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EP1617972A1 - Method for rounding part edges - Google Patents

Method for rounding part edges

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)
French (fr)
Other versions
EP1617972B1 (en
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/en
Application granted granted Critical
Publication of EP1617972B1 publication Critical patent/EP1617972B1/en
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.

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

Abstract

The invention relates to a method for rounding part edges, in particular for turbomashines. According to said invention, an edge (2,3) formed by at least two adjacent surfaces (4, 5) of a part (1) is rounded in a direction to said adjacent surfaces. A jet (7) consisting essentially of abrasive particles is directed to the edge (2, 3), the jet centre being tangential with respect to a bisectrix (6) between said surfaces (4, 5). Said jet is displaceable according to a defined feed with respect to the part (1) along the edge (2,3) in such a way that a defined removal of the part material is carried out associated with rounding in the direction of the surfaces (4, 5).

Description

Verfahren zum Verrunden von Kanten an Bauteilen Process for rounding edges on components
Die Erfindung betrifft ein Verfahren zum Verrunden von Kanten an Bauteilen, insbesondere von Turbomaschinen, gemäß dem Oberbegriff des Patentanspruches 1.The invention relates to a method for rounding edges on components, in particular of turbomachinery, according to the preamble of patent claim 1.
Das Verrunden von Kanten an Bauteilen, insbesondere von Turbomaschinen, kann aus verschiedensten Gründen erforderlich sein. Hierzu zählen die Verbesserung der Festigkeit und/oder Aerodynamik sowie die Vermeidung von Verletzungsgefahr. In Abhängigkeit vom Bauteil kann es sich dabei um scharfe Kanten an Bauteilen handeln, die zu den angrenzenden Oberflächen des Bauteils zu verrunden sind. Alternativ können die Kanten auch ebene oder räumliche Flächen bilden, die angrenzende, im Allgemeinen erheblich größere Oberflächen des Bauteils verbinden. Der letztgenannte Fall liegt üblicherweise bei relativ grob vorgefertigten Kanten an strömungsmechanisch wirksamen Schaufeln von Turbomaschinen, insbesondere an Leit- und Laufschaufeln von Gasturbinen, vor, bei dem die Schaufelkanten zur angrenzenden Druck- und/oder Saugseite der Schaufel aus Festigkeits- und Aerodynamikaspekten zu verrunden sind.Rounding edges on components, especially turbomachinery, may be necessary for a variety of reasons. This includes improving strength and / or aerodynamics and avoiding the risk of injury. Depending on the component, there may be sharp edges on components that need to be rounded to the adjacent surfaces of the component. Alternatively, 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 ,
Es ist bekannt, Oberflächen vor Beschichtungsvorgängen durch abrasives Strahlen aufzurauhen, um die Oberflächen zu reinigen und die Haftung zur Schicht zu verbessern. DE 697 12 613 T2 zeigt zusätzlich ein Verfahren zum Honen von Schneidkanten, wobei diese durch abrasive Fluidstrahlen mit abrasiven Strahlmitteln bearbeitet werden, um feine Riefen in die Oberfläche einzubringen.It is known to roughen surfaces before coating processes by abrasive blasting in order to clean the surfaces and to improve the adhesion to the layer. 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 offenbart ein Verfahren zur Oberflächenbehandlung, bei dem die Oberfläche einer Partikelbestrahlung unterzogen wird. Hierdurch werden Druckspannungen in das Material eingebracht, um die Dauerfestigkeit insbesondere die Zugfestigkeit des Bauteils zu erhöhen.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.
Das Verrunden wird im Fall von Schaufelkanten, welche fertigungsbedingt im allgemeinen nur relativ grob vorbearbeitet sind, bis dato weitgehend in Handarbeit ausgeführt, wobei ggf. handgeführte Maschinen, wie Bandschleifer etc., eingesetzt werden. Dies ist mit einem hohen Personal- und Zeitaufwand verbunden, wobei auch mit gezielter Kon- trolle und Prüfung letztlich kein reproduzierbares, gleichbleibendes Bearbeitungsergebnis gewährleistet ist.In the case of blade edges, which are generally only roughly pre-machined due to production, rounding has hitherto been carried out largely by hand, with manual machines, such as belt grinders, etc. being used where appropriate. This is associated with a high expenditure of personnel and time, whereby also with targeted trolling and testing ultimately no reproducible, consistent processing result is guaranteed.
