WO2010003404A2 - Procédé de fabrication de rotors de turbine à gaz à aubage intégral - Google Patents

Procédé de fabrication de rotors de turbine à gaz à aubage intégral Download PDF

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Publication number
WO2010003404A2
WO2010003404A2 PCT/DE2009/000959 DE2009000959W WO2010003404A2 WO 2010003404 A2 WO2010003404 A2 WO 2010003404A2 DE 2009000959 W DE2009000959 W DE 2009000959W WO 2010003404 A2 WO2010003404 A2 WO 2010003404A2
Authority
WO
WIPO (PCT)
Prior art keywords
blade ring
plastic
rotor
blade
ring
Prior art date
Application number
PCT/DE2009/000959
Other languages
German (de)
English (en)
Other versions
WO2010003404A3 (fr
Inventor
Ulrich Knott
Thomas Uihlein
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2010003404A2 publication Critical patent/WO2010003404A2/fr
Publication of WO2010003404A3 publication Critical patent/WO2010003404A3/fr

Links

Classifications

    • 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
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B23K20/129—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding specially adapted for particular articles or workpieces
    • 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
    • B23K20/24—Preliminary treatment
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05B2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05B2230/239—Inertia or friction welding

Definitions

  • the invention relates to a method for manufacturing integrally bladed gas turbine rotors.
  • Modern gas turbines in particular aircraft engines, must meet the highest demands in terms of reliability, weight, performance, economy and service life.
  • aircraft engines have been developed, particularly in the civil sector, which fully meet the above requirements and have achieved a high degree of technical perfection.
  • the most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys and high-strength steels.
  • the high strength steels are used for shaft parts, gear parts, compressor casings and turbine casings.
  • Titanium alloys are typical materials for compressor parts.
  • Nickel alloys are suitable for the hot parts of the aircraft engine.
  • gas turbine components made of titanium alloys nickel alloy or other alloys are known from the prior art primarily investment casting and forging. All highly stressed gas turbine components, such as the blades for a compressor, are forgings. Blades and vanes of the turbine, however, are usually designed as precision castings.
  • Integrally bladed rotors are also referred to as blisk (bladed disk) or bling (bladed ring), depending on whether there is a disk-shaped rotor body or a ring-shaped rotor body.
  • Gas turbine rotors are known in which a blade ring from several guide is finely connected to a rotor body by the fact that the blade ring is connected to a material at least in sections, so as to fix the blade ring when connecting to the rotor body to the material. After bonding the blade ring to the rotor body by friction welding, the material is removed from the blade ring.
  • the present invention is based on the problem of proposing a novel method for producing integrally bladed gas turbine rotors.
  • this problem is solved by a method for manufacturing integrally bladed gas turbine rotors according to claim 5. Thereafter, the blade ring is connected to a plastic, in such a way that at least one solid plastic molding is connected to the blade ring by gluing.
  • this problem is solved by a method for
  • this problem is solved by a method for. Manufacture of integrally bladed gas turbine rotors according to claim 12. Thereafter, the blade ring is connected to a plastic, in such a way that solid plastic granules are introduced into cavities of the blade ring, wherein subsequently the plastic granules are melted and connected to the blade ring.
  • All aspects of the present invention have in common that when connecting the blade ring with the material of the blade ring is not exposed to high temperatures. As a result, a negative effect on the material structure of the blade ring can be avoided. Furthermore, the invention is characterized in that the material can be removed easily without negative effects on the blade ring of the same.
  • the second and third aspect of the present invention according to which either at least one solid plastic molding or a metal foam is connected to the blade ring.
  • the connection of the or each plastic molding or metal foam with the blade ring the same is exposed to any heat load. It is also possible to remove the or each plastic molded part or the metal foam from the blade ring by simple means. Negative effects on the blade ring can be safely avoided.
  • the present invention relates to a method for producing integrally bladed gas turbine rotors, wherein for this purpose a blade ring of a plurality of blades is connected to a rotor base body by friction welding, in particular by linear friction welding.
  • this material is removed from the blade ring.
  • the blade ring is connected to a plastic, in such a way that liquid plastic is connected by injection molding with the blade ring.
  • liquid polystyrene is preferably injected by means of a plastic injection molding machine into cavities or spaces of the blade ring, wherein after curing of the liquid plastic, the blade ring can be fixed to the plastic for friction welding.
  • the removal of the polystyrene from the blade ring after it has been connected to the rotor base body is preferably carried out with the aid of liquid nitrogen using the so-called embrittlement effect.
  • the blade ring is connected to a plastic such that at least one solid plastic molding with the blade ring is connected by gluing. In this case, then the blade ring is not exposed to any thermal stress.
  • the blade ring can be fixed to the or each plastic molding.
  • the or each plastic molded piece is removable from the rotor base body in such a way that the adhesive, via which the or each plastic molded piece is connected to the rotor base body, is dissolved by means of a solvent.
  • the blade ring is connected to a metal foam, which is introduced into cavities or clearances of the blade ring, so as to fix the blade ring for friction welding to the metal foam.
  • the metal foam is thereby connected to the blade ring, that between the blade ring and the metal foam in advance a release agent is positioned, which prevents a cohesive connection of the metal foam with the blade ring.
  • the release agent is applied to the blade ring, then the metal foam is connected to the blade ring in the region of the release agent.
  • the removal of the metal foam from the blade ring after connecting the same with the rotor base body also takes place via the release agent.
  • release agents suitable waxes are used.
  • the blade ring is connected to a plastic in that a solid plastic granules is introduced into cavities or spaces of the blade ring, and then the plastic granules are melted and connected to the blade ring.
  • Removal of the plastic after connecting the blade ring with the rotor body is preferably carried out by chemical, mechanical or thermal means.
  • the invention allows a rotor blade assembly of a plurality of rotor blades to be connected to a rotor body for manufacturing integrally bladed gas turbine rotors without adverse effects on the rotor blade ring.

