US20180003386A1 - Fuel Nozzle of Gas Turbine Combustor and Manufacturing Method Thereof, and Gas Turbine Combustor - Google Patents

Fuel Nozzle of Gas Turbine Combustor and Manufacturing Method Thereof, and Gas Turbine Combustor Download PDF

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Publication number
US20180003386A1
US20180003386A1 US15/606,023 US201715606023A US2018003386A1 US 20180003386 A1 US20180003386 A1 US 20180003386A1 US 201715606023 A US201715606023 A US 201715606023A US 2018003386 A1 US2018003386 A1 US 2018003386A1
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US
United States
Prior art keywords
fuel nozzle
gas turbine
turbine combustor
base plate
fuel
Prior art date
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Abandoned
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US15/606,023
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English (en)
Inventor
Yoshihide Wadayama
Satoshi Kumagai
Keisuke Miura
Mitsuhiro KARISHUKU
Satoshi Dodo
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Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
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Filing date
Publication date
Application filed by Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD. reassignment MITSUBISHI HITACHI POWER SYSTEMS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DODO, SATOSHI, Karishuku, Mitsuhiro, MIURA, KEISUKE, KUMAGAI, SATOSHI, WADAYAMA, YOSHIHIDE
Publication of US20180003386A1 publication Critical patent/US20180003386A1/en
Assigned to MITSUBISHI POWER, LTD. reassignment MITSUBISHI POWER, LTD. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
Priority to US17/173,454 priority Critical patent/US11511378B2/en
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K15/00—Electron-beam welding or cutting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K15/00—Electron-beam welding or cutting
    • B23K15/0046—Welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B23P19/02—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F23R3/286—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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2213/00—Burner manufacture specifications
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to combustors and gas turbines including the combustors and, more particularly, to a fuel nozzle structure of a gas turbine combustor including a plurality of multi-hole coaxial jet burners.
  • One known combustion method of the gas turbine combustor is premixed combustion that premixes fuel with air before combustion. This can achieve a considerable reduction in the amount of NOx emissions compared with diffusion combustion in which fuel is directly injected into a combustion chamber for combustion.
  • the premixed combustion involves a higher likelihood of a backfire in which flames enter an unburned side of a fuel supply portion as a flame temperature increases.
  • a known combustor has a configuration that includes a plurality of fuel nozzles that jet fuel and an air hole plate having through holes formed therein to be associated with respective fuel nozzles.
  • the combustor is a multi-hole coaxial jet type that achieves both backfire resistance and low NOx by forming a fuel jet spurted from the fuel nozzle and an air jet spurted from the air hole into a coaxial jet to thereby uniformly mix fuel with air for combustion.
  • Patent Document 1 discloses a “gas turbine combustor including a fuel nozzle and a fuel nozzle header that form a coaxial jet of fuel and air, in which an air layer is provided between the fuel nozzle and the fuel nozzle header to insulate the fuel nozzle from the fuel nozzle header; the gas turbine combustor thereby reduces thermal stress produced on the thermal nozzle header and improves a service life of the thermal nozzle header.
  • the multi-hole, coaxial jet burner structure includes a plurality of fuel nozzles that are disposed at small intervals. Forming a sufficient welded portion is thus difficult in bonding the fuel nozzle with a base plate (fuel nozzle header). Improvement of reliability in strength of the bond portion between the fuel nozzle and the base plate thus constitutes an important challenge.
  • Patent Document 1 discloses means, for example, for screwing and fixing the fuel nozzle to the base plate. Reliability in strength of the bond portion such as the welded portion is not sufficient for operation performed over a long period of time due to high-cycle fatigue in which vibration stress acts on the fuel nozzle and thermal stress produced between the fuel nozzle and the base plate.
  • an aspect of the present invention provides a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor.
  • the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle.
  • An interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.
  • An aspect of the present invention provides a method for manufacturing a fuel nozzle for a gas turbine combustor.
  • the method includes: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.
  • the present invention considerably improves mechanical strength and reliability of a fuel nozzle for use in, for example, a multi-hole coaxial jet burner and enables healthy operation of a gas turbine combustor including the fuel nozzle over an extended period of time.
  • FIG. 1 is a perspective view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 2 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 3 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 4 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 5 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 6 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 7 is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8A is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8B is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8C is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8D is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8E is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 8F is a diagram showing a manufacturing process of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 9A is a cross-sectional view showing a schematic configuration of a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 9B is a view on arrow A-A′ in FIG. 9A .