Angesichts dieser bekannten Verfahren und ihrer Nachteile bzw. ihrer anwendungstechnischen Grenzen besteht die Aufgabe der Erfindung darin, ein Verfahren zum Verrunden von Kanten bereitzustellen, welches durch eine maschinelle, ggf. automatisierbare Arbeitsweise eine erhebliche Zeit- und Personaleinsparung ermöglicht und zu reproduzierbaren Ergebnissen führt. Letztere sollen möglichst qualitativ einwandfrei bei möglichst kleiner Ausschussrate sein.In view of these known methods and their disadvantages or their application-technical limits, 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.
Die Aufgabe wird durch die in Patentanspruch 1 gekennzeichneten Merkmale gelöst.The object is achieved by the features characterized in claim 1.
Überraschenderweise hat sich herausgestellt, dass durch abrasives Strahlen unter Beachtung definierter Bearbeitungsparameter und Düsendefinitionen relativ genaue, gerundete Oberflächengeometrien an scharfen Kanten von Bauteilen oder relativ grob vorbearbeiteten Schaufelkanten herstellbar sind. Die Funktionstüchtigkeit dieses Verfahrens sowie seine Reproduzierbarkeit wurden in Versuchen bestätigt.Surprisingly, it has been found that abrasive blasting, taking into account defined machining parameters and nozzle definitions, can produce relatively precise, rounded surface geometries on sharp edges of components or relatively roughly pre-machined blade edges. The functionality of this process and its reproducibility have been confirmed in tests.
Beim erfindungsgemäßen Verfahren wird der Strahl mit seiner Mitte etwa tangential zur Winkelhalbierenden an der Kante zwischen den im Allgemeinen zwei Oberflächen, zu denen die Verrundung erfolgen soll, eingestellt. Bei in Form einer scharfen Kante aufeinandertreffenden Oberflächen ist die Lage der Winkelhalbierenden unmittelbar klar. Bei nicht unmittelbar aufeinandertreffenden Oberflächen, die z.B. durch eine Kante in Form einer ebenen oder räumlichen Fläche verbunden sind, wie z.B. die Druck- und Saugseite einer grob vorgefertigten Kante einer Schaufel einer Gasturbine, werden Tangenten an die beiden Oberflächen an einer solchen Kante gelegt und die Winkelhalbierende zwischen den sich schneidenden Tangenten festgelegt. Im letztgenannten Fall einer zur Druck- und Saugseite einer Schaufel zur verrundenden Kante tangiert diese Winkelhalbierende die Profilmittellinie der Schaufel an der Kante, d.h. im Staupunkt.In the method according to the invention, 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. With surfaces that meet in the form of a sharp edge, the position of the bisector is immediately clear. In the case of 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. In the latter case of an edge rounding to the pressure and suction side of a blade, this bisector of the angle touches the profile center line of the blade on the edge, i.e. at the stagnation point.
Zur Reduzierung einer etwaigen Nachbearbeitung der verrundeten Kanten werden relativ kleine Partikel mit einer Größe von 0 bis δOO.mesh, vorzugsweise von 180 bis 320 mesh, verwendet. Hierdurch wird mit dem Verfahren ein Materialabtrag zum Verrunden erzeugt und Risse oder Rauigkeiten an den Oberflächen vermieden.To reduce any post-processing of the rounded edges, relatively small particles with a size of 0 to δOO.mesh, preferably from 180 to 320 mesh, used. As a result, the process produces material removal for rounding and cracks or roughness on the surfaces are avoided.
Unter anderem zur Erzeugung eines Strahls mit definierter Geometrie und Energie im Hinblick auf Querschnitt, Form etc. wird der Strahl mittels einer Düse mit definiertem Austrittsdurchmesser und definiertem Austrittwinkel erzeugt.Among other things, to generate a jet with a defined geometry and energy in terms of cross section, shape, etc., the jet is generated by means of a nozzle with a defined outlet diameter and a defined outlet angle.
Zur Erzeugung einer gleichbleibenden Geometrie entlang der Kante kann die Relativbewegung zwischen Düse und Bauteil bevorzugt in einem definierten, variierbaren Abstand zwischen Düse und Schaufelkante erfolgen.In order to produce a constant geometry along the edge, 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.
Der Abstand wird im allgemeinen bei flächigen Kanten mit sich über deren Länge ändernder Breite in entsprechender Weise stufenlos angepasst.In the case of flat edges with a width that changes over their length, the distance is generally continuously adapted in a corresponding manner.
