EP2097617A2 - Couronne d'aubes fixes et procédé de fabrication - Google Patents

Couronne d'aubes fixes et procédé de fabrication

Info

Publication number
EP2097617A2
EP2097617A2 EP07846376A EP07846376A EP2097617A2 EP 2097617 A2 EP2097617 A2 EP 2097617A2 EP 07846376 A EP07846376 A EP 07846376A EP 07846376 A EP07846376 A EP 07846376A EP 2097617 A2 EP2097617 A2 EP 2097617A2
Authority
EP
European Patent Office
Prior art keywords
vane
vanes
support ring
ring
vane support
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Withdrawn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
EP07846376A
Other languages
German (de)
English (en)
Inventor
Siegfried Sikorski
Max Kraus
Karl Hofmann
Alois NIEDERSÜSS
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 EP2097617A2 publication Critical patent/EP2097617A2/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • 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
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2230/238—Soldering
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • 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
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • Vane ring Vane ring and method for producing the same
  • the invention relates to a vane ring according to the preamble of claim 1. Furthermore, the invention relates to a method for producing a vane ring and a method for producing guide vanes for a vane ring.
  • the most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys (also called superalloys) 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 components for a compressor, are forgings. Components for a turbine, however, are usually designed as precision castings.
  • Powder metallurgical injection molding is an interesting alternative for the manufacture and production of complex components.
  • Powder metallurgical injection molding is related to plastic injection molding and is also referred to as metal mold injection or metal injection molding (MIM).
  • MIM metal injection or metal injection molding
  • Gas turbines have stator vane rings in the area of a compressor and in the area of a turbine, wherein a vane ring comprises a plurality of guide vanes which are fastened to a guide vane carrier ring.
  • the vanes are typically soldered to the vane support ring.
  • the guide vanes and the vane support ring are made of an identical material.
  • the present invention based on the problem to provide a novel vane ring and a method for producing the same.
  • the vane support ring and the vanes are made of different materials, the material of which the vanes are made being more valent than the material of which the vane support ring is made.
  • the guide blade carrier ring and the guide vanes are manufactured from different materials, wherein the material of the guide vanes is of higher quality than the material of the guide vane carrier ring. This makes it possible to provide a tailored to the thermal and mechanical requirements Leitschaufelkranz while optimizing the cost.
  • the vane support ring and the vanes are each made of a nickel-based alloy, wherein the nickel-based alloy from which the vanes are made is more heat-resistant than the nickel-base alloy from which the vane support ring is made.
  • the inventive method for producing a vane ring is defined in claim 5.
  • a method for manufacturing vanes for a vane ring is defined in claim 11.
  • FIG. 1 a plurality of jointly produced guide blade blanks; and FIG. 2 also shows a number of jointly manufactured guide blade blanks.
  • the present invention relates to a vane ring of a turbomachine, in particular of a gas turbine designed as an aircraft engine.
  • a vane ring has a plurality of vanes attached to a vane support ring.
  • the guide blade carrier ring and the guide vanes are manufactured from different materials.
  • the vane support ring is made of a first material
  • the vanes are made of a second material
  • the material from which the vanes are made is superior to the material from which the vane support ring is made.
  • a higher-grade material is to be understood in particular to mean that it has a higher heat resistance and is therefore more heat-resistant.
  • the vane support ring of the vane ring is made of the nickel-based alloy IN 718.
  • the vanes are made of a higher quality or higher heat resistant nickel base alloy, namely the nickel base alloy UDIMET 720.
  • the vanes are soldered to the vane support ring.
  • the procedure is such that the guide blade carrier ring is produced from the first material, in particular from the nickel-based alloy IN 718, in particular by forging.
  • the guide vanes are made of the second material, in particular of UDIMET 720, preferably by powder metallurgical injection molding.
  • FIGS. 1 and 2 each show such blanks 10, 11 produced by powder metallurgical injection molding from a plurality of guide blade blanks 12 and 13, respectively.
  • the guide blade blanks 13 in the blank 11 are stacked one above the other in the radial direction, so that adjacent guide blade blanks 13 are connected via webs 15 such that a guide blade tip of a guide blade blank 13 is connected to the guide blade root of the adjacent guide blade blank 13 via a web 15.
  • Powder metallurgy injection molding is also referred to as Metal Injection Molding (MIM).
  • MIM Metal Injection Molding
  • the vane blanks produced by powder metallurgy injection molding are made by milling or grinding or an electrochemical Machining (ECM) process edited.
  • ECM electrochemical Machining
  • the machining of the guide blade blanks preferably takes place by means of a Precise Electrochemical Machining (PECM) process.
  • vanes preferably made by a combined MIM process and PECM process, are inserted into and soldered to the vane support ring and then heat treated thereon to produce the vane ring so produced to provide optimum stator vane rigidity.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une couronne d'aubes fixes d'une turbomachine, notamment d'une turbine à gaz, comportant un anneau support d'aubes fixes et plusieurs aubes fixes fixées audit anneau support. Selon l'invention, la couronne d'aubes fixes et les aubes fixes sont réalisées en matériaux différents, le matériau constituant les aubes fixes étant de meilleure qualité que le matériau constituant l'anneau support d'aubes fixes.
EP07846376A 2006-12-08 2007-12-01 Couronne d'aubes fixes et procédé de fabrication Withdrawn EP2097617A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006057912A DE102006057912A1 (de) 2006-12-08 2006-12-08 Leitschaufelkranz sowie Verfahren zum Herstellen desselben
PCT/DE2007/002169 WO2008067796A2 (fr) 2006-12-08 2007-12-01 Couronne d'aubes fixes et procédé de fabrication

