EP2476864A1 - Disque aubagé d'une turbomachine et procédé de fabrication - Google Patents

Disque aubagé d'une turbomachine et procédé de fabrication Download PDF

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Publication number
EP2476864A1
EP2476864A1 EP11150851A EP11150851A EP2476864A1 EP 2476864 A1 EP2476864 A1 EP 2476864A1 EP 11150851 A EP11150851 A EP 11150851A EP 11150851 A EP11150851 A EP 11150851A EP 2476864 A1 EP2476864 A1 EP 2476864A1
Authority
EP
European Patent Office
Prior art keywords
blade
disc
weld
weld seam
disk
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.)
Withdrawn
Application number
EP11150851A
Other languages
German (de)
English (en)
Inventor
Karl-Hermann Richter
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.)
MTU Aero Engines AG
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
Priority to EP11150851A priority Critical patent/EP2476864A1/fr
Priority to US13/350,504 priority patent/US9284848B2/en
Publication of EP2476864A1 publication Critical patent/EP2476864A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • 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
    • F05D2230/233—Electron beam 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/234—Laser 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/236—Diffusion bonding
    • 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

Definitions

  • the present invention relates to a blade-disc unit for a turbomachine with a disc and a plurality of blades, which are materially connected to the disc.
  • blade-disc units which are also referred to as a so-called blisk, where blisk is an artificial word for the combination of blade and disk.
  • Such blade-disc units which constitute a rotor for a corresponding gas turbine or an aircraft engine, are characterized in that the blades are cohesively, for example by welding, arranged on the disc.
  • a direct welding of the blades with the disc is not possible there, as by welding a corresponding change or damage of the disc or blade material could occur, resulting in a not acceptable property profile.
  • melt-weldable nickel wrought alloys such as Inconel 718
  • the blade materials are formed from polycrystalline directionally solidified or single-crystalline nickel casting alloys having a high ⁇ 'content which provides the requisite strength to the blade material. By melting the blade material, this structure would be destroyed and affected accordingly the strength of the blade.
  • an adapter between the blade and disc is provided in the prior art, wherein the adapter is connected by friction welding to the blade and then the adapter is arranged by a fusion welding to the disc.
  • this is very complicated by the additional use of the adapter and the necessary additional welding operations.
  • the invention is based on the idea that a cohesive connection between the disk and the blade can also be achieved if one of the connection partners, ie either disk or blade, is not melted and only a melting of the other connection partner, ie according to the blade or disk , in which a solder joint can be formed by the molten material in the connection region and / or the energy introduced by the melting is sufficient to form, for example, a diffusion connection in the connection region of blade and disk.
  • the invention provides a weld spaced from the actual connection surface or directly to the connection surface, but only in the range of one of the connection partners provide while the other connection partners, so either disc or blade, are not melted.
  • the weld is understood in the sense that an area of one of the components to be joined is melted, so that there is a molten area.
  • welding seam is not to be understood as meaning that there is a fusion-technical mixing of materials of the components to be joined.
  • the blade is not melted, but only by molten material of the connection partner, so in aircraft engines z.
  • the disc is connected via a solder connection or via the heat provided in the melting area via a diffusion connection.
  • the weld can be introduced into either the disk or the blade, in particular at a distance of 0 to 3 mm, preferably 0 to 2.5 mm from the actual connection surface, that is, for example, the abutment surface of the components to be joined, wherein the weld itself has a thickness of 2 to 100 mm, in particular 5 to 75 mm in the direction transverse to the butt joint may have.
  • the disc and the blade can form a butt joint with a centering lip, wherein the weld seam can be formed as an I-seam.
  • the weld seam can be introduced in particular so that an edge of the weld which delimits it is formed parallel to the butt joint or abutment surface.
  • the weld can therefore be slightly tilted according to the opening angle of the welding cone introduced into the material.
  • energy beam methods such as, for example, electron beam welding or laser beam welding, may be used as the welding method, although other suitable welding methods may also be used.
  • solder material can be inserted in the joining region, that is to say at the butt joint or the abutment surface between the pane to be joined and the blade, for example in the form of a solder foil of a metallic material, in particular nickel or a nickel alloy, which is heated by the adjacent melting region (Weld) also melts and provides a solder joint.
  • FIG. 1 a Blisk invention is shown in partial perspective view.
  • the FIG. 1 Blisk shown comprises a disc 1, on which a plurality of blades 2 are arranged or can be arranged.
