disposed on the inner side in the radial direction centered on the combustor axis Ac and the second group G 2 is disposed on the outer side in the radial direction centered on the combustor axis Ac has been given by way of example.
  • the first group G 1 may be disposed on the outer side in the radial direction centered on the combustor axis Ac
  • the second group G 2 may be disposed on the inner side in the radial direction centered on the combustor axis Ac.
  • both the second main burners 16 B in which the first group G 1 is disposed on the inner side in the radial direction centered on the combustor axis Ac and the second main burners 16 B in which the first group G 1 is disposed on the outer side in the radial direction centered on the combustor axis Ac may be separately provided.
  • the second main burners 16 B in which the disposition of the first group G 1 and the second group G 2 is divided in the radial direction centered on the combustor axis Ac and the second main burners 16 B in which the disposition of the first group G 1 and the second group G 2 is divided in the circumferential direction centered on the combustor axis Ac may be mixed in the fuel injector 14 A.
  • the second embodiment changes the disposition pattern of the main burners with respect to the aforementioned first embodiment. For this reason, the same portions as the aforementioned first embodiment are described with the same reference signs, and duplicate description thereof is omitted.
  • FIG. 8 is a view equivalent to FIG. 6 in a second embodiment of this invention.
  • a fuel injector 14 B in the second embodiment includes first main burners 16 A and second main burners 16 B that act as a plurality of main burners 16 .
  • the first main burners 16 A and the second main burners 16 B have the same constitution except that fuel concentration distributions are different.
  • the fuel injector 14 B has seven first main burners 16 A and only one second main burner 16 B that are continuously disposed in a circumferential direction. As in FIG. 6 , the case where the fuel injector 14 B illustrated in FIG. 8 includes the eight main burners 16 is illustrated. However, the number of main burners 16 may be nine or more or seven or less as long as there are a plurality of main burners 16 .
  • the fuel injector 14 B only one second main burner 16 B is provided and, thereby like the fuel injector 14 A of the first embodiment, the first main burners 16 A and the second main burner 16 B are disposed in an aperiodic disposition pattern over the entire circumference in the circumferential direction.
  • the fuel injector 14 B has the first main burners 16 A and the second main burner 16 B disposed in an aperiodic disposition pattern (a disposition pattern that is not in rotational symmetry) in the circumferential direction centered on a combustor axis Ac.
  • FIG. 8 a case where a first group G 1 is disposed on an outer side in a radial direction centered on the combustor axis Ac and a second group G 2 is disposed on an inner side is given by way of example, but this invention is not limited to this disposition.
  • the disposition of the first group G 1 and the second group G 2 of FIG. 8 may be replaced.
  • the first group G 1 and the second group G 2 may be directed in any direction, for example in the radial direction and the circumferential direction centered on the combustor axis Ac.
  • fuel concentration distribution caused by the first main burners 16 A can be made slightly different from that caused by the second main burner 16 B. For this reason, flames can be inhibited from becoming uniform in the circumferential direction of the fuel injector 14 A in which the main burners 16 are disposed.
  • the fuel concentration distribution can be inhibited from excessively varying in the entire combustor 3 . As a result, an increase in nitrogen oxides (NO x ) and generation of combustion oscillations can be separately curbed.
  • the third embodiment changes the disposition pattern of the main burners with respect to the aforementioned first embodiment. For this reason, the same portions as the aforementioned first embodiment are described with the same reference signs, and duplicate description thereof is omitted.
  • FIG. 9 is a view equivalent to FIG. 6 in a third embodiment of this invention.
  • a fuel injector 14 C in the third embodiment includes first main burners 16 A and second main burners 16 B that act as a plurality of main burners 16 .
  • the first main burners 16 A and the second main burners 16 B have the same constitution except that the fuel concentration distributions are different.
  • the fuel injector 14 C has four first main burners 16 A as well as four second main burner 16 B. Like the first embodiment, the case where the fuel injector 14 C in the third embodiment includes the eight main burners 16 is illustrated. However, the number of main burners 16 may be nine or more or seven or less as long as there are a plurality of main burners 16 .
  • the first main burners 16 A and the second main burners 16 B are alternately disposed in a circumferential direction centered on a combustor axis Ac.
  • the second main burners 16 B in the third embodiment also has a constitution in that disposition of first and second groups G 1 and G 2 is not limited to that illustrated in FIG. 9 .
  • fuel concentration distribution caused by the first main burners 16 A can be made slightly different from that caused by the second main burners 16 B. For this reason, the fuel concentration distribution can be inhibited from becoming uniform in a circumferential direction of the fuel injector 14 A in which the main burners 16 are disposed.
  • the fuel concentration distribution can be inhibited from excessively varying in the entire combustor 3 . As a result, an increase in nitrogen oxides (NO x ) and generation of combustion oscillations can be separately curbed.
  • the fourth embodiment is different from the aforementioned first embodiment only in a constitution in which, in each main burner 16 B, an injected amount of fuel of a first group G 1 is made different from that of a second group G 2 . For this reason, the same portions as the aforementioned first embodiment are described with the same reference signs, and duplicate description thereof is omitted.