Publications (1)

Publication Number Publication Date
EP2097617A2 true EP2097617A2 (fr) 2009-09-09

Family

ID=39363169

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07846376A Withdrawn EP2097617A2 (fr) 2006-12-08 2007-12-01 Couronne d'aubes fixes et procédé de fabrication

Country Status (5)

Country Link
US (1) US20100074740A1 (fr)
EP (1) EP2097617A2 (fr)
CA (1) CA2669582A1 (fr)
DE (1) DE102006057912A1 (fr)
WO (1) WO2008067796A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009013819A1 (de) * 2009-03-18 2010-09-23 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Leitschaufelkranzes für eine Gasturbine sowie Leitschaufelkranz
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
US10161254B2 (en) 2013-03-11 2018-12-25 United Technologies Corporation Structural guide vane sonic shape and inspection
DE102013216354B4 (de) * 2013-08-19 2015-11-05 MTU Aero Engines AG Verfahren zur Herstellung eines Leitschaufelkranzes und Leitschaufelkranz

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10355313A1 (de) * 2003-11-27 2005-06-23 Mtu Aero Engines Gmbh Leitschaufelgitter sowie Verfahren zur Herstellung desselben

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314137A (en) * 1964-02-06 1967-04-18 Schellens True Corp Making product articles by combined cavitation and machining of bar stock
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
DE3527367A1 (de) * 1985-07-31 1987-02-12 Mtu Muenchen Gmbh Auf pulvermetallurgischem wege hergestellte bauteile
CA2030427A1 (fr) * 1989-12-19 1991-06-20 Jonathan S. Stinson Methode d'amelioration de l'integration structurale des joints de liaison d'articles moules en grappe
SE465712B (sv) * 1990-03-01 1991-10-21 Asea Brown Boveri Saett att av pulver tillverka formgods genom isostatisk kompaktering i en deformerbar kapsel
US5732468A (en) * 1996-12-05 1998-03-31 General Electric Company Method for bonding a turbine engine vane segment
JP4060981B2 (ja) * 1998-04-08 2008-03-12 本田技研工業株式会社 ガスタービンの静翼構造体及びそのユニット
US6154959A (en) * 1999-08-16 2000-12-05 Chromalloy Gas Turbine Corporation Laser cladding a turbine engine vane platform
US6821087B2 (en) * 2002-01-21 2004-11-23 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
DE10331397A1 (de) * 2003-07-11 2005-01-27 Mtu Aero Engines Gmbh Verfahren zur Herstellung von Bauteilen einer Gasturbine sowie entsprechendes Bauteil
US20070202000A1 (en) * 2004-08-24 2007-08-30 Gerhard Andrees Method For Manufacturing Components
US20060093849A1 (en) * 2004-11-02 2006-05-04 Farmer Andrew D Method for applying chromium-containing coating to metal substrate and coated article thereof
JP5278936B2 (ja) * 2004-12-02 2013-09-04 独立行政法人物質・材料研究機構 耐熱超合金
SE528006C2 (sv) * 2004-12-23 2006-08-01 Volvo Aero Corp Statisk gasturbinkomponent och förfarande för reparation av en sådan komponent
GB0519502D0 (en) * 2005-09-24 2005-11-02 Rolls Royce Plc Vane assembly
US20070122266A1 (en) * 2005-10-14 2007-05-31 General Electric Company Assembly for controlling thermal stresses in ceramic matrix composite articles
GB2437298B (en) * 2006-04-18 2008-10-01 Rolls Royce Plc A Seal Between Rotor Blade Platforms And Stator Vane Platforms, A Rotor Blade And A Stator Vane

