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WO2008077374A1 - Procédé de fabrication d'un blisk ou d'un bling et composant ainsi fabriqué - Google Patents

Procédé de fabrication d'un blisk ou d'un bling et composant ainsi fabriqué Download PDF

Info

Publication number
WO2008077374A1
WO2008077374A1 PCT/DE2007/002245 DE2007002245W WO2008077374A1 WO 2008077374 A1 WO2008077374 A1 WO 2008077374A1 DE 2007002245 W DE2007002245 W DE 2007002245W WO 2008077374 A1 WO2008077374 A1 WO 2008077374A1
Authority
WO
WIPO (PCT)
Prior art keywords
ring
rotor
blade
blade ring
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.)
Ceased
Application number
PCT/DE2007/002245
Other languages
German (de)
English (en)
Inventor
Ulrich Knott
Albin Platz
Karl-Hermann Richter
Dieter Schneefeld
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
Publication of WO2008077374A1 publication Critical patent/WO2008077374A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines

Definitions

  • the present invention relates to a method for producing a blisk ("bladed disk”) or a bling ("bladed ring") of a gas turbine or a high or low pressure compressor.
  • the invention further relates to a component produced by the method.
  • Bladed (Bladed Disk) and Bling (Bladed Ring) designate rotor designs where blades are made integral with a load bearing disk or bearing ring
  • the advantage of these rotor designs is that the disks or ring shape are designed for low edge loads
  • compacting blisks made of titanium or nickel-based alloys are produced, in particular by milling, and occasionally by linear friction welding or electrochemical ablation
  • the disc and blade materials basically have to be different from each other, which means that turbine blisks can only be realized by means of joint technology, bearing in mind, however, that joining methods, such as linear friction welding, are necessary Compressive forces are not or are poorly suited to produce such turbine blisks. The same applies to bling.
  • the known production methods can only be used to a limited extent if different structural designs of blisks or blings are required.
  • the known methods are sometimes very complex and go hand in hand with a corresponding high cost. It is therefore an object of the present invention to provide a generic method for producing a blisk ("bladed disk”) or a bling ("bladed ring”), which is used both in the production of a blisk or bling a gas turbine or a high or low pressure compressor can be and a variety of structural designs of these components allows.
  • a erf ⁇ ndungsconcees method for producing a blisk ("bladed disk”) or a bling ("bladed ring") of a gas turbine or a high or low pressure compressor comprises the following steps: a) producing an annular blade ring and b) connecting the annular blade ring with a rotor disk or a rotor ring, such that the blade ring is arranged on the outer circumference of the rotor disk or the rotor ring.
  • the inventive method can be used both in the production of blisks or blings for a gas turbine o- but also for a high or low pressure compressor.
  • the separate production of the blade ring and the subsequent connection of the blade ring with the rotor disk or the rotor ring also allows a variety of structural Ges- tions of these components. For example, cooling ducts that pass through both the blades and the disk in a turbine blisk to direct cooling air outwardly from the air system through the blades can be readily manufactured.
  • the blade ring is produced by joining individual blades or blade segments produced by casting. It is possible that an annular element is equipped with the individual blades or individual blade segments are joined to form an annular blade ring.
  • a joining method a high-temperature soldering or a diffusion soldering can be used. But it is also possible that the blade ring is made in one piece by means of a casting or milling process.
  • connection of the annular blade ring with the rotor disk and the rotor ring takes place by means of a joining process.
  • the joining process can be carried out by means of an electron beam welding method, a rotary friction welding method, a diffusion soldering method or a diffusion welding method.
  • Other suitable joining processes are conceivable. It has been found in the use of the electron beam welding process that the quality of the connection can be significantly improved if, for example, metallic intermediate layers are used on the surface to be joined. The metallic interlayers are used because the blade material is generally not melt weldable. But it is also possible that the electron beam is deflected offset in the direction of a melt-weldable disc material.
  • a suitable solder is applied to one of the surfaces to be joined (for example with solder foil or a physical vapor deposition method) and then introduced locally in a vacuum furnace or with a locally, for example, annular inductor, the required heat energy.
  • a rotary friction welding process as a joining process for connecting the blade ring with the rotor disk or the rotor ring, the joining surface between turbine ring and disc can be made conical.
  • the rotor disk or the rotor ring has an oversize in the axial direction and can subsequently tungsd be finished.
  • flywheel friction welding is used as the rotary friction welding method.
  • a corresponding joining device is to be selected which ensures that the joining components are pressed together at the corresponding diffusion welding temperature, so that an intimate connection is created between the blade ring and the rotor disk or the rotor ring.
  • the positioning of the blade ring on the rotor disk and the rotor ring by means of shrinking takes place.
  • the blade ring, the rotor disk and the rotor ring have the necessary radii.
  • the shrinkage ensures an intimate connection between the individual elements of the blisk or the bling.
  • recesses are formed in the rotor disk and the rotor ring after connecting the annular blade ring with the rotor disk or the rotor ring, wherein the recesses between each two adjacent individual blades or blade segments of the blade ring on the outer circumference of the rotor disk or the rotor ring encircling are arranged.