  • FIG. 10 is a cross-sectional view showing a known fuel nozzle.
  • FIG. 11A is a cross-sectional view showing a schematic configuration of a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 11B is a view on arrow B-B′ in FIG. 11A .
  • FIG. 12 is a cross-sectional view of a fuel nozzle in a gas turbine combustor according to an embodiment of the present invention.
  • FIG. 9A is a cross-sectional view showing a structure of main parts of the gas turbine combustor.
  • FIG. 9B is a view on arrow A-A′ in FIG. 9A .
  • the following describes an embodiment in which the present invention is applied to a multi-hole coaxial jet burner. It is noted that FIGS. 9A and 9 B are schematic drawings and the number of air holes 55 differs between FIG. 9A and FIG. 9B .
  • a burner 53 includes a fuel distributor (end flange) 57 , a plurality of fuel nozzles 56 , a combustor liner 3 , and an air hole plate 54 .
  • the end flange 57 distributes fuel 41 .
  • the fuel nozzles 56 inject the fuel 41 .
  • the air hole plate 54 has a disc shape and is disposed at an upstream side end portion of the fuel liner 3 .
  • the air hole plate 54 has a plurality of air holes 55 that face a downstream side of the fuel nozzles 56 and through which combustion air 12 passes.
  • a mixture 42 of the fuel 41 and the combustion air 12 passes through the air hole plate 54 before being supplied to a combustion chamber 1 .
  • FIG. 10 shows an exemplary connection structure for a fuel nozzle 56 in the known art.
  • the fuel nozzle 56 is welded to an end flange 57 that serves as a fuel distributor.
  • the fuel nozzle 56 has a root portion bonded to the end flange 57 at a welded portion 60 ; however, an area of the fuel nozzle 56 which area inserted in the end flange 57 is not mechanically bonded to the end flange 57 and is yet to be deposited.
  • Another known art arrangement for example, is the fuel nozzle 56 screwed into the end flange 57 .
  • FIG. 1 is a view showing an appearance of the fuel nozzle 56 and the end flange 57 according to the present invention.
  • FIG. 2 is a cross-sectional view of the fuel nozzle 56 and the end flange 57 according to the present invention.
  • the fuel nozzle 56 used in the present embodiment has an outside diameter of 0.0 mm and a portion of the fuel nozzle 56 inserted in the end flange 57 has an outside diameter of 0.5 mm.
  • the nozzle has a 0.0 mm through hole thereinside through which fuel passes.
  • the end flange 57 has a hole having a hole diameter of 0.5 mm.
  • the material used for both the fuel nozzle 56 and the end flange 57 is stainless steel SUS304.
  • the fuel nozzle structure of the present embodiment includes an electron beam weld line 100 formed at a bond portion between the fuel nozzle 56 and the end flange 57 on a surface of the end flange 57 . Additionally, as shown in FIG. 2 , the fuel nozzle 56 and the end flange 57 are integrated with each other having no undeposited portion at a boundary therebetween.
  • the electron beam weld line 100 is formed to have a fusion depth 101 of 1 mm or less.
  • the multi-hole coaxial jet burner structure includes a plurality of fuel nozzles that are disposed at small intervals. Thus, preferably, the electron beam weld line 100 is formed to have a width of 1 mm or less.
  • FIG. 7 is a sectional structural drawing of the fuel nozzle 56 and the end flange 57 . It is noted that FIG. 7 shows only an area near the root of the fuel nozzle 56 and omits showing a shape of a leading end portion thereof.
  • the fuel nozzle 56 is inserted in the hole provided in the end flange 57 and seal welding is then performed by electron beam irradiation at the boundary portion with the end flange 57 at the root portion of the fuel nozzle 56 , so that the electron beam weld line 100 is formed.
  • the electron beam weld line 100 is also formed through seal welding by the electron beam irradiation on the side of a bottom surface of the end flange.
  • a bonding interface between the fuel nozzle 56 and the end flange 57 is preferably in a vacuum state. Electron beam welding (EBW) that can emit a high energy beam in a high vacuum is thus used.
  • EBW Electron beam welding
  • a subassembly of the fuel nozzle 56 and the end flange 57 is subjected to a hot isostatic pressing (HIP) process to thereby achieve metallurgical bonding in the bonding interface.