Abstract

La présente invention concerne un procédé de fabrication de rotors de turbine à gaz à aubage intégral. Une couronne d'aubes mobiles composée de plusieurs aubes mobiles est reliée à un corps de base du rotor de manière qu'une matière première soit reliée à la couronne d'aubes mobiles afin de fixer cette dernière à la matière première par soudage par friction lors de la liaison de la couronne d'aubes mobiles au corps de base du rotor. Une fois la couronne d'aubes mobiles reliée au corps de base du rotor, la matière première est retirée de la couronne d'aubes mobiles. Selon l'invention, la couronne d'aubes mobiles est reliée à une matière plastique, plus précisément une matière plastique fluide est reliée à la couronne d'aubes mobiles par moulage par injection. En variante, la couronne d'aubes mobiles est reliée à une matière plastique, plus précisément au moins une pièce moulée solide en matière plastique est reliée à la couronne d'aubes mobiles par collage. En variante, la couronne d'aubes mobiles est reliée à une mousse métallique, plus précisément un élément de séparation est placé entre la mousse métallique et la couronne d'aubes mobiles, lequel élément de séparation empêche un assemblage par liaison de matière entre la mousse métallique et la couronne d'aubes mobiles. En variante, la couronne d'aubes mobiles est reliée à une matière plastique, plus précisément des granulés solides de matière plastique sont introduits dans des cavités de la couronne d'aubes mobiles, lesquels granulés de matière plastique sont ensuite fondus et reliés à la couronne d'aubes mobiles.
PCT/DE2009/000959 2008-07-11 2009-07-09 Procédé de fabrication de rotors de turbine à gaz à aubage intégral WO2010003404A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008032726A DE102008032726A1 (de) 2008-07-11 2008-07-11 Verfahren zum Herstellen von integral beschaufelten Gasturbinenrotoren
DE102008032726.3 2008-07-11

Publications (2)

Publication Number Publication Date
WO2010003404A2 true WO2010003404A2 (fr) 2010-01-14
WO2010003404A3 WO2010003404A3 (fr) 2010-03-18

Family

ID=41226781

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2009/000959 WO2010003404A2 (fr) 2008-07-11 2009-07-09 Procédé de fabrication de rotors de turbine à gaz à aubage intégral

Country Status (2)

Country Link
DE (1) DE102008032726A1 (fr)
WO (1) WO2010003404A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2456142C2 (ru) * 2010-09-13 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением деталей из титановых сплавов
RU2456141C2 (ru) * 2010-06-18 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением деталей из титановых сплавов
RU2456143C2 (ru) * 2010-06-18 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением заготовок из титановых сплавов для моноблоков турбомашин
CN111037235A (zh) * 2019-12-31 2020-04-21 安徽亘浩机械设备制造有限公司 风机防护圈快速制备方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108274109A (zh) * 2018-04-18 2018-07-13 北京世佳博科技发展有限公司 一种用于散热器类产品的复合连接方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19858702A1 (de) * 1998-12-18 2000-06-29 Mtu Muenchen Gmbh Schaufel und Rotor für eine Gasturbine und Verfahren zum Verbinden von Schaufelteilen
US20080016688A1 (en) * 2006-07-19 2008-01-24 Snecma Process for manufacturing a blisk and mold for implementing the process

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19858702A1 (de) * 1998-12-18 2000-06-29 Mtu Muenchen Gmbh Schaufel und Rotor für eine Gasturbine und Verfahren zum Verbinden von Schaufelteilen
US20080016688A1 (en) * 2006-07-19 2008-01-24 Snecma Process for manufacturing a blisk and mold for implementing the process

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2456141C2 (ru) * 2010-06-18 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением деталей из титановых сплавов
RU2456143C2 (ru) * 2010-06-18 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением заготовок из титановых сплавов для моноблоков турбомашин
RU2456142C2 (ru) * 2010-09-13 2012-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ линейной сварки трением деталей из титановых сплавов
CN111037235A (zh) * 2019-12-31 2020-04-21 安徽亘浩机械设备制造有限公司 风机防护圈快速制备方法

Also Published As

Publication number Publication date
WO2010003404A3 (fr) 2010-03-18
DE102008032726A1 (de) 2010-01-14

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