Bevorzugt kann die Richtung der Mitte des Strahls zur Profilmittellinie der Schaufel an der Schaufelkante in einem Winkel ß angestellt und/oder zur Profilmittellinie in Richtung Druck- oder Saugseite seitlich versetzt eingestellt werden, um z.B. Aerodynamik gewollte Konturasymmetrien an der zu verrundenden Kante auszubilden.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 β 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.
In den Unteransprüchen sind bevorzugte Ausgestaltungen sowie Anwendungen des Verfahrens und der Vorrichtung beschrieben.Preferred embodiments and applications of the method and the device are described in the subclaims.
Die Erfindung wird nachfolgend anhand der Zeichnung mit Bezug auf Ausführungsbeispiele näher erläutert:The invention is explained in more detail below with reference to the drawing with reference to exemplary embodiments:
Fig. 1 zeigt in vereinfachter, nicht maßstäblicher Darstellung die Bearbeitung einer Eintrittskante einer Schaufel;1 shows a simplified, not to scale representation of the machining of a leading edge of a blade;
Fig. 2 zeigt in entsprechender Darstellung wie Fig. 1 ein alternatives Ausführungsbeispiel für die Bearbeitung.Fig. 2 shows in a representation corresponding to Fig. 1, an alternative embodiment for the processing.
Das Verfahren zum Verrunden von Kanten ist bei verschiedensten Bauteilen anwendbar. Anwendungsfälle liegen insbesondere überall dort, wo scharfe Kanten an Bauteilen zu angrenzenden Oberflächen hin zu verrunden sind oder wo vorgefertigte Kanten zur Gestaltung des Übergangs zwischen angrenzenden Oberflächen mit definierter Gestalt zu verrunden sind.The process for rounding 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.
Nachfolgend wird das Verfahren anhand einer Kante an einer strömungsmechanisch wirksamen Schaufel einer Gasturbine beschrieben, wobei eine relativ grob vorgefertigte Schaufelkante zu angrenzenden Oberflächen, im vorliegenden Fall der Druck- und/oder Saugseite der Schaufel, zu verrunden ist.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.
Die Schaufel 1 soll im fertigbearbeiteten Zustand eine strömungsgünstige Gestalt aufweisen. Dies setzt voraus, dass die Druckseite 4 und die Saugseite 5 des Schaufelprofils bestmöglich der Sollkontur entsprechen. Dies setzt ebenfalls voraus, dass die Schaufelkanten 2, 3, d.h. die Eintrittskante und die Austrittskante der Schaufel 1, die angrenzenden Oberflächen, d.h. die Druck- und Saugseite 4,5, strömungsgünstig verbinden. Neben den aerodynamischen Anforderungen spielen auch festigkeits- und verschleißtechnische Aspekte bei den Schaufelkanten 2,3 eine wichtige Rolle. In der Regel werden die Ein- und Austrittskanten von Schaufeln definiert gerundet ausgeführt, um all diesen Anforderungen gerecht zu werden.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.
Schaufeln mit relativ dünnem Profil und relativ spitzen Ein- und Austrittskanten, wie insbesondere Verdichterschaufeln von Axialverdichtern, werden häufig durch Schmieden und/oder Fräsen und/oder elektrochemische Bearbeitung (ECM) gefertigt, wobei die Schaufelkanten zunächst geometrisch nur relativ grob ausgeführt sind, d.h. mit ebenen Flächen, Ecken, Fasen etc.. Die großflächigen Druck -und Saugseiten 4,5 entsprechen häufig schon relativ genau der Sollkontur, so dass dort, falls überhaupt, nur noch eine Feinbearbeitung mit geringem oder keinem Materialabtrag nötig ist. Somit sind die vorgefertigten Ein- und Austrittskanten in der Weise zu runden, dass sie ohne Knicke, Stufen oder andere Störstellen in die Druck- und Saugseiten 4,5 übergehen.Blades with a relatively thin profile and relatively pointed leading and trailing edges, such as, in particular, compressor blades of axial compressors, 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. 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.
