WO2007095902A1 - Procédé de fabrication et de réparation d'un rotor à aubage intégral - Google Patents

Procédé de fabrication et de réparation d'un rotor à aubage intégral Download PDF

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Publication number
WO2007095902A1
WO2007095902A1 PCT/DE2007/000282 DE2007000282W WO2007095902A1 WO 2007095902 A1 WO2007095902 A1 WO 2007095902A1 DE 2007000282 W DE2007000282 W DE 2007000282W WO 2007095902 A1 WO2007095902 A1 WO 2007095902A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
projection
stool
blade
integrally bladed
Prior art date
Application number
PCT/DE2007/000282
Other languages
German (de)
English (en)
Other versions
WO2007095902A8 (fr
Inventor
Reinhold Meier
Wilfried SCHÜTTE
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 WO2007095902A1 publication Critical patent/WO2007095902A1/fr
Publication of WO2007095902A8 publication Critical patent/WO2007095902A8/fr

Links

Classifications

    • 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
    • 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
    • B23K13/00—Welding by high-frequency current heating
    • B23K13/01—Welding by high-frequency current heating by induction heating
    • B23K13/02—Seam 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
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • 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
    • 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
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a method for producing and / or repairing an integrally bladed rotor, in particular an integrally bladed gas turbine rotor.
  • titanium alloys 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 housing and turbine housing.
  • Titanium alloys are typical materials for compressor parts.
  • Nickel alloys are suitable for the hot turbine parts of the aircraft engine.
  • As a manufacturing method for gas turbine components made of titanium alloys, nickel alloy or other alloys are known from the prior art m primarily investment casting and forging. All highly stressed gas turbine components, such as the blades for a compressor, are forgings. Components for a turbine, however, m usually performed as precision castings.
  • Integrally bladed rotors are also referred to as blisk (b_laded disk) or blmg (bled ring), depending on whether there is a disk-shaped rotor body or a ring-shaped rotor body. All previously known from the prior art method for the production of integrally bladed rotors require a high production cost and are therefore expensive. Furthermore, the repair of integrally bladed rotors presents difficulties.
  • the present invention is based on the problem to provide a novel method for producing and / or repairing an integrally bladed rotor. This problem is solved by a method for manufacturing and / or repairing an integrally bladed rotor according to claim 1.
  • the method comprises at least the following steps: a) providing a Rotorgroundkorpers, wherein the Rotorgroundkorper has at least one stool-like projection for the connection of a respective blade to the Rotorgroundkorper; b) providing at least one rotor blade, wherein the or each Laufs ⁇ haufel has a stool-like projection for connecting the same to a stool-like projection of the Rotorgroundkorpers; c) jointing the or each blade to the Rotorgroundkorper by inductive high frequency pressure welding, wherein the or each rotor blade is connected at its stool-like projection with a stool-like projection of the Rotorgroundkorpers; d) contouring of the or each of the Rotorgroundkorper grooved Laufschaufei.
  • the present invention proposes a sequence of process steps for producing and / or repairing an integrally bladed rotor, which is equally suitable for the manufacture and repair of integrally bladed rotors and which furthermore has high reproducibility.
  • the steps used for producing and / or repairing integrally bladed rotors in combination, in particular inductive high-frequency pressure welding, are highly automatable process steps, so that integrally bladed rotors can be manufactured and repaired effectively and inexpensively.
  • a heat treatment of the or each Fugestelle, namely the or each weld in particular in a repair of an integrally bladed rotor after the joints in step c) and prior to contouring according to step d) performed.
  • Fig. 1 is a schematic representation of an integrally bladed rotor
  • FIG. 2 is a schematic axial section through a stool-like projection of Rotorcampuskorper or Laufschaufei.
  • Figure 3 is a schematic radial section through the stool-like projection of Rotorgroundkorper or blade before the joints.
  • Fig. 4 is a schematic radial section through the hump-like projection of the rotor body or rotor blade after joining.
  • FIG. 1 shows in a highly schematic perspective view an integrally bladed gas turbine rotor 10 to be produced or repaired with the aid of the method according to the invention, the integrally bladed gas turbine rotor 10 having a rotor main body 11 and a plurality of rotor blades 12.
  • the blades 12 are permanently attached to an outer hub 13 of the rotor base body 11 and therefore an integral part thereof.
  • the rotor blades 12 are arranged equidistantly or equidistant from each other over the circumference of the rotor base body 11 or its hub 13.
