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WO2016088612A1 - Chambre de combustion de turbine à gaz et turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz et turbine à gaz Download PDF

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Publication number
WO2016088612A1
WO2016088612A1 PCT/JP2015/082982 JP2015082982W WO2016088612A1 WO 2016088612 A1 WO2016088612 A1 WO 2016088612A1 JP 2015082982 W JP2015082982 W JP 2015082982W WO 2016088612 A1 WO2016088612 A1 WO 2016088612A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
combustion
gas turbine
fuel injection
burner
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/JP2015/082982
Other languages
English (en)
Japanese (ja)
Inventor
昂志 平野
貴丈 宇土
剛生 小田
嘉治 野中
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.)
Kawasaki Heavy Industries Ltd
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Kawasaki Jukogyo KK
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 Kawasaki Heavy Industries Ltd, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Priority to DE112015005430.8T priority Critical patent/DE112015005430T5/de
Priority to US15/521,314 priority patent/US20170307210A1/en
Publication of WO2016088612A1 publication Critical patent/WO2016088612A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/08—Disposition of 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
    • F23R3/28—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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/002—Combustion apparatus characterised by the shape of the combustion chamber the chamber having an elongated tubular form, e.g. for a radiant tube
    • 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
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the present invention relates to a gas turbine combustor and a gas turbine.
  • NOx nitrogen oxides
  • the applicant has a plurality of premixed combustion type main burners arranged on the upstream side (first combustion region) of the combustion chamber and the combustion chamber in the combustion chamber on the downstream side (second combustion region) of the combustion chamber.
  • a gas turbine combustor having a diffusion combustion type reheating burner arranged so as to face a dilution air hole through which air is introduced has been proposed (for example, see Patent Document 1).
  • the gas turbine combustor described in Patent Document 1 employs a diffusion combustion type reheating burner and has an advantage of low risk of flashback.
  • the fuel flow rate of the additional burner is increased, the fuel concentration in the combustion region of the additional burner increases and the combustion temperature rises, resulting in a problem that the NOx emission amount increases.
  • an object of the present invention is to reduce the NOx emission amount from the diffusion burner reheating burner in the gas turbine combustor and the gas turbine having the above-described configuration.
  • a combustor for a gas turbine according to the present invention is a combustor for a gas turbine in which fuel is mixed with combusted air introduced from a compressor and burned, and the generated combustion exhaust gas is supplied to the gas turbine.
  • a premixed combustion type main burner disposed on the upstream side of the combustion tube, and disposed on the downstream side of the main burner through the peripheral wall of the combustion tube and from the peripheral wall to the combustion chamber
  • a plurality of diffusion combustion type burner burners that inject fuel into the combustion cylinder, and the plurality of burner burners are arranged in alignment in the circumferential direction and the axial direction of the combustion cylinder.
  • the main burner is a premixed combustion method, the amount of NOx in the high-temperature combustion gas generated in the primary combustion region upstream of the combustion chamber is suppressed.
  • the plurality of additional burners are arranged in alignment in the circumferential direction and the axial direction of the combustion cylinder, and the additional fuel is distributed and supplied from each additional burner to the combustion chamber.
  • the fuel flow rate per additional burner is smaller than when the burners are arranged in the circumferential direction. Therefore, the fuel concentration in the combustion region of each additional burner is reduced, and the combustion temperature of each additional burner is reduced overall, so that the amount of NOx in the combustion gas can be suppressed.
  • the plurality of tracking burners arranged in adjacent rows may be staggered in the circumferential direction.
  • the combustion of the additional burner arranged on the downstream side is less affected by the combustion of the additional burner arranged on the upstream side by arranging the additional burners in the circumferential direction in a staggered manner. Combustion of the side burner can be stabilized.
  • a fuel header that distributes the fuel to each of the plurality of additional burners may be provided.
  • a first fuel header that distributes the first fuel mainly composed of methane to a predetermined number of additional burners, and the remaining predetermined number of additional burners contain hydrogen gas or hydrogen. You may provide the 2nd fuel header which distributes the 2nd fuel which consists of gas.
  • fuel can be distributed to a plurality of additional burners with a simple configuration.