  • HIP hot isostatic pressing
  • Bonding conditions used were as follows: temperature 1100° C., pressure 120 MPa, and holding time 5 h.
  • the application of the HIP process obtains the fuel nozzle integrated with the end flange having no undeposited portion at the boundary between the fuel nozzle 56 and the end flange 57 .
  • the fuel nozzle 56 is metallurgically and integrally bonded with the end flange (base plate) 57 that supports the fuel nozzle 56 .
  • the fuel nozzle 56 and the end flange (base plate) 57 have an interface including a surface in which bonding is performed by electron beam welding (fusion joint) and an inside part in which bonding is performed by the hot isostatic pressing process (pressure bonding).
  • an orifice 106 for flow rate adjustment is press-fitted from the bottom surface of the integrated fuel nozzle as illustrated at right in FIG. 7 .
  • a flow rate characteristic of a group of fuel nozzles is thereby made uniform.
  • the electron beam welding for vacuum sealing the bonding interface is required only to provide a fusion zone that is such that a sealed portion is not broken during the hot isostatic pressing (HIP) process and is not required to provide a penetration depth to be achieved by ordinary electron beam welding.
  • the fusion zone has a shape that is 0.5 mm wide and 1.0 mm deep and yet the shape does not pose any airtightness problem during the hot pressing process. It is noted that a greater fusion depth or width as a result of the electron beam, while not posing any problem in airtight sealing performance, produces surface irregularities of the fusion zone, resulting in a crater-like dent. Thus, the fusion zone is preferably kept small.
  • the bond portion between the fuel nozzle 56 and the end flange 57 is preferably spaced apart from a nozzle wall surface.
  • the multi-hole coaxial jet burner has small intervals between nozzles and a space of at least 1.5 mm was necessary from the wall surface.
  • Having the fusion zone at a flat portion on the surface of the end flange 57 specifically, to thereby avoid a curved portion at the nozzle root portion enables emission of the electron beam in parallel with a longitudinal direction of the nozzle and is thus preferable for bonding nozzles that are spaced apart from each other at small intervals. Additionally, not having the bond portion at the curved portion of the nozzle root portion allows favorable mechanical strength to be achieved with respect to the vibration stress acting on the nozzle.
  • the present embodiment has been described for an exemplary case of a fusion joint formed mainly by electron beam irradiation as the seal welding method applied to the surfaces of the fuel nozzle 56 and the end flange 57 .
  • This is nonetheless illustrative only and not limiting. Any other welding method may be used when the requirement that the bonding interface can be airtightly sealed in a vacuum state is satisfied.
  • the fuel nozzle structure of the gas turbine combustor according to the present embodiment can improve bonding strength between the fuel nozzle and the end flange (base plate). Durability and strength reliability of the fuel nozzle of the gas turbine combustor can thereby be improved.
  • FIG. 4 shows a cross-sectional structure of a fuel nozzle 56 and an end flange 57 according to the present embodiment.
  • a protrusion 103 is formed in advance at portions of a nozzle root portion and the end flange to which electron beam welding is applied and the protrusion 103 is flattened after the hot isostatic pressing (HIP) process.
  • HIP hot isostatic pressing
  • a machined curvature 104 may be formed by cutting to remove the surface of the fusion zone (EBW) that has been formed on the flat portion.
  • FIG. 8A outlines a manufacturing process in the present embodiment.
  • FIGS. 8B to 8F show more detailed manufacturing steps.
  • the left drawing of FIG. 8A shows a condition corresponding to FIG. 8D and the right drawing of FIG. 8A shows a condition corresponding to FIG. 8F .
  • Each of FIGS. 8A to 8F shows only an area near a root of a fuel nozzle 56 and omits showing a shape of a leading end portion thereof.
  • the fuel nozzle 56 is inserted into a hole provided in an end flange 57 and a bottom plate 107 is disposed on the side of a back surface of the end flange 57 . Electron beam welding is performed on each of a bond portion between the fuel nozzle 56 and the end flange 57 and a bond portion between the end flange 57 and the bottom plate 107 to thereby form an electron beam weld line 100 .
  • the hot isostatic pressing (HIP) process is thereafter performed to integrate the fuel nozzle 56 and the end flange 57 with the bottom plate 107 as shown at right of FIG. 8A and a hole communicating with an internal hole provided in the fuel nozzle 56 is formed in the bottom plate 107 .
  • An orifice 106 is disposed inside the hole in the bottom plate 107 .