  • the present invention now relates to a method for producing and repairing the integrally bladed gas turbine rotor 10 shown in FIG.
  • the procedure is such that a preferably forged rotor base body 11 is first provided.
  • the forged rotor base body 11 has hump-like projections for connecting a respective rotor blade to the rotor base body 11, wherein the number of hump-like projections corresponds to the number of blades to be connected.
  • such a hump-like projection 14 for connecting a rotor blade 12 is located at a circumferential position. At the other circumferential positions, corresponding rotor blades 12 are already joined to hump-like projections 14.
  • At least one preferably forged rotor blade 12 is further provided, wherein the or each forged blade 12 also has a hump-like projection 15 for connecting the same to a hump-like projection 14 of the rotor base body 11.
  • a blade 12 are added with their hump-like projection 15 to a corresponding hump-like projection 14 of the rotor body 11, so the corresponding blade 12 is first aligned relative to the rotor body 11 (see Fig. 3), in which case the two stool-like protrusions 14 and 15 of blade 12 and rotor main body 11 come to rest against each other, and then wherein the blade 12 is connected to the Rotorgroundkorper 11 by inductive high frequency pressure welding to form a weld zone 16.
  • the stool-like projection 14 of the rotor base body 11 and the stool-like projection 15 of the rotor blade 12 to be bonded to the rotor base body 11 have a uniform profile thickness (see FIG. 2), so that can be ensured over the entire profile of the blade 12 a good weld to Rotorgroundkorper 11. If one works with such uniform profile thicknesses of the stool-like projections 14, 15 of rotor blade 12 and rotor base body 11, an optimum selection of the welding parameters of the inductive high-frequency pressure welding is possible.
  • the inductive high frequency pressure welding works with low compression forces, so that the forged Rotorgroundkorper 11 is preferably provided with a final contour.
  • a final contour machining or of each rotor blade 12 attached to the rotor body 11 is preferably carried out by PECM, ie by Precise Elektro Chemical Machimng.
  • PECM material is removed from the rotor blades 12 by means of electrodes, with the geometric contour of the electrodes used corresponding to the geometric contour to be produced. This blade edge contours can be produced with high accuracy, so that post-processing after the PECM is not required.
  • the final contour machining of the blades can take place over the entire radial extension of the same between a radially outer blade tip and a radially inner Anbmdungs Suite same to the Rotorgroundkorper 11 and over the entire axial extent Endkontearbeitearbeitung between a flow inlet edge and a flow exit edge.
  • 2 and 4 show dashed lines in the final contour machining to be produced desired contours 17th
  • the stool-like projections 14 and 15 in the region of the rotor base body 11 and of the rotor blades 12 ensure a constructive decoupling of the rotor base body 11 and the blade of the rotor blades 12.
  • the stool-like projections 14, 15 can between the Ro- torgroundkorper 11 and the blade 12 a targeted transition ms aerodynamic profile of the blade of the blades are provided.
  • the stool-like projections 14, 15 with their gleichrichigen profile thickness continue to allow the inductive high frequency pressure welding, the formation of high-precision weld, so that the connection between Rotorgrundkorper 11 and blades 12 is characterized by a high strength. In case of repair, repeated blade changes are possible.
  • a heat treatment of the weld takes place after the joint has been formed by inductive high-frequency compression welding and before the PECM machining of the rotor blades.
  • the inventive method enables economical production and repair of integrally bladed rotors, wherein the forging processes for Rotorgroundkorper and the blades are optimally matched to the desired component strength of these components.
  • the inventive method is safe, easy to test and well reproducible.
  • the blades can be forged from a different material as the Rotorgroundskorper.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Procédé de fabrication et/ou de réparation d'un rotor à aubage intégral (10) consistant au moins à a) mettre en oeuvre un corps de base de rotor présentant au moins une saillie (11) de type bosse (14) destinée à la fixation d'une aube (12) respective au corps de base de rotor; b) à mettre en oeuvre au moins une aube présentant une saillie de type bosse (15) destinée à la fixation à une saillie de type bosse du corps de base de rotor; c) à assembler les aubes au corps de base de rotor par soudage par compression haute fréquence inductif, les aubes étant assemblées sur leur saillie de type bosse à une saillie de type bosse du corps de base de rotor; et d) à usiner les contours des aubes assemblées au corps de base de rotor.
PCT/DE2007/000282 2006-02-25 2007-02-15 Procédé de fabrication et de réparation d'un rotor à aubage intégral WO2007095902A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006008836A DE102006008836A1 (de) 2006-02-25 2006-02-25 Verfahren zur Herstellung und/oder Reparatur eines integral beschaufelten Rotors
DE102006008836.0 2006-02-25

