EP2004346A2 - Procede de fabrication d'un composant - Google Patents

Procede de fabrication d'un composant

Info

Publication number
EP2004346A2
EP2004346A2 EP07722168A EP07722168A EP2004346A2 EP 2004346 A2 EP2004346 A2 EP 2004346A2 EP 07722168 A EP07722168 A EP 07722168A EP 07722168 A EP07722168 A EP 07722168A EP 2004346 A2 EP2004346 A2 EP 2004346A2
Authority
EP
European Patent Office
Prior art keywords
component
blade
transition
gas turbine
transition region
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Withdrawn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
EP07722168A
Other languages
German (de)
English (en)
Inventor
Thomas Dautl
Thomas Peschke
Alexander Winkler
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 EP2004346A2 publication Critical patent/EP2004346A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/005—Vibratory devices, e.g. for generating abrasive blasts by ultrasonic vibrations
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • Y10T29/49336—Blade making

Definitions

  • the invention relates to a method for producing a component, in particular a gas turbine component.
  • Modern gas turbines in particular aircraft engines, must meet the highest demands in terms of reliability, weight, performance, economy and service life.
  • 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 turbine parts of the aircraft engine.
  • Powder metallurgical injection molding represents an alternative for the manufacture or production of complex components. Powder metallurgical injection molding is related to plastic injection molding and is also referred to as metal mold injection molding or metal injection molding (MIM) processes.
  • MIM metal injection molding
  • gas turbine components are components with complex geometries or surface contours
  • gas turbine blades have transition areas between component surfaces, which are characterized by relatively small transition radii.
  • small transition radii between a suction side surface and a pressure side surface are desired in order to control the aerodynamic behavior of such blades. optimizing shovels.
  • small transition radii between a fir tree-like or dovetail-shaped surface and an end face are desirable so as to increase the aerofoil of paddle roots.
  • the present invention based on the problem to provide a novel method for producing a component.
  • This problem is solved by a method for manufacturing a component according to claim 1.
  • the method comprises at least the following steps: a) producing a component having a plurality of component surfaces, at least one transition region between two component surfaces having a transition radius which is greater than 0.05 mm and less than 0.30 mm; b) solidifying the component at least at the or each transition region by ultrasonic shot peening.
  • Fig. 1 is a highly schematic flow diagram of the method according to the invention for producing a component.
  • the present invention relates to a method for producing a component, in particular a method for manufacturing a rotor blade of a gas turbine rotor.
  • a method for producing a component in particular a method for manufacturing a rotor blade of a gas turbine rotor.
  • a rotor blade of a gas turbine is produced.
  • Such a blade has a plurality of component surfaces, wherein transition areas between two component surfaces are characterized by a transition radius.
  • a rotor blade is provided in step 10, which has at least one transition region with a relatively small transition radius, which is greater than 0.05 mm and less than 0.30 mm.
  • This transition region with the relatively small transition radius may be e.g. a transition region on a blade trailing edge of an airfoil of the blade act, ie, a transition region between a suction side surface and a pressure side surface of the airfoil.
  • a transition radius of 0.05 mm a thickness of the blade trailing edge of 0.10 mm can be provided.
  • the transition region with the relatively small transition radius may be a transition region on a blade root of the blade, namely a transition region between a fir tree-like or dovetail-shaped, extending substantially in the longitudinal direction of the blade airfoil and extending substantially in the transverse direction of the blade end face of the blade root.
  • step 10 the blade is made by forging or investment casting or by powder metallurgy injection molding.
  • the precision balls used as a jet body are not directed as with conventional shot peening with the aid of a directed compressed air jet to the radiating transition regions of the blade, but the precision balls are accelerated by means of a sonotrode vibrating in the ultrasonic range, whereby the precision balls in the sense of a stochastic distribution and therefore meet the or each transition region of the component to be solidified in an undirected manner.
  • step 10 after finishing in the sense of step 10 and before solidification in the sense of step 11 in the sense of step 12, it can be checked whether, due to the manufacturing tolerance of step 10, prior to solidification of the or each transition region, rounding thereof is required , If necessary, branching is made to step 13 and rounding of the or each transition region is performed by means of a brush-type tool.
  • step 10 the manufacturing quality of step 10 is sufficiently good, then the rounding according to step 13 can be dispensed with and the solidification in the sense of step 11 can take place directly on the production of the component in the sense of step 10.
  • the method according to the invention it becomes possible for the first time to provide transition regions with transition radii of less than 0.30 mm on rotor blades of a gas turbine rotor and to strengthen them without the risk of damage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Forging (AREA)
  • Laser Beam Processing (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un procédé de fabrication d'un composant, notamment d'un composant de turbine à gaz, comprenant au moins les étapes suivantes : a) fabrication d'un composant avec plusieurs surfaces de composant, au moins une partie de transition entre deux surfaces de composant présentant un rayon de transition supérieur à 0,05 mm et inférieur à 0,3 mm; b) solidification du composant au moins au niveau de la ou de chaque partie de transition, par grenaillage par ultrasons.
EP07722168A 2006-04-11 2007-04-04 Procede de fabrication d'un composant Withdrawn EP2004346A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006016949A DE102006016949A1 (de) 2006-04-11 2006-04-11 Verfahren zum Herstellen eines Bauteils
PCT/DE2007/000610 WO2007115550A2 (fr) 2006-04-11 2007-04-04 Procede de fabrication d'un composant

Publications (1)

Publication Number Publication Date
EP2004346A2 true EP2004346A2 (fr) 2008-12-24

Family

ID=38536537

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07722168A Withdrawn EP2004346A2 (fr) 2006-04-11 2007-04-04 Procede de fabrication d'un composant

Country Status (4)