  • FIG. 10 is a front view equivalent to FIG. 6 in a fourth embodiment of this invention.
  • a main nozzle 23 of the main burner 16 B in the fourth embodiment includes a first fuel supply system F 1 and a second fuel supply system F 2 that are independent of each other.
  • the main burner 16 B includes fuel discharge holes 32 that communicate with the first fuel supply system F 1 and belong to the first group G 1 , and fuel discharge holes 32 that communicate with the second fuel supply system F 2 and belong to the second group G 2 .
  • the first fuel supply system F 1 and the second fuel supply system F 2 are different in supply pressure of fuel F from each other.
  • the first fuel supply system F 1 and the second fuel supply system F 2 may separately adjust, for example, a discharged amount of the fuel F that is discharged from the fuel discharge holes 32 of main swirlers 25 belonging to the first group G 1 , and a discharged amount of the fuel F that is discharged from the fuel discharge holes 32 of main swirlers 25 belonging to the second group G 2 .
  • a pressure ratio between the fuel F supplied by the first fuel supply system F 1 and the fuel F supplied by the second fuel supply system F 2 may be set to 0.9:1.1.
  • the amount of the fuel discharged from the fuel discharge holes 32 of the first group G 1 can be made different from that discharged from the fuel discharge holes 32 of the second group G 2 . Therefore, a concentration of fuel around the main nozzle 23 can be easily made uneven in the second main burner 16 B.
  • the disposition pattern of the first and second main burners 16 A and 16 B is made different, but may be a disposition pattern other than the aforementioned disposition patterns.
  • the disposition pattern may include both the first main burners 16 A and the second main burners 16 B, and may be used as, for example, disposition patterns from Case 1 to Case 22 shown in the following table.
  • numbers “1” to “22” recorded in the leftmost column are cases, and numbers “1” to “8” recorded at the uppermost position in each column correspond to the positions “1” to “8” of the main burners 16 in the circumferential direction of each of the above embodiments.
  • the rightmost column is the “number” of second main burners 16 B in one fuel injector.
  • a case where the first main burners 16 A are disposed is set to “0,” and a case where the second main burners 16 B are disposed is set to “1”.
  • the disposition pattern of the main burners 16 is not limited to those of the following table, and the disposition patterns of the following table may be disposition patterns rotated in the circumferential direction.
  • Case “1” involved disposition patterns obtained by rotating the disposition pattern of the second embodiment around the nozzle central axis P 3 , and substantially the same result was obtained from the disposition patterns.
  • Case “6” also involved disposition patterns obtained by rotating the disposition pattern of the first embodiment around the nozzle central axis P 3 , and substantially the same result was obtained from the disposition patterns.
  • Case “22” involved disposition patterns identical to that of the third embodiment.
  • the three patterns of Cases “1,” “6” and “22” will be described as representative examples.
  • This invention is not limited to the constitutions of the above embodiments, and can include a change in design without departing from the gist of this invention.
  • the concentration of fuel in the first main burners 16 A in the circumferential direction substantially becomes even has been described.
  • the variation in the concentration of fuel in the first main burners 16 A in the circumferential direction may be smaller than that in the second main burners 16 B, and this invention is not limited to the case where the concentration of fuel is even.
  • each of the second main burners 16 B includes the first and second groups G 1 and G 2 having different injected amounts of fuel
  • the number of groups having different injected amounts of fuel is not limited to two. Three or more groups may be formed. Further, depending on the number of groups which each of the second main burners 16 B includes, a kind of the injected amount may be three or more.
  • each of the second main burners 16 B generates the fuel-air premixture in which the concentration of fuel is uneven in the circumferential direction centered on the nozzle central axis P 3 has been described.
  • the second main burners 16 B can curb a variation in the flames of the entire combustor 3 while the flames caused by the fuel-air premixture generated by each of the second main burners 16 B are made different from the flames caused by the fuel-air premixture generated by each of the first main burners 16 A
  • the fuel-air premixture is not limited to the constitution in which the concentration of fuel is uneven in the circumferential direction centered on the nozzle central axis P 3 .
  • the fuel discharge holes 28 and 32 are formed in the main swirlers 25 .
  • the fuel discharge holes 28 and 32 are not limited to being formed in the main swirlers 25 .
  • the fuel discharge holes 28 and 32 may be formed in outer circumferential surfaces of the main nozzles 23 .
  • the ratio between the hole diameters of the fuel discharge holes 32 of the first group G 1 and the hole diameters of the fuel discharge holes 32 of the second group G 2 , and the ratio between the amount of the fuel discharged from the fuel discharge holes 32 of the first group G 1 and the amount of the fuel discharged from the fuel discharge holes 32 of the second group G 2 are not limited to the ratios of each of the above embodiments.
  • This invention can be applied to a combustor. According to this combustor, an increase in nitrogen oxides and generation of combustion oscillations can be separately curbed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US16/629,445 2017-07-19 2018-07-19 Combustor and gas turbine Abandoned US20200182469A1 (en)