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10355313A1 (de) * 2003-11-27 2005-06-23 Mtu Aero Engines Gmbh Leitschaufelgitter sowie Verfahren zur Herstellung desselben

Also Published As

Publication number Publication date
WO2008067796A3 (fr) 2008-09-12
DE102006057912A1 (de) 2008-06-12
US20100074740A1 (en) 2010-03-25
WO2008067796A2 (fr) 2008-06-12
CA2669582A1 (fr) 2008-06-12

Similar Documents

Publication Publication Date Title
EP1656233B1 (fr) Procede pour realiser et/ou reparer des pieces de turbines a gaz
EP2352615B1 (fr) Procédé de production ou de réparation de disques aubagés monoblocs
EP1322838B1 (fr) Aube de turbomachine et turbomachine
EP1979577A1 (fr) Segment d'aube de guidage d'une turbine a gaz et procede pour sa fabrication
EP1973716B1 (fr) Procédé d'usinage de pièces par fraisage
DE102007050142A1 (de) Verfahren zur Herstellung einer Blisk oder eines Blings, damit hergestelltes Bauteil und Turbinenschaufel
DE102009010109A1 (de) Herstellung einer Turbinenblisk mit einer Oxikations- bzw. Korrosionsschutzschicht
WO2010000238A1 (fr) Procédé de fabrication d’aubes de turbine à gaz
WO2007095902A1 (fr) Procédé de fabrication et de réparation d'un rotor à aubage intégral
DE10331599A1 (de) Bauteil für eine Gasturbine sowie Verfahren zur Herstellung desselben
EP2097617A2 (fr) Couronne d'aubes fixes et procédé de fabrication
EP2346639B1 (fr) Procédé d'assemblage
EP2404036B1 (fr) Procédé de fabrication d'un rotor aubagé monobloc
DE10343782A1 (de) Verfahren zur Herstellung von Bauteilen
DE102005019077A1 (de) Schaufel einer Strömungsmaschine und Verfahren zur Herstellung und/oder Reparatur derselben
WO2008077374A1 (fr) Procédé de fabrication d'un blisk ou d'un bling et composant ainsi fabriqué
DE69120175T2 (de) Reparaturtechnik für Schaufelfüsse
DE102005033625B4 (de) Verfahren zur Herstellung und /oder Reparatur eines integral beschaufelten Rotors
DE102005040184B4 (de) Mantelringsegment einer Gasturbine und Verfahren zur Herstellung derselben
DE102019217434A1 (de) Verfahren zur schichtweisen additiven Herstellung eines Verbundwerkstoffs
DE10355313A1 (de) Leitschaufelgitter sowie Verfahren zur Herstellung desselben
WO2020249148A1 (fr) Rotors pour compresseur à haute pression et turbine à basse pression d'un turboréacteur à double flux, ainsi que procédé pour sa fabrication
DE102012109746A1 (de) Rotor, Dampfturbine und Verfahren zur Herstellung eines Rotors
EP3708775A1 (fr) Composant, utilisation d'un tel composant ainsi que procédé de fabrication d'un tel composant
WO2010057475A1 (fr) Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090603

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20091012

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20160908