WO2014126234A1 - タービンノズル及びその製造方法 - Google Patents

タービンノズル及びその製造方法 Download PDF

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Publication number
WO2014126234A1
WO2014126234A1 PCT/JP2014/053603 JP2014053603W WO2014126234A1 WO 2014126234 A1 WO2014126234 A1 WO 2014126234A1 JP 2014053603 W JP2014053603 W JP 2014053603W WO 2014126234 A1 WO2014126234 A1 WO 2014126234A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine nozzle
ring portion
brazing material
manufacturing
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2014/053603
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
博道 平木
善博 川又
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to US14/760,517 priority Critical patent/US20150354593A1/en
Priority to EP14751725.4A priority patent/EP2933440A4/en
Priority to CN201480005178.3A priority patent/CN104937220B/zh
Priority to RU2015128612A priority patent/RU2015128612A/ru
Publication of WO2014126234A1 publication Critical patent/WO2014126234A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B23K1/0018—Brazing of turbine parts
    • 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
    • B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
    • B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
    • 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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/008—Rocket engine parts, e.g. nozzles, combustion chambers
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49325—Shaping integrally bladed rotor

Definitions

  • the present invention relates to a turbine nozzle and a manufacturing method thereof.
  • the present invention particularly relates to a turbine nozzle that is a part of a turbo pump for a rocket engine and a method for manufacturing the same.
  • turbo pumps are used to supply fuel and oxidants (see Patent Document 1).
  • One of the components of the turbo pump is a turbine nozzle.
  • the turbine nozzle is a component that functions to expand and decompress the gas and change the flow direction of the gas so that the gas collides with the turbine blade at an optimum angle.
  • the turbine nozzle has been integrally molded as one component.
  • machining which limits the machining method.
  • electric discharge machining for example, there is a problem that manufacturing cost and manufacturing time increase. Even in the case of casting, the manufacturing time is long, and there is a problem that the cost is high in small-volume production.
  • One object of the present invention is to provide a technique capable of reducing the cost and time required for manufacturing a turbine nozzle.
  • a method for manufacturing a turbine nozzle includes an inner ring part, an outer ring part having a larger diameter than the inner ring part, and a blade sandwiched between the inner ring part and the outer ring part.
  • the manufacturing method includes: (A) a step of forming a first part integrally including one of the inner ring portion and the outer ring portion and a blade; and (B) the other of the inner ring portion and the outer ring portion.
  • Forming the second part (C) combining the first part and the second part such that the outer surface of the inner ring portion and the inner surface of the outer ring portion face each other; A gap is formed between the wing of the one part and the second part, and includes (D) melting and pouring the brazing material into the gap and brazing the wing of the first part and the second part.
  • the manufacturing method may further include a step of inserting a spacer into the gap between the step (C) and the step (D).
  • the brazing material may be installed on the upper surface of the wing at a position adjacent to the gap.
  • the brazing material may include both a wire brazing material and a powder brazing material.
  • the first part is integrally provided with an inner ring portion and a wing.
  • the second component is an outer diameter ring portion.
  • a turbine nozzle in another aspect of the present invention, includes an inner ring part, an outer ring part having a larger diameter than the inner ring part, and a blade sandwiched between the inner ring part and the outer ring part.
  • One of the inner diameter ring portion and the outer diameter ring portion and the wing are integrally formed as a first component.
  • the other of the inner ring portion and the outer ring portion is a second part.
  • the wing of the first part and the second part are brazed.
  • FIG. 1 is a top view schematically showing a configuration of a turbine nozzle.
  • FIG. 2 is a side view schematically showing a cross-sectional structure of a blade of the turbine nozzle.
  • FIG. 3 is a top view conceptually showing the method for manufacturing the turbine nozzle according to the first embodiment of the present invention.
  • FIG. 4 is a top view for explaining the method for manufacturing the turbine nozzle according to the first embodiment of the present invention.
  • FIG. 5 is a side view for explaining the method for manufacturing the turbine nozzle according to the first embodiment of the present invention.
  • FIG. 6 is a top view for explaining the method for manufacturing the turbine nozzle according to the second embodiment of the present invention.
  • FIG. 7 is a side view for explaining the turbine nozzle manufacturing method according to the second embodiment of the present invention.
  • FIG. 8 is a side view for explaining the method for manufacturing the turbine nozzle according to the third embodiment of the present invention.
  • FIG. 9 is a top view conceptually showing the method for manufacturing the turbine nozzle according to the
  • FIG. 1 is a top view schematically showing a configuration of a turbine nozzle 1 according to the present embodiment.
  • the turbine nozzle 1 includes an inner diameter ring portion 10, an outer diameter ring portion 20, and a blade 30.
  • Both the inner diameter ring portion 10 and the outer diameter ring portion 20 are members having a ring shape.
  • the inner ring portion 10 has an inner surface 11 and an outer surface 12.
  • the outer ring portion 20 has an inner surface 21 and an outer surface 22.
  • the diameter of the outer ring part 20 is larger than the diameter of the inner ring part 10. More specifically, the diameter of the inner surface 21 of the outer diameter ring portion 20 is larger than the diameter of the outer surface 12 of the inner diameter ring portion 10. Therefore, the inner diameter ring portion 10 can be disposed in the ring of the outer diameter ring portion 20, and at this time, the outer side surface 12 of the inner diameter ring portion 10 and the inner side surface 21 of the outer diameter ring portion 20 face each other.