  • the blades 2 have on one side a shroud 4 and on the opposite side a blade root 3, with which they are connected to the disc 1.
  • a plurality of grooves 5 are formed along the circumference of the cylinder jacket surface of the disc 1, in which the Schaufelfiiße 3 of the blades 2 are inserted.
  • FIG. 1 further shows where in the embodiment shown the FIG. 1 the weld is provided to produce by a melting of the disc material a cohesive connection between blades and disc.
  • the weld 6 is at a certain distance d from the surface of the disc 2 and the abutting surface between the disc 1 and blades 2.
  • On the disc 1 grooves 5 are formed, which serve to accommodate the blade root 3.
  • the melting of the disc material in the region of the weld seam 6 also causes heating in the connection region between the blade root 3 and the boundary material of the disc 1 in the grooves 5, so that a corresponding cohesive connection is formed there. If there is an inflow of the molten disc material in the connecting region between the disc 1 and blade 2 so a solder joint is formed, in which molten disc material serves as a solder material for connection to the blade root.
  • the weld seam 6, ie the molten area can reach as close as possible to the blade root 3 as long as the blade material is not melted or damaged in any other way due to excessive heat input.
  • the molten region that is, the weld 6 can also be introduced at a distance d from the actual abutment surface against which the blade root 3 and the disc abut one another, so that only the disc material heated thereby at the impact surface between the blade root 3 and disc 1 ensures a material connection.
  • the joint on which the disk 1 and the blade 2 are connected to one another can be designed essentially as a butt joint, wherein a so-called 1-seam with a centering lip 8 can be formed on the stump joint.
  • the thickness of the blade 2 is slightly larger than the thickness D of the disc 1, so that in the region of the centering lip 8, the blade protrudes beyond the disc 1 and forms a contact shoulder.
  • the attachment of the weld 6 is selected in the disc 1 in the embodiment shown for a turbine blisk in aircraft engine construction, since the disc material is usually a melt-weldable nickel wrought alloy, such as Inconel 718, while it is in the blade material to polycrystalline, directionally solidified or monocrystalline casting alloys, which are usually not melt-weldable due to their high ⁇ '-share, otherwise cracks may arise and beyond their strength-enhancing ⁇ '-structure is destroyed.
  • the weld 6 can be introduced by appropriate energy beams, such as electron beams or laser beams, although other suitable welding methods can be used.
  • the shape of the weld seam 6, that is to say of the molten area, is generally conical in cross-section, that is to say with flanks converging toward or apart from one another, which delimit the weld seam 6.
  • the weld 6 is introduced so that the flank, so the edge region of the weld 6, which is adjacent to the connection region, ie in the present case adjacent to the blade 2, as parallel as possible to the butt joint or the impact surface formed thereby extends to prevent in that due to the conical configuration over the cross-section of the material-locking connection, different connection conditions exist due to the different distance between the melted area and the component to be connected.
  • the thickness D of the disc material can in this case be selected so that welding defects caused, for example, by a "nail head" in the region of the jet entrance are in the allowance a 1 , while welding defects which lie in the region of the weld root are are in a measure a 2 , so that overall no impairment of the required strength values for the disc 1 is to be feared.
  • the distance d of the weld 6 from the butt joint 7 can be chosen to be different, depending on the material combinations used for the disc 1 and the blade. 2
  • solder material for example in the form of a solder foil of a metallic material, such as, in particular, nickel or a nickel alloy, which melts upon introduction of the radiant energy to produce the weld 6 and forms a corresponding solder joint, can be arranged.
  • the integral connection is effected by diffusion bonding directly at the butt joint.
  • additional energy beams can be used parallel to the electron or laser beam 9, which are directed directly to the region of the butt joint 7 and provide additional heating there, but without melting the material and in particular the material To guide blade material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
EP11150851A 2011-01-13 2011-01-13 Disque aubagé d'une turbomachine et procédé de fabrication Withdrawn EP2476864A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11150851A EP2476864A1 (fr) 2011-01-13 2011-01-13 Disque aubagé d'une turbomachine et procédé de fabrication
US13/350,504 US9284848B2 (en) 2011-01-13 2012-01-13 Method for integrally connecting blades and disks in order to form a blade-disk unit, as well as correspondingly produced blade-disk unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11150851A EP2476864A1 (fr) 2011-01-13 2011-01-13 Disque aubagé d'une turbomachine et procédé de fabrication

Publications (1)

Publication Number Publication Date
EP2476864A1 true EP2476864A1 (fr) 2012-07-18

Family

ID=44065239

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11150851A Withdrawn EP2476864A1 (fr) 2011-01-13 2011-01-13 Disque aubagé d'une turbomachine et procédé de fabrication