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JP2017140209A JP2019020071A (ja) 2017-07-19 2017-07-19 燃焼器及びガスタービン
PCT/JP2018/027085 WO2019017429A1 (ja) 2017-07-19 2018-07-19 燃焼器及びガスタービン

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CN115335638A (zh) * 2020-03-31 2022-11-11 三菱重工业株式会社 燃气轮机的燃烧器以及燃气轮机
CN117968094A (zh) * 2024-02-20 2024-05-03 中国航发四川燃气涡轮研究院 阵列多点喷射燃烧室及其一体化喷嘴结构

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JP2989515B2 (ja) * 1995-04-11 1999-12-13 三菱重工業株式会社 ガスタービンの予混合式燃焼装置
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
JPH11294770A (ja) 1998-04-15 1999-10-29 Mitsubishi Heavy Ind Ltd 燃焼器
JP2001254947A (ja) 2000-03-14 2001-09-21 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
JP2002201966A (ja) * 2000-12-28 2002-07-19 Toyota Central Res & Dev Lab Inc ガスタービン用予混合燃焼器およびその燃料供給制御方法
DE10108560A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer
EP1400752B1 (en) * 2002-09-20 2008-08-06 Siemens Aktiengesellschaft Premixed burner with profiled air mass stream, gas turbine and process for burning fuel in air
WO2005095864A1 (de) * 2004-03-31 2005-10-13 Alstom Technology Ltd Mehrfachbrenneranordnung zum betrieb einer brennkammer sowie verfahren zum betreiben der mehrfachbrenneranordnung
US8037688B2 (en) * 2006-09-26 2011-10-18 United Technologies Corporation Method for control of thermoacoustic instabilities in a combustor
EP2698582B1 (en) * 2011-03-16 2017-11-22 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and gas turbine
WO2013128572A1 (ja) * 2012-02-28 2013-09-06 三菱重工業株式会社 燃焼器及びガスタービン
JP5984770B2 (ja) * 2013-09-27 2016-09-06 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
JP6222633B2 (ja) 2013-11-15 2017-11-01 三菱日立パワーシステムズ株式会社 制御装置、燃焼器、ガスタービン、制御方法及び制御プログラム
JP6086860B2 (ja) * 2013-11-29 2017-03-01 三菱日立パワーシステムズ株式会社 ノズル、燃焼器、及びガスタービン
JP2017140209A (ja) 2016-02-10 2017-08-17 株式会社日立製作所 磁気共鳴イメージング装置及び画像処理方法

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JP2019020071A (ja) 2019-02-07
DE112018003678T5 (de) 2020-05-14
WO2019017429A1 (ja) 2019-01-24
JP7161567B2 (ja) 2022-10-26
JP2021101152A (ja) 2021-07-08

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