  • FIG. 2 schematically shows a cross-sectional structure of the blade 30 when viewed from the direction A in FIG.
  • each wing 30 has a cross-sectional wing shape.
  • the plurality of blades 30 are annularly arranged in the space between the inner ring portion 10 and the outer ring portion 20.
  • a gap between adjacent blades 30 is a gas flow path.
  • the first part PA and the second part PB are molded separately.
  • the first part PA is a part that integrally includes the inner diameter ring portion 10 and the blade 30.
  • the second component PB is the outer diameter ring portion 20.
  • the first part PA is arranged in the ring of the second part PB (outer diameter ring portion 20). That is, the first component PA and the second component PB are combined so that the outer side surface 12 of the inner diameter ring portion 10 and the inner side surface 21 of the outer diameter ring portion 20 face each other. Then, the blade 30 of the first part PA and the second part PB are joined by “brazing”. Thereby, the turbine nozzle 1 is completed.
  • the turbine nozzle 1 produced in this way has a brazing part 40 (joint part by brazing material) between the blade 30 and the second part PB.
  • FIG. 4 and 5 are a top view and a side view, respectively, for explaining the “brazing” in more detail.
  • the first part PA is arranged in the ring of the second part PB (outer diameter ring part 20), as shown in FIG. 4, the inner surface of the blade 30 and the second part PB (outer diameter ring part 20).
  • a slight gap 50 is formed between the two.
  • the sizes and shapes of the first part PA and the second part PB are designed so that a slight gap 50 is formed.
  • the gap is preferably constant, but is not limited thereto.
  • the brazing material 60 is an alloy having a lower melting point than the first part PA and the second part PB, which are the base materials.
  • a nickel-based brazing material 60 is used.
  • Such a brazing material 60 is installed in or near the gap 50.
  • the brazing material 60 is placed on the upper surface of the wing 30 at a position adjacent to the gap 50 as shown in FIGS. 4 and 5. After the brazing material 60 is installed, heating is performed. By this heating, the brazing material 60 is melted and flows into the gap 50. In this way, the blade 30 of the first part PA and the second part PB are brazed.
  • the turbine nozzle 1 is created by brazing the first part PA and the second part PB.
  • the gas flow path is also narrowed.
  • the turbine nozzle 1 is integrally molded as a single part, such a narrow gas flow path can be precisely created by machining. Have difficulty.
  • the first part PA and the second part PB can be easily created by machining. Therefore, it is possible to reduce the cost and time required for manufacturing the turbine nozzle 1 as compared with the case of electric discharge machining or casting.
  • [Second Embodiment] 6 and 7 are a top view and a side view, respectively, for explaining brazing in the second embodiment.
  • the spacer 70 is inserted into the gap 50. After the spacer 70 is inserted into the gap 50, the brazing material 60 is melted and poured into the gap 50 as in the case of the first embodiment.
  • the spacer 70 is exemplified by nickel foil. Such a spacer 70 is sandwiched between the outer side surface of the blade 30 and the inner side surface 21 of the outer diameter ring portion 20.
  • the installation position of the spacer 70 is arbitrary as long as the occurrence of misalignment is prevented, but it is preferable that the spacer 70 be disposed uniformly over the entire circumference of the gap 50.
  • the same effect as in the first embodiment can be obtained.
  • the “center misalignment” is prevented from occurring between the first part PA and the second part PB.
  • FIG. 8 is a schematic view for explaining the brazing material 60 in the third embodiment.
  • the brazing material 60 includes a powder brazing material 62 in addition to the wire brazing material 61.
  • the powder brazing material 62 has a property that it is easier to melt than the wire brazing material 61. And if the powder brazing material 62 melts, it will become invitation water and the wire brazing material 61 will also begin to melt. That is, when the powder brazing material 62 is used, the wire brazing material 61 is more easily melted than when the powder brazing material 62 is not provided.
  • the powder brazing material 62 is provided at the end of the brazing material 60, for example.
  • powder brazing material 62 is applied to both ends of wire brazing material 61. Thereby, the brazing material 60 becomes easy to melt as a whole.
  • the first part PA and the second part PB are molded separately.
  • the first part PA is a part that integrally includes the outer diameter ring portion 20 and the blade 30.
  • the second component PB is the inner diameter ring portion 10.
  • the second part PB (inner diameter ring portion 10) is arranged in the ring of the first part PA. That is, the first component PA and the second component PB are combined so that the outer side surface 12 of the inner diameter ring portion 10 and the inner side surface 21 of the outer diameter ring portion 20 face each other. Then, the blade 30 of the first part PA and the second part PB are joined by “brazing”.
  • the brazing method is the same as in the above-described embodiment.
  • the turbine nozzle 1 produced in this way has a brazing part 40 (joint part by brazing material) between the blade 30 and the second part PB.
  • JP2013-029430 This application claims convention priority based on the Japanese patent application number (JP2013-029430). The disclosure of which is incorporated herein by reference.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2014/053603 2013-02-18 2014-02-17 タービンノズル及びその製造方法 Ceased WO2014126234A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US14/760,517 US20150354593A1 (en) 2013-02-18 2014-02-17 Turbine nozzle and manufacturing method thereof
EP14751725.4A EP2933440A4 (en) 2013-02-18 2014-02-17 TURBINE NOZZLE AND METHOD FOR THE MANUFACTURE THEREOF
CN201480005178.3A CN104937220B (zh) 2013-02-18 2014-02-17 涡轮机喷嘴及其制造方法
RU2015128612A RU2015128612A (ru) 2013-02-18 2014-02-17 Сопло турбины и способ его изготовления