Country Status (2)

Country Link
US (1) US9284848B2 (fr)
EP (1) EP2476864A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10668547B2 (en) 2017-05-09 2020-06-02 Gebrueder Busatis Gesellschaft M.B.H. Saw blade for a saw cutting stalk crops
US11058061B2 (en) 2016-10-28 2021-07-13 Gebrueder Busatis Gesellschaft M.B.H. Transport and processing roller for a harvester
CN115319419A (zh) * 2022-08-22 2022-11-11 昆山西诺巴精密模具有限公司 一种钛合金材质整体叶盘的加工方法及其应用

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014158598A1 (fr) * 2013-03-14 2014-10-02 United Technologies Corporation Ensemble rotor de turbine à liaison de phase liquide transitoire
FR3014477B1 (fr) * 2013-12-06 2016-01-08 Turbomeca Rotor a aubes

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE215126C (fr) *
US2380276A (en) * 1944-01-03 1945-07-10 Gen Electric Welded structure
GB614547A (en) * 1945-09-19 1948-12-17 Svenska Turbinfab Ab Improvements in axial flow elastic fluid turbines or compressors
US2709568A (en) * 1948-05-26 1955-05-31 United Aircraft Corp Welded turbine disc with blades
DE1808069A1 (de) * 1968-11-09 1970-08-06 Motoren Turbinen Union Laufrad mit gekuehlten oder ungekuehlten Laufschaufeln
DE2428826A1 (de) * 1973-06-18 1975-01-09 Hitachi Ltd Verfahren zum verschweissen ungleicher metalle
DE2510286A1 (de) * 1975-03-08 1976-09-16 Motoren Turbinen Union Schaufel-/scheibenverbindung fuer stroemungsmaschinen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3794807A (en) * 1972-04-10 1974-02-26 Gen Electric Method of beam welding dissimilar metal parts
JPS55147495A (en) * 1979-05-09 1980-11-17 Hitachi Ltd Butt welding method
FR2732630B1 (fr) * 1995-04-04 1997-06-20 Lorraine Laminage Procede de soudage bord a bord de deux flans metalliques
FR2742368B1 (fr) * 1995-12-18 1998-03-06 Framatome Sa Procede de raccordement par soudage heterogene bout a bout de deux pieces de natures differentes et utilisations
DE102004032975A1 (de) * 2004-07-08 2006-02-09 Mtu Aero Engines Gmbh Verfahren zum Verbinden von Schaufelblättern mit Schaufelfüßen oder Rotorscheiben bei der Herstellung und/oder Reparatur von Gasturbinenschaufeln oder integral beschaufelten Gasturbinenrotoren
DE102005006047A1 (de) * 2005-02-10 2006-09-07 Mtu Aero Engines Gmbh Verfahren zur Herstellung und/oder Reparatur eines integral beschaufelten Rotors
US20070189894A1 (en) * 2006-02-15 2007-08-16 Thamboo Samuel V Methods and apparatus for turbine engine rotors

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE215126C (fr) *
US2380276A (en) * 1944-01-03 1945-07-10 Gen Electric Welded structure
GB614547A (en) * 1945-09-19 1948-12-17 Svenska Turbinfab Ab Improvements in axial flow elastic fluid turbines or compressors
US2709568A (en) * 1948-05-26 1955-05-31 United Aircraft Corp Welded turbine disc with blades
DE1808069A1 (de) * 1968-11-09 1970-08-06 Motoren Turbinen Union Laufrad mit gekuehlten oder ungekuehlten Laufschaufeln
DE2428826A1 (de) * 1973-06-18 1975-01-09 Hitachi Ltd Verfahren zum verschweissen ungleicher metalle
DE2510286A1 (de) * 1975-03-08 1976-09-16 Motoren Turbinen Union Schaufel-/scheibenverbindung fuer stroemungsmaschinen

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11058061B2 (en) 2016-10-28 2021-07-13 Gebrueder Busatis Gesellschaft M.B.H. Transport and processing roller for a harvester
US10668547B2 (en) 2017-05-09 2020-06-02 Gebrueder Busatis Gesellschaft M.B.H. Saw blade for a saw cutting stalk crops
CN115319419A (zh) * 2022-08-22 2022-11-11 昆山西诺巴精密模具有限公司 一种钛合金材质整体叶盘的加工方法及其应用

Also Published As

Publication number Publication date
US20120183404A1 (en) 2012-07-19
US9284848B2 (en) 2016-03-15

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