  • the gas turbine of the present invention includes any one of the combustors described above. According to this structure, the gas turbine provided with the combustor which can suppress the discharge
  • FIG. 2A is a sectional view in the axial direction of the combustor viewed from the direction AA in FIG. 2
  • FIG. 2B is a sectional view in the axial direction of the combustor viewed from the direction BB in FIG. 2
  • FIG. 3D is an axial sectional view of the combustor viewed from the CC direction in FIG. 2
  • FIG. 4D is an axial sectional view of the combustor viewed from the DD direction in FIG.
  • Fig. 1 shows the schematic configuration and functions of the gas turbine.
  • the compressor 2 sucks the atmosphere and generates compressed air 200.
  • the compressed air 200 is combusted together with fuel in the combustor 3 to generate high-temperature and high-pressure combustion product gas (hereinafter referred to as “combustion exhaust gas 300”).
  • the combustion exhaust gas 300 is supplied to the turbine 4 and used for rotating the rotor 5.
  • the rotation of the rotor 5 is transmitted to the compressor 2 and used to generate compressed air 200 (hereinafter referred to as “combustion air 200”), while the rotation of the rotor 5 is transmitted to the generator 6 to generate power.
  • compressed air 200 compressed air 200
  • FIG. 2 shows the combustor 3.
  • the combustor 3 includes a flow direction of compressed air 200 supplied from a compressor (see FIG. 1) (a direction from the top to the bottom in FIG. 1) and a flow direction of combustion exhaust gas 300 (see FIG. 1). Is a backflow can type combustor which is opposed to each other inside.
  • the type of the combustor may be an annular type having a plurality of fuel injection valves on the circumference.
  • the combustor 3 includes a combustion cylinder 34 and a casing 35 that are arranged concentrically on the central axis 302.
  • a burner unit 30 is attached to the top of the combustion cylinder 34, and a combustion chamber 33 for burning fuel or the like injected from the burner unit 30 is formed inside the combustion cylinder 34.
  • the combustion cylinder 34 is surrounded by a cylindrical casing 35, and an annular combustion air flow path 37 through which the combustion air 200 supplied from the compressor flows is formed between the combustion cylinder 34 and the casing 35. ing.
  • the casing 35 and the combustion cylinder 34 support a plurality of reheating burners 36 on the downstream side of the burner unit 30.
  • the burner unit 30 is disposed along the central axis 302 and premixed main burner 31 that injects a premixed gas generated by mixing fuel and combustion air 200 into the combustion chamber 33.
  • a diffusion combustion type pilot burner 32 for directly injecting fuel into the combustion chamber 33.
  • the main burner 31 is arranged concentrically around the pilot burner 32.
  • the main burner 31 and the pilot burner 32 are in communication with the first fuel supply source 305 through a pipe 304.
  • the main burner 31 has an outer cylinder 310 and an inner cylinder 312 that are arranged concentrically along the central axis 302.
  • the inner cylinder 312 also serves as a combustion air injection cylinder 322b of a pilot burner 32 described later.
  • An annular space between the outer cylinder 310 and the inner cylinder 312 is used as a premixing channel 314 for mixing fuel and combustion air.
  • the pilot burner 32 includes a fuel injection cylinder 322a extending along the central axis 302 and a combustion air injection cylinder 322b concentrically mounted on the fuel injection cylinder 322a, and a fuel injection path formed in the fuel injection cylinder 322a.
  • the first fuel supply source 305 (Not shown) is connected to the first fuel supply source 305 via a pipe 304b including a flow rate adjustment valve. By opening the flow rate adjustment valve at the time of startup, the first fuel supply source 305 The supplied natural gas is injected into the combustion chamber 33.
  • An annular air flow path 324 is formed between the fuel injection cylinder 322a and the combustion air injection cylinder 322b, one end of which is connected to the combustion air flow path 37 and the other end is connected to the combustion chamber 33.
  • the combustion air 200 supplied from the compressor is injected into the combustion chamber 33.
  • the premix channel 314 has one end opened to the combustion chamber 33 and the other end opened to the combustion air channel 37 through the plurality of air intake ports 315 toward the radially outer side.
  • a plurality of main fuel nozzles 316 for ejecting the first fuel are arranged outside the air intake port 315 in the radial direction.
  • the plurality of air intake ports 315 and the plurality of main fuel nozzles 316 corresponding to the plurality of air intake ports 315 are preferably arranged at equal intervals in the circumferential direction around the central axis 302.