Country Link
US (1) US20090119920A1 (fr)
EP (1) EP2004346A2 (fr)
DE (1) DE102006016949A1 (fr)
WO (1) WO2007115550A2 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9474546B1 (en) 2008-04-18 2016-10-25 Advanced Bionics Ag Pre-curved electrode array insertion tools
EP2451366B1 (fr) * 2009-07-08 2017-03-15 Advanced Bionics AG Outils d'insertion de fil
US8753352B2 (en) 2010-06-25 2014-06-17 Advanced Bionics Ag Tools, systems, and methods for inserting a pre-curved electrode array portion of a lead into a bodily orifice
US8774944B2 (en) 2010-06-25 2014-07-08 Advanced Bionics Ag Tools, systems, and methods for inserting an electrode array portion of a lead into a bodily orifice
US8753353B2 (en) 2010-06-25 2014-06-17 Advanced Bionics Ag Tools, systems, and methods for inserting an electrode array portion of a lead into a bodily orifice
GB201418258D0 (en) * 2014-10-15 2014-11-26 Rolls Royce Plc Manufacture method
GB201615671D0 (en) 2016-09-15 2016-11-02 Rolls Royce Plc A method of manufacturing a component from a nickel-based superalloy
BE1025262B1 (fr) * 2017-05-31 2019-01-07 Safran Aero Boosters S.A. Procede de grenaillage pour piece de turbomachine
CN108436402A (zh) * 2018-06-19 2018-08-24 绵阳市瑞丰机电制造有限公司 一种汽轮机静叶叶片加工工艺

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4426867A (en) * 1981-09-10 1984-01-24 United Technologies Corporation Method of peening airfoils and thin edged workpieces
FR2801236B1 (fr) * 1999-11-18 2001-12-21 Snecma Procede et machine de grenaillage par ultrasons de pieces sur une roue
FR2816537B1 (fr) * 2000-11-16 2003-01-17 Snecma Moteurs Procede et installation de grenaillage par ultrasons des alveoles annulaires d'attache d'aubes sur un rotor
FR2816538B1 (fr) * 2000-11-16 2003-01-17 Snecma Moteurs Procede pour augmenter la duree de vie des attaches d'aubes sur un rotor
US20060021410A1 (en) * 2004-07-30 2006-02-02 Sonats-Societe Des Nouvelles Applications Des Techniques De Surfaces Shot, devices, and installations for ultrasonic peening, and parts treated thereby
DE102004037954A1 (de) * 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Vorrichtung zum Oberflächenstrahlen von Bauteilen
US7384244B2 (en) * 2004-12-16 2008-06-10 General Electric Company Fatigue-resistant components and method therefor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007115550A3 *

Also Published As

Publication number Publication date
DE102006016949A1 (de) 2007-10-25
WO2007115550A2 (fr) 2007-10-18
US20090119920A1 (en) 2009-05-14
WO2007115550A3 (fr) 2008-02-21

Similar Documents

Publication Publication Date Title
DE10337866B4 (de) Verfahren zur Herstellung von Bauteilen für Gasturbinen
EP2004346A2 (fr) Procede de fabrication d'un composant
EP2081731B1 (fr) Procédé de réparation de pales de turbines à haute pression
DE102010037690A1 (de) Turbinenrotor-Fabrikation unter Anwendung des Kaltspritzens
EP1973716B1 (fr) Procédé d'usinage de pièces par fraisage
DE60319492T2 (de) Reparaturmethode für einen Turbinenleitapparat und Turbinenleitapparat
DE102009010109A1 (de) Herstellung einer Turbinenblisk mit einer Oxikations- bzw. Korrosionsschutzschicht
DE102009049707A1 (de) Verfahren zur Herstellung einer Lauf- oder Statorschaufel und eine derartige Schaufel
DE10357656A1 (de) Verfahren zur Herstellung von Gasturbinenbauteilen und Bauteil für eine Gasturbine
DE69116440T2 (de) Verfahren zur Reparatur von Turbinen
WO2011054342A1 (fr) Disque aubagé monobloc, turbine à gaz et procédé de fabrication d'un tel disque aubagé monobloc
EP2725193A1 (fr) Methode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.
WO2010000238A1 (fr) Procédé de fabrication d’aubes de turbine à gaz
DE102009013819A1 (de) Verfahren zur Herstellung eines Leitschaufelkranzes für eine Gasturbine sowie Leitschaufelkranz
EP2323799B1 (fr) Procédé d'assemblage d'éléments
EP3147069A1 (fr) Procédé de fabrication d'une aube hybride d'une turbomachine thermique par soudage de rechargement
EP1051568B1 (fr) Procede pour produire un composant d'une turbomachine expose a l'usure
EP1805344B1 (fr) Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure
DE102019118072A1 (de) Rotor und Verfahren zum Herstellen eines Rotors
WO2010149141A2 (fr) Procédé de fabrication et/ou de réparation d'une pale pour une turbomachine
EP1393836A1 (fr) Méthode de fabrication d'éléments aubagés, ébauches pour les éléments aubagés et utilisation des ébauches
DE69821198T2 (de) Verfahren zur Herstellung einer bimetallischen Turbinenschaufel und Verwendung
WO2007003166A1 (fr) Procede de fabrication d'une piece composite constituee de deux segments entre lesquels est situee une couche adhesive en materiau a base de nickel
DE102008035585A1 (de) Verfahren zur Herstellung metallischer Bauteile
DE102019202054A1 (de) Laufschaufel für eine thermische Rotationsmaschine sowie Verfahren zum Herstellen einer solchen Laufschaufel

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: 20081008

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PESCHKE, THOMAS

Inventor name: DAUTL, THOMAS

Inventor name: WINKLER, ALEXANDER

17Q First examination report despatched

Effective date: 20090218

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

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: 20100515