Publications (2)

Publication Number Publication Date
WO2007095902A1 true WO2007095902A1 (fr) 2007-08-30
WO2007095902A8 WO2007095902A8 (fr) 2007-10-25

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Application Number Title Priority Date Filing Date
PCT/DE2007/000282 WO2007095902A1 (fr) 2006-02-25 2007-02-15 Procédé de fabrication et de réparation d'un rotor à aubage intégral

Country Status (2)

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DE (1) DE102006008836A1 (fr)
WO (1) WO2007095902A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009080013A1 (fr) * 2007-12-22 2009-07-02 Mtu Aero Engines Gmbh Procédé de production et de réparation d'un composant d'une turbine à gaz
DE102009033835A1 (de) * 2009-07-18 2011-01-20 Mtu Aero Engines Gmbh Verfahren zum Austauschen einer Schaufel eines Rotors mit integrierter Beschaufelung und ein derartiger Rotor
DE102009043184A1 (de) * 2009-09-26 2011-04-07 Mtu Aero Engines Gmbh Verfahren zur Reparatur eines integralen Rotors und integraler Rotor
EP2957719A1 (fr) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Unité de rotor pour turbomachine et procédé de construction de celui-ci
EP4183977A1 (fr) * 2021-11-18 2023-05-24 General Electric Company Appareil et procédés d'assemblage de profil aérodynamique

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009016799A1 (de) * 2009-04-07 2010-10-14 Mtu Aero Engines Gmbh Verfahren zum Verschweißen zweier Bauteile
DE102011011495B4 (de) * 2011-02-17 2013-05-08 Lufthansa Technik Ag Vorrichtung zum Reparieren von Gasturbinenschaufeln

Citations (10)

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Publication number Priority date Publication date Assignee Title
US4012616A (en) * 1975-01-02 1977-03-15 General Electric Company Method for metal bonding
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
US5511949A (en) * 1993-01-06 1996-04-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method for producing a monobloc rotor with hollow blades and monobloc rotor with hollow blades obtained by said method
EP0841470A2 (fr) * 1996-11-12 1998-05-13 United Technologies Corporation Méthode de connexion d'une aube à un rotor intégral
WO2000037210A1 (fr) * 1998-12-18 2000-06-29 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Pale et rotor pour turbine a gaz et procede pour relier des parties de pale
DE19922012C1 (de) * 1999-05-12 2000-10-19 Mtu Muenchen Gmbh Verfahren zur Fertigung angepaßter, strömungstechnischer Oberflächen
DE10343760A1 (de) * 2003-09-22 2005-04-14 Mtu Aero Engines Gmbh Verfahren zur Herstellung oder Reparatur eines beschaufelten Rotors für eine Strömungsmaschine sowie dafür geeignete Schaufeln bzw. Ersatzschaufelabschnitte
WO2006005296A1 (fr) * 2004-07-08 2006-01-19 Mtu Aero Engines Gmbh Procede de liaison d'aubes a des emplantures ou a des disques de rotor lors de la fabrication et / ou de la reparation d'aubes de turbines a gaz ou de rotors de turbines a gaz a aubes constituees d'un seul tenant avec le rotor
WO2006026962A1 (fr) * 2004-09-10 2006-03-16 Mtu Aero Engines Gmbh Procede pour realiser un rotor de turbine a gaz a aubes creuses integrees
WO2006084439A1 (fr) * 2005-02-10 2006-08-17 Mtu Aero Engines Gmbh Procede pour produire et/ou reparer un rotor a aubage integre par soudage par diffusion par induction