  • Each main fuel nozzle 316 is formed with a plurality of fuel injection holes (not shown) for injecting the first fuel toward the air intake 315 at a portion facing the air intake 315, while adjusting the flow rate. It is connected to the first fuel supply source 305 through a pipe 304a including a valve. Thus, the fuel supplied from the first fuel supply source 305 and the combustion air 200 supplied from the combustion air flow path 37 together with the combustion air 200 supplied from the first fuel supply source 305 are opened by opening the flow rate adjustment valve during normal operation. 315 is supplied to the premixing flow path 314 and mixed in the premixing flow path 314, and the premixed gas is injected into the combustion chamber 33.
  • the air intake 315 is provided with a plurality of swirl vanes (swirlers) that impart a swirl force to the combustion air 200 flowing into the premixing flow path 314 to promote premixing with the first fuel. 317 is provided.
  • the reheating burner 36 is a diffusion combustion type burner, and includes a cylindrical fuel injection nozzle 38 and an air hole 340.
  • the fuel injection nozzle 38 is included in a casing 35 along eight axial centers 360 that are included in a plane orthogonal to the central axis 302 and are arranged at equal intervals (45 ° intervals) in the circumferential direction. And attached to the combustion cylinder 34, respectively.
  • eight fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, and 38d-1 to 38d-8 each have one fuel injection nozzle row.
  • the four fuel injection nozzle rows 38a, 38b, 38c, 38d are arranged at predetermined intervals along the direction of the central axis 302 (see FIG. 2).
  • the first fuel headers 39a and 39c for distributing the first fuel to the fuel injection nozzles 38a-1 to 38a-8 and 38c-1 to 38c-8 are connected to the section.
  • the first fuel headers 39a and 39c are connected to a first fuel supply source 305 via a pipe 306 including a flow rate adjustment valve.
  • the fuel injection nozzles 38b-1 to 38b-8 and 38d-1 to 38d-8 constituting the fuel injection nozzle rows 38b and 38d are connected to 8, 38d-1 to 38d-8.
  • the second fuel headers 39b and 39d are connected to the second fuel supply source 307 via a pipe 308 including a flow rate adjusting valve. When the flow rate adjusting valve is opened during high load operation, The fuel and the second fuel are configured to be injected into the combustion chamber 33.
  • the said 1st fuel shows the liquid containing 60 volume% or more of hydrocarbons, the gas which hydrogen gas is 10 volume% or less, or 60 volume% or more of hydrocarbons.
  • the second fuel indicates a gas containing 50% by volume or more of hydrogen.
  • natural gas is illustrated as an example of the first fuel
  • hydrogen gas is illustrated as an example of the second fuel.
  • the first and second fuel headers 39a, 39c, 39b, and 39d are formed in a ring shape and arranged so as to surround the outer casing 35. Further, the fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, 38d-1 to 38d-8 are provided with respective fuel injections on the peripheral wall of the combustion cylinder 34. An air hole 340 for taking a part of compressed air 200 as combustion air from around the nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, 38d-1 to 38d-8. (See FIGS. 2 and 3).
  • 3 (a) to 3 (d) show the AA arrow cross section, the BB arrow cross section, the CC arrow cross section, and the DD arrow cross section in FIG.
  • FIGS. 3A and 3C show the angular positions of the eight fuel injection nozzles 38a-1 to 38a-8 constituting the fuel injection nozzle row 38a and the eight fuels constituting the fuel injection nozzle row 38c.
  • the angular positions of the injection nozzles 38c-1 to 38c-8 are the same.
  • the angular positions of the eight fuel injection nozzles 38b-1 to 38b-8 constituting the fuel injection nozzle row 38b are respectively equal to the eight fuel injection nozzle rows 38a and 38c.
  • the fuel injection nozzles 38a-1 to 38a-8 and 38c-1 to 38c-8 are arranged so as to be shifted by a half pitch angle (22.5 degrees) with respect to the angular positions.
  • the eight fuel injection nozzle rows 38d-1 to 38d-8 constituting the fuel injection nozzle row 38d are also at the angular positions of the eight fuel injection nozzle rows 38c. They are arranged with a half-pitch angle (22.5 degrees) shifted from the angular positions of the injection nozzles 38c-1 to 38c-8. That is, the fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, 38d-1 to 38d-8 arranged in adjacent rows are staggered in the circumferential direction. It is arranged.