  • FIGS. 8B to 8F the above manufacturing method will be described in greater detail with reference to FIGS. 8B to 8F .
  • the internal hole in the fuel nozzle 56 is sealed by a sealing member 59 .
  • the fuel nozzles 56 are inserted in respective holes provided in the end flange 57 and the bottom plate 107 is then disposed on the back surface of the end flange 57 .
  • the boundary portions with the end flange 57 are vacuum sealed by electron beam welding as in the first embodiment.
  • end flange 57 and the bottom plate 107 disposed on the back surface of the end flange 57 are welded together along an outer periphery of the end flange 57 .
  • the electron beam weld line 100 is formed along the bond portion between the fuel nozzle 56 and the end flange 57 and the bond portion between the end flange 57 and the bottom plate 107 .
  • the bottom plate 107 has a vacuum evacuation hole 108 for vacuum evacuation formed therein. Performance of vacuum evacuation of each of bonding interfaces involving the fuel nozzles 56 , the end flange 57 , and the bottom plate 107 through the vacuum evacuation hole 108 allows sealing portions at the root portions of the fuel nozzles 56 vacuumized by, for example, the electron beam welding to be checked for, for example, a possible leak or other defect. Sealing the vacuum evacuation hole 108 provided in the bottom plate 107 after the vacuum evacuation process enables a vacuum to be maintained in the abovementioned bonding interfaces.
  • the foregoing is subjected to the hot isostatic pressing (HIP) process, which achieves metallurgical bonding in the interfaces for integration as shown in FIG. 8E . The same processing conditions are used as in the first embodiment.
  • HIP hot isostatic pressing
  • holes are drilled in portions on the previous bottom plate 107 portion in the integrated subassembly, so that the holes communicate with the respective internal holes in the fuel nozzles and function as through holes.
  • the holes are drilled in the bottom plate 107 to have hole diameters larger than hole diameters of the respective internal holes in the nozzle.
  • the orifices 106 for flow rate adjustment are then disposed in the holes drilled in the bottom plate 107 . A flow rate characteristic of the fuel nozzles 56 is thereby equalized.
  • the bottom surfaces of the fuel nozzles 56 in which through holes are formed may be sealed through, for example, welding. It is further noted that, while the above has been described for an exemplary case in which the internal hole in the fuel nozzle 56 is sealed by the sealing member 59 , the same state can also be achieved by having a closed bottom when the fuel nozzle 56 is subjected to a drilling operation.
  • the fuel nozzle structure and the manufacturing method according to the present embodiment are suitable when applied to a fuel nozzle structure in a gas turbine combustor after fluid characteristics of the fuel nozzle having a through internal hole have been evaluated.
  • a fuel nozzle structure according to a fourth embodiment will be described with reference to FIG. 3 .
  • a hole in an end flange 57 in which a fuel nozzle 56 is inserted has a positioning shoulder 102 .
  • the shoulder determines a position of the fuel nozzle 56 in a height direction and an angle of the fuel nozzle 56 with respect to the end flange 57 .
  • a surface of the end flange 57 is machined to a required depth to form the shoulder. Having the positioning shoulder 102 allows depths into which the fuel nozzles 56 disposed in a plane of the large end flange 57 are to be inserted to be selected as necessary.
  • having the positioning shoulder 102 allows the height of the fuel nozzle 56 to be accurately determined irrespective of smoothness of the surface of the end flange 57 .
  • the manufacturing method of the third embodiment in which the fuel nozzle 56 has a closed hole is used.
  • brazing portion 105 is applied to an airtight seal between a root portion of a fuel nozzle 56 and an end flange 57 .
  • BNi-5 complying with the JIS standards or other material having a high melting point is used. This is because of the following reason: specifically, the brazing material does not melt even with the application of the hot isostatic pressing (HIP) process at 1100° C. to the bonds between the fuel nozzle 56 and the end flange 57 .
  • HIP hot isostatic pressing
  • the application of the brazing to the airtight seal between the fuel nozzle 56 and the end flange 57 can achieve the same effect as that achieved by the application of the electron beam welding.
  • a fuel nozzle 56 has a recess formed on a bottom surface side thereof.
  • the recess communicates with a through hole through which fuel passes.
  • An orifice 106 for flow rate adjustment is press-fitted in the recess of the fuel nozzle 56 .
