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EP1617972A1 - Procede pour arrondir des aretes de pieces - Google Patents

Procede pour arrondir des aretes de pieces

Info

Publication number
EP1617972A1
EP1617972A1 EP04722146A EP04722146A EP1617972A1 EP 1617972 A1 EP1617972 A1 EP 1617972A1 EP 04722146 A EP04722146 A EP 04722146A EP 04722146 A EP04722146 A EP 04722146A EP 1617972 A1 EP1617972 A1 EP 1617972A1
Authority
EP
European Patent Office
Prior art keywords
blade
edge
jet
pressure
suction side
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.)
Granted
Application number
EP04722146A
Other languages
German (de)
English (en)
Other versions
EP1617972B1 (fr
Inventor
Klemens Werner
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 EP1617972A1 publication Critical patent/EP1617972A1/fr
Application granted granted Critical
Publication of EP1617972B1 publication Critical patent/EP1617972B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
    • B24C1/083—Deburring
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B9/00—Machines or devices designed for grinding edges or bevels on work or for removing burrs; Accessories therefor
    • 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
    • Y10T29/47—Burnishing
    • Y10T29/479—Burnishing by shot peening or blasting
    • 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
    • Y10T29/49332—Propeller making
    • 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 rounding edges on components, in particular of turbomachinery, according to the preamble of patent claim 1.
  • Rounding edges on components may be necessary for a variety of reasons. This includes improving strength and / or aerodynamics and avoiding the risk of injury.
  • edges on components there may be sharp edges on components that need to be rounded to the adjacent surfaces of the component.
  • the edges can also form flat or spatial surfaces that connect adjacent, generally considerably larger surfaces of the component. The latter case is usually present in the case of relatively roughly prefabricated edges on aerodynamically effective blades of turbomachinery, in particular on guide and rotor blades of gas turbines, in which the blade edges are to be rounded off from the strength and aerodynamic aspects to the adjacent pressure and / or suction side of the blade ,
  • DE 697 12 613 T2 additionally shows a method for honing cutting edges, these being processed by abrasive fluid jets with abrasive blasting agents in order to introduce fine grooves into the surface.
  • DE 197 20 750 C1 discloses a method for surface treatment in which the surface is subjected to particle radiation. As a result, compressive stresses are introduced into the material in order to increase the fatigue strength, in particular the tensile strength of the component.
  • the object of the invention is to provide a method for rounding edges which, by means of a mechanical, possibly automated, method of operation enables considerable time and personnel savings and leads to reproducible results.
  • the latter should be as high-quality as possible with the smallest possible reject rate.
  • the center of the beam is set approximately tangentially to the bisector at the edge between the generally two surfaces to which the rounding is to take place.
  • surfaces that meet in the form of a sharp edge the position of the bisector is immediately clear.
  • surfaces that do not meet directly e.g. are connected by an edge in the form of a flat or spatial surface, e.g. the pressure and suction side of a roughly prefabricated edge of a blade of a gas turbine
  • tangents are placed on the two surfaces at such an edge and the bisector between the intersecting tangents is defined.
  • this bisector of the angle touches the profile center line of the blade on the edge, i.e. at the stagnation point.
  • the jet is generated by means of a nozzle with a defined outlet diameter and a defined outlet angle.
  • the relative movement between the nozzle and the component can preferably take place at a defined, variable distance between the nozzle and the blade edge.
  • the distance is generally continuously adapted in a corresponding manner.
  • the direction of the center of the jet to the profile center line of the blade at the blade edge can preferably be set at an angle ⁇ and / or can be set laterally offset in relation to the profile center line in the direction of the pressure or suction side, e.g. To create aerodynamics of desired contour asymmetries on the edge to be rounded.
  • FIG. 1 shows a simplified, not to scale representation of the machining of a leading edge of a blade
  • Fig. 2 shows in a representation corresponding to Fig. 1, an alternative embodiment for the processing.
  • edges can be applied to a wide variety of components. Applications are in particular everywhere where there are sharp edges on components adjacent surfaces are to be rounded or where prefabricated edges are to be rounded to define the transition between adjacent surfaces with a defined shape.
  • the method is described below using an edge on a fluidically effective blade of a gas turbine, a relatively roughly prefabricated blade edge being rounded off to adjacent surfaces, in the present case the pressure and / or suction side of the blade.
  • the blade 1 should have a streamlined shape in the finished state. This presupposes that the pressure side 4 and the suction side 5 of the blade profile correspond as closely as possible to the target contour. This also presupposes that the blade edges 2, 3, i.e. the leading edge and the trailing edge of the blade 1, the adjacent surfaces, i.e. connect the pressure and suction side 4,5, aerodynamically. In addition to the aerodynamic requirements, strength and wear aspects also play an important role for the blade edges 2,3. As a rule, the leading and trailing edges of blades are rounded in a defined manner to meet all these requirements.
  • Blades with a relatively thin profile and relatively pointed leading and trailing edges are often manufactured by forging and / or milling and / or electrochemical processing (ECM), the blade edges initially being relatively rough, i.e. with flat surfaces, corners, chamfers, etc.
  • ECM electrochemical processing
  • the large-area pressure and suction sides 4, 5 often correspond relatively precisely to the target contour, so that, if at all, only fine machining with little or no material removal is necessary.
  • the prefabricated leading and trailing edges are thus to be rounded in such a way that they pass into the pressure and suction sides 4, 5 without kinks, steps or other imperfections.
  • the abrasive blasting is used for this purpose as a machining process with targeted removal of the blade material.
  • 1 shows a nozzle 8 of a jet device, not shown, from which a jet 7 emerges, which jet consists of abrasive particles and a carrier gas or a carrier liquid.
  • a jet 7 emerges, which jet consists of abrasive particles and a carrier gas or a carrier liquid.
  • the center of the jet direction R here extends tangentially to the profile center line 6 of the blade 1 on the blade leading edge 2 and thus corresponds at least approximately to the later inflow during operation.
  • the removal result depends on several factors, such as the jet pressure, the exit angle ⁇ of the jet 7 from the nozzle 8, the exit diameter D of the nozzle 8, the distance A of the blade edge 2 from the nozzle 8, the type of abrasive including the particle size and particle distribution in the jet 7, the jet direction R, " and the local exposure time depending on the blade edge parallel, relative feed rate between the nozzle 8 and the component 1.
  • these factors are to be optimized depending on the blade geometry and the blade material, for which practical tests are generally required If, for example, the distance between blade edge 2, 3 and nozzle 8 is too small, instead of a rounding, the blade edge 2, 3 can be concavely hollowed out with maximum removal in the area of the stagnation point, which must be avoided.
  • the method according to the invention is in principle applicable to all types of components and in particular turbomachine blades, be it in housings, disks, rings, compressors, pumps and turbines in axial, diagonal and radial construction.