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013029430A JP6045389B2 (ja) 2013-02-18 2013-02-18 タービンノズル及びその製造方法
JP2013-029430 2013-02-18

Publications (1)

Publication Number Publication Date
WO2014126234A1 true WO2014126234A1 (ja) 2014-08-21

Family

ID=51354232

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2014/053603 Ceased WO2014126234A1 (ja) 2013-02-18 2014-02-17 タービンノズル及びその製造方法

Country Status (6)

Country Link
US (1) US20150354593A1 (enExample)
EP (1) EP2933440A4 (enExample)
JP (1) JP6045389B2 (enExample)
CN (1) CN104937220B (enExample)
RU (1) RU2015128612A (enExample)
WO (1) WO2014126234A1 (enExample)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6841376B2 (ja) 2018-02-27 2021-03-10 株式会社Ihi ロケットエンジン用ターボポンプ
CN115523029B (zh) * 2022-10-24 2024-12-10 德阳钰鑫机械制造有限公司 一种整流器的制造工艺及整流器

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JP2005098133A (ja) * 2003-09-22 2005-04-14 Toshiba Corp ガスタービン翼の拡散ろう付補修方法および補修用治具
JP2005103641A (ja) * 2003-09-26 2005-04-21 General Electric Co <Ge> ニッケル系ろう合金組成、その関連方法及び物品
JP2009222010A (ja) 2008-03-18 2009-10-01 Mitsubishi Heavy Ind Ltd ロケットノズル及びロケットエンジン燃焼ガス流れの制御方法
JP2013002444A (ja) * 2011-06-17 2013-01-07 General Electric Co <Ge> タービンエンジンのタービンノズルセグメントを補修する方法
JP2013029430A (ja) 2011-07-28 2013-02-07 Mitsubishi Electric Corp ２チャネル追尾装置、および追尾方法

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JP2005098133A (ja) * 2003-09-22 2005-04-14 Toshiba Corp ガスタービン翼の拡散ろう付補修方法および補修用治具
JP2005103641A (ja) * 2003-09-26 2005-04-21 General Electric Co <Ge> ニッケル系ろう合金組成、その関連方法及び物品
JP2009222010A (ja) 2008-03-18 2009-10-01 Mitsubishi Heavy Ind Ltd ロケットノズル及びロケットエンジン燃焼ガス流れの制御方法
JP2013002444A (ja) * 2011-06-17 2013-01-07 General Electric Co <Ge> タービンエンジンのタービンノズルセグメントを補修する方法
JP2013029430A (ja) 2011-07-28 2013-02-07 Mitsubishi Electric Corp ２チャネル追尾装置、および追尾方法

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Title
See also references of EP2933440A4

Also Published As

Publication number Publication date
EP2933440A1 (en) 2015-10-21
JP6045389B2 (ja) 2016-12-14
CN104937220A (zh) 2015-09-23
RU2015128612A (ru) 2017-03-23
JP2014156851A (ja) 2014-08-28
EP2933440A4 (en) 2016-03-30
CN104937220B (zh) 2016-11-09
US20150354593A1 (en) 2015-12-10

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