  • FIG. 6 by providing the orifice 106 for flow rate adjustment at a part of the through hole of the fuel nozzle 56 , a flow rate characteristic of a group of fuel nozzles can be made uniform.
  • FIG. 6 illustrates an example in which a bond portion between the fuel nozzle 56 and an end flange 57 is bonded by electron beam welding (EBW), the orifice 106 for flow rate adjustment can achieve the same effect even with bonding by brazing as described with reference to the fifth embodiment.
  • EBW electron beam welding
  • FIGS. 11A and 11B An embodiment in which the present invention is applied to another type of combustor is illustrated in FIGS. 11A and 11B .
  • FIG. 11A is a cross-sectional view showing a main structure of a gas turbine combustor.
  • FIG. 11B is a view on arrow B-B′ in FIG. 11A .
  • Reference symbol 200 denotes a gas turbine combustor.
  • Reference symbol 208 denotes a combustion chamber.
  • Reference symbol 203 denotes a diffusion fuel nozzle (pilot burner).
  • Reference symbol 205 denotes a premixer.
  • Reference symbol 201 denotes a premix fuel nozzle.
  • the gas turbine combustor 200 includes a diffusion burner 212 and a premix burner 211 .
  • the diffusion burner 212 includes the diffusion fuel nozzle 203 that injects diffusion combustion fuel 210 into the combustion chamber 208 .
  • the premix burner 211 includes the premix fuel nozzle 201 that injects premix fuel 206 into the premixer 205 .
  • the diffusion fuel nozzle 203 is disposed at a central portion upstream side of the combustion chamber 208 .
  • the diffusion fuel nozzle 203 is surrounded by a plurality of premixers 205 and fuel nozzles 201 for premixed combustion disposed therearound.
  • the premix fuel nozzles 201 and the diffusion fuel nozzle 203 are mechanically bonded with an end flange 207 .
  • FIG. 12 is a cross-sectional view of the premix fuel nozzle 201 .
  • the premix fuel nozzle 201 has a root portion vacuum sealed by electron beam welding (electron beam weld line 100 ) and metallurgically bonded by the hot isostatic pressing (HIP) process with the end flange 207 .
  • the bonding method or procedure in either one of the above-described embodiments is employed. Specifically, all of the above-described embodiments are applicable to not only the multi-hole coaxial jet burner, but also the bonding between the premix fuel nozzle and the end flange.
  • the application of the present invention enables integration of the fuel nozzle with the end flange involving no undeposited portion therebetween, so that favorable structural strength and reliability can be achieved.
  • the present invention is not limited to the above-described embodiments and may include various modifications.
  • the entire detailed configuration of the embodiments described above for ease of understanding of the present invention is not always necessary to embody the present invention.
  • Part of the configuration of one embodiment may be replaced with the configuration of another embodiment, or the configuration of one embodiment may be added to the configuration of another embodiment.
  • the configuration of each embodiment may additionally include another configuration, or part of the configuration may be deleted or replaced with another.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Gas Burners (AREA)
US15/606,023 2016-07-01 2017-05-26 Fuel Nozzle of Gas Turbine Combustor and Manufacturing Method Thereof, and Gas Turbine Combustor Abandoned US20180003386A1 (en)

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JP2016131411A JP6633982B2 (ja) 2016-07-01 2016-07-01 ガスタービン燃焼器、ガスタービン燃焼器の燃料ノズルの製造方法

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US17/173,454 Active US11511378B2 (en) 2016-07-01 2021-02-11 Fuel nozzle of gas turbine combustor and manufacturing method thereof, and gas turbine combustor

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US11112116B2 (en) 2019-02-27 2021-09-07 Mitsubishi Power, Ltd. Gas turbine combustor and gas turbine
US11333359B2 (en) 2019-02-27 2022-05-17 Mitsubishi Power, Ltd. Gas turbine combustor and gas turbine
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RU2665605C1 (ru) 2018-08-31
CN107559880A (zh) 2018-01-09
JP2018003696A (ja) 2018-01-11
US20210164661A1 (en) 2021-06-03
KR101939471B1 (ko) 2019-01-16
CN107559880B (zh) 2019-08-13
EP3263990A1 (en) 2018-01-03
KR20180004003A (ko) 2018-01-10
EP3263990B1 (en) 2020-09-16
RU2665605C9 (ru) 2018-11-01
JP6633982B2 (ja) 2020-01-22
US11511378B2 (en) 2022-11-29

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