Landscapes

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

Abstract

L'invention concerne un procédé pour arrondir des arêtes de pièces, notamment de turbomachines. Selon ce procédé, une arête (2,3) formée par au moins deux surfaces (4,5) adjacentes de la pièce (1) est arrondie en direction desdites surfaces (4,5). Un jet (7) constitué essentiellement de particules abrasives est dirigé sur l'arête (2,3), le centre du jet étant tangentiel à la bissectrice (6) entre lesdites surfaces (4,5). Le jet est déplacé avec une avance définie par rapport à la pièce (1) le long de l'arête (2,3) de sorte qu'un enlèvement défini de la matière de la pièce est réalisé avec un arrondissage en direction des surfaces (4,5).
EP04722146A 2003-04-27 2004-03-20 Procede pour arrondir des aretes de pieces Expired - Lifetime EP1617972B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10319020A DE10319020B4 (de) 2003-04-27 2003-04-27 Verfahren zum Verrunden von Kanten an Schaufeln von Turbomaschinen
PCT/DE2004/000581 WO2004096493A1 (fr) 2003-04-27 2004-03-20 Procede pour arrondir des aretes de pieces

Publications (2)

Publication Number Publication Date
EP1617972A1 true EP1617972A1 (fr) 2006-01-25
EP1617972B1 EP1617972B1 (fr) 2007-05-09

Family

ID=33393920

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04722146A Expired - Lifetime EP1617972B1 (fr) 2003-04-27 2004-03-20 Procede pour arrondir des aretes de pieces

Country Status (5)

Country Link
US (1) US7950121B2 (fr)
EP (1) EP1617972B1 (fr)
DE (2) DE10319020B4 (fr)
RU (1) RU2348505C2 (fr)
WO (1) WO2004096493A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005054866A1 (de) * 2005-11-17 2007-05-31 Mtu Aero Engines Gmbh Verfahren zum Herstellen von metallischen Bauteilen, insbesondere für Turbomaschinen, mit kleinen Kantenradien
US8613641B2 (en) * 2008-10-22 2013-12-24 Pratt & Whitney Canada Corp. Channel inlet edge deburring for gas diffuser cases
EP2465636A1 (fr) 2010-12-16 2012-06-20 MTU Aero Engines AG Procédé et dispositif de développement d'un domaine d'un composant ayant un contour prédéterminé
US10155298B2 (en) * 2011-12-21 2018-12-18 Sikorsky Aircraft Corporation Alpha case removal process for a main rotor blade spar
US8906221B2 (en) 2012-08-06 2014-12-09 General Electric Company Electrochemical grinding tool and method
US9162301B2 (en) 2012-08-06 2015-10-20 General Electric Company Electrochemical machining tools and methods
GB2506357B (en) * 2012-09-26 2015-01-28 Rolls Royce Plc Machining of an article
JP6253533B2 (ja) * 2014-07-01 2017-12-27 株式会社神戸製鋼所 切削工具の製造方法
GB2590936B (en) * 2020-01-07 2024-03-06 Vapormatt Ltd Treatment machine and method of improving a cutting edge
RU2757171C1 (ru) * 2021-04-06 2021-10-11 Общество с ограниченной ответственностью Управляющая компания "Алтайский завод прецизионных изделий" Способ дробеструйной обработки втулок плунжеров топливных насосов высокого давления

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3078546A (en) * 1960-06-13 1963-02-26 Bruce E Kiernan Cutting tool
DK0616564T3 (fr) * 1991-12-11 1997-03-17 Christian Diat
KR0127666B1 (ko) * 1992-11-25 1997-12-30 모리시다 요이찌 세라믹전자부품 및 그 제조방법
US5709587A (en) * 1996-03-25 1998-01-20 Kennametal Inc. Method and apparatus for honing an elongate rotary tool
DE19720756C1 (de) * 1997-05-07 1998-09-24 Tacr Turbine Airfoil Coating A Verfahren zum Oberflächenbearbeiten von mechanischen Bauteilen mittels Partikelbestrahlung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004096493A1 *

Also Published As

Publication number Publication date
WO2004096493A1 (fr) 2004-11-11
DE10319020B4 (de) 2006-06-14
US7950121B2 (en) 2011-05-31
DE502004003770D1 (de) 2007-06-21
US20070050977A1 (en) 2007-03-08
RU2348505C2 (ru) 2009-03-10
RU2005136898A (ru) 2007-06-10
DE10319020A1 (de) 2004-11-25
EP1617972B1 (fr) 2007-05-09

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