  • Such a configuration advantageously forms a shroud for shielding the rotor disk or the rotor ring.
  • the shroud consists of the ring element or annular region of the blade ring.
  • An inventive component of a gas turbine or a high or low pressure compressor in particular a blisk ("bladed disk”) or a bling ("bladed ring”) consists of a separately manufactured annular blade ring and a rotor disk or rotor ring connected thereto, wherein the Blade ring is arranged in the outer circumference of the rotor disk or the rotor ring. Due to the two-part design of the component according to the invention whose cost-effective production of a variety of different designs is guaranteed. In this case, the blade ring may consist of a multiplicity of individual blades or blade segments joined to one another in segments.
  • this has a shroud for shielding the rotor disk or the rotor ring.
  • the shroud serves in particular for shielding the hot gas in the gas turbine.
  • the shroud can be formed, for example, by an annular region of the blade ring, wherein after connecting the annular blade ring with the rotor disk or the rotor ring recesses in the rotor disk or the rotor ring are formed, wherein the recesses between each two adjacent individual blades of the blade ring on the outer circumference the rotor disk or rotor ring are arranged circumferentially.
  • the components according to the invention are produced by one of the methods described above.
  • FIG. 1 is a schematic representation of a blade ring as part of a component according to the invention.
  • Figure 2 is a schematic representation of an inventive joined component according to a first embodiment
  • Figure 3 is a schematic representation of an inventive joined component according to a second embodiment
  • Figure 4 is a schematic representation of an inventive joined component according to a third embodiment
  • FIG. 5 shows a schematic representation of a joining process for connecting an annular blade ring with a rotor disk for producing a component according to the invention according to a first embodiment
  • Figure 6 is a schematic representation of a joining process for connecting an annular blade ring with a rotor disk for producing a component according to the invention according to a second embodiment.
  • FIG. 1 shows a schematic representation of a blade ring 12 as part of a blisk or a bling.
  • the blade ring 12 consists of a plurality of individual blades 14, which are arranged annularly on the outer circumference of an annular element 26 of the blade ring 12.
  • the annular element 26 is formed in the illustrated embodiment by a plurality of curved blade base elements 28 which are joined together, wherein first joining seams or points 30 arise.
  • the blades 14 are arranged centrally on the outer surface of the respective blade base element 28.
  • a root section 22 of the blade 14 is formed in the blade base 28.
  • the illustrated blade ring 12 is thereby produced by a segment-wise joining of the individual blades 14 or the blade base elements 28. In particular, this is a Hochtemperaturlöthabilit or Diffusion soldering used. But it is also possible that corresponding blade rings are produced in one piece by means of a casting or milling process.
  • FIG. 2 shows a schematic representation of a joined component 10, namely a blisk for a gas turbine.
  • the blade ring 12 is connected to a rotor disk 16 such that the blade ring 12 comes to rest on the outer periphery 18 of the rotor disk 16.
  • the rotor disk 16 and the blade ring 12 are connected by means of a joining process.
  • the joining process may be an electron beam welding process, a spin welding process, a diffusion soldering process or a diffusion welding process.
  • FIG. 3 shows a schematic representation of a further embodiment of the component 10.
  • the component 10 is again designed as a blisk.
  • the blisk has a cover band 24 for shielding the rotor disk 16.
  • the shroud 24 is formed by the annular region 26 of the blade ring 12.
  • 16 recesses 20 are formed in the rotor disk 16 after connecting the annular blade ring 12 with the rotor disk, wherein the recesses 20 are arranged circumferentially between each two adjacent individual blades 14 of the blade ring 12 on the outer periphery 18 of the rotor disk 16.
  • the formation of the recesses 20 takes place by means of a precise electrochemical removal process and / or by spark erosion. Other erosive methods are conceivable.
  • FIG. 4 shows a schematic representation of a component 10 according to a third embodiment.
  • the component 10 is a blisk. It can be seen that this blisk has no shroud 24 in comparison to the blisk shown in FIG.
  • the illustrated component 10 after joining the annular blade ring 12 with the rotor disk 16 those portions of the blade ring 12, which lie between the individual blades 14 and blade segments removed, such that only each of the foot portion 22 of the corresponding blade 14 with the rotor disc 16 is connected.
  • Such a blisk has only the second joining seams 32.
  • the removal of the intermediate regions of the blade ring 12 can also take place by means of an electrochemical removal process and / or by spark erosion.
  • FIG. 5 shows a schematic representation of a joining process for connecting the annular blade ring 12 to the rotor disk 16 for producing a component 10, namely a blisk.
  • the illustrated joining process is a friction welding process, in particular a flywheel friction welding process. It can be seen that the joining surface between the blade ring 12 and the rotor disk 16 is conical. The same applies to the resulting second weld 32.
  • a disk axis 34 is also shown schematically in this figure.
  • a friction welding namely a Schwungradreibsch experience compiler. It can be seen that in this case too, a conical weld 32, in particular a friction weld seam 32, is formed when the blade ring 12 is connected to the rotor disk 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