  • the operation of the combustor 3 having the above-described configuration will be described below with reference to FIG.
  • the gas turbine (not shown) is started, the flow rate adjustment valve is opened, and the first fuel supplied from the first fuel supply source 305 to the pilot burner 32 via the pipe 304b. (Natural gas) is injected into the combustion chamber 33.
  • the combustion air 200 injected from the annular air flow path 324 into the combustion chamber 33 is diffused and mixed in the combustion chamber 33 and ignited by an ignition source (not shown) to form a pilot flame by diffusion combustion.
  • the first fuel supplied from the first fuel supply source 305 to each main fuel nozzle 316 via the pipe 304a and the combustion air 200 flowing from the air intake port 315 are main.
  • Mixing in the premixing flow path 314 of the burner 31 generates premixed gas.
  • the premixed gas injected from the premixing flow path 314 is ignited by the pilot flame in the combustion chamber 33 and burns in the primary combustion region S ⁇ b> 1 on the base end side of the combustion chamber 33.
  • the combustion flame temperature in the combustion chamber 33 is lowered, and the amount of NOx in the combustion exhaust gas of the main burner 31 is suppressed.
  • the memorial burner 36 When high-load combustion is required to increase the output of the gas turbine, the memorial burner 36 operates as follows. The first fuel is supplied to the first fuel headers 39a and 39c, and the first fuel passes through the eight fuel injection nozzles 38a-1 to 38a-8 constituting the fuel injection nozzle row 38a and the fuel injection nozzle row 38c. The eight fuel injection nozzles 38 c-1 to 38 c-8 constituting the same are equally distributed, and the first fuel is injected from the side of the flow of the combustion exhaust gas 300.
  • the second fuel (hydrogen gas) is supplied to the second fuel headers 39b and 39d, and the second fuel includes eight fuel injection nozzles 38b-1 to 38b-8 constituting the fuel injection nozzle row 38b.
  • the fuel is equally distributed to the eight fuel injection nozzles 38d-1 to 38d-8 constituting the fuel injection nozzle row 38d, and the second fuel is injected from the side of the flow of the combustion exhaust gas 300.
  • the supply amount and ratio of the first fuel (natural gas) and the second fuel (hydrogen gas) are appropriately determined according to the combustion conditions.
  • each of the eight fuel injection nozzles 38a-1 to 38a-8 and 38b-1 to 38b-8 can be achieved with a simple configuration.
  • 38c-1 to 38c-8, and 38d-1 to 38d-8 the target fuel can be evenly distributed.
  • the second fuel is burned from the periphery of the fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, 38d-1 to 38d-8 through the air holes 340. It diffuses and mixes with a part of the combustion air 200 flowing into the chamber 33.
  • the fuel for refueling is fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c-8, 38d-1 to 38d-8.
  • the fuel Since the fuel is distributed and supplied into the combustion chamber 33, the fuel flow rate per one burner burner 36 is reduced. Therefore, the fuel concentration in the combustion region of each additional burner 36 is reduced compared with the case where a plurality of additional burner 36 are arranged only in the circumferential direction, and the overall combustion temperature can be kept low. As a result, it depends on the combustion temperature. The amount of NOx in the combustion gas 300 can be suppressed.
  • the combustors 3 have the fuel injection nozzles 38a-1 to 38a-8, 38b-1 to 38b-8, 38c-1 to 38c- arranged in adjacent rows. 8, 38d-1 to 38d-8 are staggered in the circumferential direction. By configuring in this way, the combustion of the reheating burner disposed on the downstream side becomes less affected by the combustion of the reheating burner disposed on the upstream side, and the combustion of the downstream reheating burner is stabilized. Can do.
  • the angular positions 1 to 38d-8 may coincide with each other.
  • the combustion exhaust gas 300 increased by burning the first and second fuels introduced from the reheating burner 36 is sent to the gas turbine and used for adjusting the output of the gas turbine.
  • hydrogen gas as the second fuel is injected from the fuel injection nozzles 38b-1 to 38b-8 and 38d-1 to 38d-8. Since the mass of hydrogen gas is considerably smaller than the mass of air (a mixture of oxygen and nitrogen), the main flow of the flow of the combustion exhaust gas 300 is merely applied to the flow of the combustion exhaust gas 300 from the side thereof. (Middle part) may not be reached. Therefore, for example, as shown in FIGS. 4 (a) and 4 (b), hydrogen gas is introduced into the opening at the downstream end of the fuel injection nozzles 38b-1 to 38b-8 (38d-1 to 38d-8).