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012616A (en) * 1975-01-02 1977-03-15 General Electric Company Method for metal bonding
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
US5511949A (en) * 1993-01-06 1996-04-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method for producing a monobloc rotor with hollow blades and monobloc rotor with hollow blades obtained by said method
EP0841470A2 (fr) * 1996-11-12 1998-05-13 United Technologies Corporation Méthode de connexion d'une aube à un rotor intégral
WO2000037210A1 (fr) * 1998-12-18 2000-06-29 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Pale et rotor pour turbine a gaz et procede pour relier des parties de pale
DE19922012C1 (de) * 1999-05-12 2000-10-19 Mtu Muenchen Gmbh Verfahren zur Fertigung angepaßter, strömungstechnischer Oberflächen
DE10343760A1 (de) * 2003-09-22 2005-04-14 Mtu Aero Engines Gmbh Verfahren zur Herstellung oder Reparatur eines beschaufelten Rotors für eine Strömungsmaschine sowie dafür geeignete Schaufeln bzw. Ersatzschaufelabschnitte
WO2006005296A1 (fr) * 2004-07-08 2006-01-19 Mtu Aero Engines Gmbh Procede de liaison d'aubes a des emplantures ou a des disques de rotor lors de la fabrication et / ou de la reparation d'aubes de turbines a gaz ou de rotors de turbines a gaz a aubes constituees d'un seul tenant avec le rotor
WO2006026962A1 (fr) * 2004-09-10 2006-03-16 Mtu Aero Engines Gmbh Procede pour realiser un rotor de turbine a gaz a aubes creuses integrees
WO2006084439A1 (fr) * 2005-02-10 2006-08-17 Mtu Aero Engines Gmbh Procede pour produire et/ou reparer un rotor a aubage integre par soudage par diffusion par induction

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009080013A1 (fr) * 2007-12-22 2009-07-02 Mtu Aero Engines Gmbh Procédé de production et de réparation d'un composant d'une turbine à gaz
US9333576B2 (en) 2007-12-22 2016-05-10 MTU Aero Engines AG Method for producing and repairing a part, and part of a gas turbine
DE102009033835A1 (de) * 2009-07-18 2011-01-20 Mtu Aero Engines Gmbh Verfahren zum Austauschen einer Schaufel eines Rotors mit integrierter Beschaufelung und ein derartiger Rotor
DE102009033835B4 (de) * 2009-07-18 2012-01-19 Mtu Aero Engines Gmbh Verfahren zum Austauschen einer Schaufel eines Rotors mit integrierter Beschaufelung und ein derartiger Rotor
US9138834B2 (en) 2009-07-18 2015-09-22 Mtu Aero Engines Gmbh Method for replacing a blade of a rotor having integrated blades and such a rotor
DE102009043184A1 (de) * 2009-09-26 2011-04-07 Mtu Aero Engines Gmbh Verfahren zur Reparatur eines integralen Rotors und integraler Rotor
EP2957719A1 (fr) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Unité de rotor pour turbomachine et procédé de construction de celui-ci
EP4183977A1 (fr) * 2021-11-18 2023-05-24 General Electric Company Appareil et procédés d'assemblage de profil aérodynamique
US11828190B2 (en) 2021-11-18 2023-11-28 General Electric Company Airfoil joining apparatus and methods

Also Published As

Publication number Publication date
WO2007095902A8 (fr) 2007-10-25
DE102006008836A1 (de) 2007-09-06

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