La présente invention concerne un procédé de fabrication d'un blisk ('Bladed Disk'; ensemble aube et disque) ou d'un bling ('Bladed Ring'; ensemble aube et bague) d'une turbine à gaz ou d'un compresseur à haute ou basse pression, le procédé comprenant les étapes suivantes : (a) fabrication d'une couronne d'aubes de forme annulaire (12) ; et (b) raccordement de la couronne d'aubes de forme annulaire (12) à un disque de rotor (16) ou une bague de rotor, de telle sorte que la couronne d'aubes (12) soit agencée sur la périphérie extérieure (18) du disque de rotor (16) ou de la bague de rotor. L'invention concerne en outre un composant d'une turbine à gaz ou d'un compresseur à basse ou haute pression, en particulier un blisk ('Bladed Disk' ; ensemble aube et disque) ou un bling ('Bladed Ring' ; ensemble aube et bague). Selon l'invention, le composant (10) est constitué d'une couronne d'aubes de forme annulaire (12) fabriquée séparément et d'un disque de rotor (16) reliée à celle-ci ou d'une bague de rotor reliée à celle-ci, la couronne d'aubes (12) étant agencée sur la périphérie extérieure (18) du disque de rotor (16) ou de la bague de rotor.
PCT/DE2007/002245 2006-12-23 2007-12-12 Procédé de fabrication d'un blisk ou d'un bling et composant ainsi fabriqué Ceased WO2008077374A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006061448.8 2006-12-23
DE102006061448A DE102006061448B4 (de) 2006-12-23 2006-12-23 Verfahren zur Herstellung einer Blisk oder eines Blings einer Gasturbine und danach hergestelltes Bauteil

Publications (1)

Publication Number Publication Date
WO2008077374A1 true WO2008077374A1 (fr) 2008-07-03

Family

ID=39272959

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2007/002245 Ceased WO2008077374A1 (fr) 2006-12-23 2007-12-12 Procédé de fabrication d'un blisk ou d'un bling et composant ainsi fabriqué

Country Status (2)

Country Link
DE (1) DE102006061448B4 (fr)
WO (1) WO2008077374A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2653653A1 (fr) * 2007-03-07 2013-10-23 Honeywell International Inc. Rotors de turbine multi-alliage et procédés de fabrication des rotors

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010048732B3 (de) 2010-10-16 2012-03-15 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines integral beschaufelten Rotors
DE102018200832A1 (de) 2018-01-19 2019-07-25 MTU Aero Engines AG Rotor, insbesondere Blisk einer Gasturbine, mit aufgelöstem Rim und Verfahren zum Herstellen desselben

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2922619A (en) * 1954-03-15 1960-01-26 Chrysler Corp Turbine wheel assembly
GB2052645A (en) * 1979-06-06 1981-01-28 Gen Motors Corp Manufacture of composite turbine rotors
US20030223873A1 (en) * 2002-05-30 2003-12-04 Carrier Charles William Inertia welding of blades to rotors
EP1526252A2 (fr) * 2003-10-21 2005-04-27 General Electric Company Rotor de turbine de triple caractère et sa méthode de production

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1064399A (en) * 1964-12-30 1967-04-05 Rover Co Ltd Welded turbine or compressor rotor
US4096615A (en) * 1977-05-31 1978-06-27 General Motors Corporation Turbine rotor fabrication
US4152816A (en) * 1977-06-06 1979-05-08 General Motors Corporation Method of manufacturing a hybrid turbine rotor
GB2063721A (en) * 1979-11-23 1981-06-10 Gen Motors Corp Method of bonding composite turbine wheels
GB2109274A (en) * 1981-11-13 1983-06-02 Rolls Royce Gas turbine engine rotor assembly
GB2193125B (en) * 1986-08-01 1990-07-18 Rolls Royce Plc Gas turbine engine rotor assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2922619A (en) * 1954-03-15 1960-01-26 Chrysler Corp Turbine wheel assembly
GB2052645A (en) * 1979-06-06 1981-01-28 Gen Motors Corp Manufacture of composite turbine rotors
US20030223873A1 (en) * 2002-05-30 2003-12-04 Carrier Charles William Inertia welding of blades to rotors
EP1526252A2 (fr) * 2003-10-21 2005-04-27 General Electric Company Rotor de turbine de triple caractère et sa méthode de production

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2653653A1 (fr) * 2007-03-07 2013-10-23 Honeywell International Inc. Rotors de turbine multi-alliage et procédés de fabrication des rotors

Also Published As

Publication number Publication date
DE102006061448A1 (de) 2008-06-26
DE102006061448B4 (de) 2011-12-08

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