  • the hydrogen gas can be intentionally sent to the main flow (center portion) of the flow of the combustion product gas.
  • a combustion flame having a uniform concentration distribution as a whole can be formed in the secondary combustion region S2.
  • the configuration in which the first fuel is supplied to the fuel injection nozzle rows 38a and 38c and the second fuel is supplied to the fuel injection nozzle rows 38b and 38d is exemplified. It is not restricted to such a form.
  • the fuel header is manufactured in an appropriate structure, and, for example, among the fuel injection nozzles 38a-1 to 38a-8, the first fuel is injected from the fuel injection nozzles 38a-1, 38a-3, 38a-5, and 38a-7. It is also possible to adopt a configuration in which the second fuel is injected from the remaining fuel injection nozzles 38a-2, 38a-4, 38a-6, 38a-8 (the fuel injection nozzle rows 38b, 38c, 38d are provided). The same applies to the constituent fuel injection nozzles 38b-1 to 38b-8, 38c-1 to 38c-8, and 38d-1 to 38d-8).
  • the fuel injection nozzles 38 are supported on the outer casing 35 at eight equal intervals (45 degree intervals).
  • the number of the fuel injection nozzles 38 is at least two. Often, the number can be changed as appropriate. Needless to say, the pitch angle for shifting the angular position of each fuel injection nozzle in the opposed fuel injection nozzle rows also changes by changing the number of fuel injection nozzles 38.
  • the first fuel is supplied to the first fuel headers 39a and 39c and the second fuel is supplied to the second fuel headers 39b and 39d. It is also possible to supply the first fuel or the second fuel to all of the first fuel headers 39a and 39c and the second fuel headers 39b and 39d.

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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 une chambre de combustion de turbine à gaz et une turbine à gaz, avec lesquelles la quantité des émissions de NOx à partir d'un brûleur de conduit de type à combustion diffuse peut être réduite. Selon l'invention, un brûleur de conduit (36) est pourvu de buses d'injection de combustible cylindriques (38) et de trous d'air (340). Les buses d'injection de combustible (38) sont portées par un boîtier extérieur (35) le long de huit centres axiaux (360) inclus à l'intérieur d'un plan orthogonal à un axe central (302) et disposés à des intervalles équidistants (intervalles de 45 degrés) le long de la circonférence. Des ensembles de huit buses d'injection de combustible (38a-1 à 38a-8, 38b-1 à 38b-8, 38c-1 à 38c-8, 38d-1 à 38d-8) sont respectivement constitués sous forme d'uniques rangées de buses d'injection de combustible, les quatre rangées de buses d'injection de combustible (38a, 38b, 38c, 38d) étant disposées à un espacement prescrit dans le sens de l'axe central (302). Les positions angulaires des buses d'injection de combustible (38a-1 à 38a-8, 38b-1 à 38b-8, 38c-1 à 38-8, 38d-1 à 38d-8) sont disposées de façon à être décalées d'un demi-angle de pas dans des rangées opposées.
PCT/JP2015/082982 2014-12-02 2015-11-25 Chambre de combustion de turbine à gaz et turbine à gaz Ceased WO2016088612A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE112015005430.8T DE112015005430T5 (de) 2014-12-02 2015-11-25 Gasturbinenbrenner und Gasturbine
US15/521,314 US20170307210A1 (en) 2014-12-02 2015-11-25 Gas turbine combustor and gas turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2014244082A JP2016109309A (ja) 2014-12-02 2014-12-02 ガスタービン用燃焼器、及びガスタービン
JP2014-244082 2014-12-02

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WO2016088612A1 true WO2016088612A1 (fr) 2016-06-09

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US (1) US20170307210A1 (fr)
JP (1) JP2016109309A (fr)
DE (1) DE112015005430T5 (fr)
WO (1) WO2016088612A1 (fr)

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CN112283749A (zh) * 2020-11-21 2021-01-29 西安热工研究院有限公司 一种适用于燃气轮机燃烧室的旋流喷嘴装置

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JP7287811B2 (ja) * 2019-03-25 2023-06-06 三菱重工業株式会社 燃焼器及びガスタービン
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