Erfindungsgemäß wird hierfür das abrasive Strahlen als Bearbeitungsverfahren mit gezieltem Abtrag des Schaufelmaterials verwendet. Man erkennt in der Fig. 1 eine Düse 8 einer nicht näher dargestellten Strahlvorrichtung, aus der ein Strahl 7 austritt, welcher aus abrasiven Partikeln und einem Trägergas bzw.. einer Trägerflüssigkeit besteht. Zu- mindest ein erheblicher Teil der abrasiven Partikel trifft mit hoher Geschwindigkeit senkrecht oder näherungsweise senkrecht auf die nur vorbearbeitete, mehr oder weniger noch eckige Schaufelkante 2, deren Ausgangszustand in der Fig.1 gestrichelt angedeutet ist. Die Mitte der Strahlrichtung R verläuft hier tangential zur Profilmittellinie 6 der Schaufel 1 an der Schaufelvorderkante 2 und entspricht somit zumindest annähernd der späteren Anströmung im Betrieb. Es besteht selbstverständlich die Möglichkeit, die Längsmittelachse der Düse 8 und damit die Mitte des Strahles 7 bedarfsweise mehr zur Saugseite 5 oder zur Druckseite 4 zu verschieben und/oder den Anströmwinkel der Strahlrichtung R in gewissen Grenzen zu ändern, wie es in Fig. 2 anhand des Winkels ß gezeigt ist. Auf diese Art lässt sich ein asymmetrischer Abtrag mit Schwerpunkt zur Druck- oder Saugseite hin erzielen, was unter gewissen Umständen sinnvoll sein kann.According to the invention, 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. To- at least a substantial part of the abrasive particles hits the only pre-machined, more or less angular blade edge 2 at high speed, vertically or approximately vertically, the initial state of which is indicated by dashed lines in FIG. 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. There is of course the possibility of shifting the longitudinal central axis of the nozzle 8 and thus the center of the jet 7 more towards the suction side 5 or the pressure side 4 and / or changing the inflow angle of the jet direction R within certain limits, as is shown in FIG. 2 of the angle ß is shown. In this way, asymmetrical removal with a focus on the pressure or suction side can be achieved, which can be useful under certain circumstances.
Das Abtragergebnis hängt von mehreren Faktoren ab, wie dem Strahldruck, dem Austrittswinkel α des Strahles 7 aus der Düse 8, dem Austrittsdurchmesser D der Düse 8, dem Abstand A der Schaufelkante 2 von der Düse 8, der Art des Strahlmittels einschließlich der Partikelgröße und Partikelverteilung im Strahl 7, der Strahlrichtung R," und der lokalen Einwirkdauer in Abhängigkeit von der schaufelkantenparallelen, relativen Vorschubgeschwindigkeit zwischen der Düse 8 und dem Bauteil 1. Diese Faktoren sind in Abhängigkeit von der Schaufelgeometrie und dem Schaufelwerkstoff zu optimieren, wofür in aller Regel praktische Versuche erforderlich sein werden. Ist beispielsweise der Abstand zwischen Schaufelkante 2,3 und Düse 8 zu gering, so kann es statt zu einer Verrundung zu einer konkaven Aushöhlung der Schaufelkante 2,3 mit maximalen Abtrag im Bereich des Staupunktes kommen, was unbedingt zu vermeiden ist. Bei korrektem Abstand ergibt sich ein gewisser Partikelauftrag im Bereich des Staupunktes, wodurch dieser weitgehend vor Abtrag geschützt ist, und der eigentliche Abtrag zur Verrundung stromabwärts zur Druck- und Saugseite hin erfolgt. Nach einer solchen experimentellen Prozessoptimierung sind die Strahlergebnisse bei einem bestimmten Schaufeltyp jedoch sehr gleichmäßig und reproduzierbar, so dass eine maschinelle bzw. automatisierte Arbeitsweise möglich wird. Das erfindungsgemäße Verfahren ist prinzipiell bei allen Arten von Bauteilen und insbesondere Turbomaschinenschaufeln anwendbar, sei es bei Gehäusen, Scheiben, Ringen, Verdichtern, Pumpen und Turbinen in Axial-, Diagonal- und Radialbauweise. The removal result depends on several factors, such as the jet pressure, the exit angle α 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. If the distance is correct, there is a certain particle application in the area d es stagnation point, whereby this is largely protected against removal, and the actual removal for rounding takes place downstream to the pressure and suction side. After such an experimental process optimization, however, the blasting results for a certain blade type are very even and reproducible, so that a mechanical or automated mode of operation is possible. 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.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
1 Bauteil/Schaufel1 component / bucket
2 Kante/Schaufelkante2 edge / blade edge
3 Kante/Schaufelkante3 edge / blade edge
4 Oberfläche/Druckseite4 surface / printing side
5 Oberfläche/Saugseite5 surface / suction side
6 Winkelhalbierende/Profilmittellinie6 bisector / profile center line
7 Strahl7 beam
8 Düse8 nozzle
A AbstandA distance
D AustrittsdurchmesserD outlet diameter
R StrahlrichtungR beam direction
Austrittswinkel ß Winkel Exit angle ß angle

Claims

Patentansprüche claims
1. Verfahren zum Verrunden von Kanten an Bauteilen, insbesondere von Turbomaschinen, wobei eine durch wenigstens zwei aneinandergrenzende Oberflächen (4,5) des Bauteils (1) erzeugte Kante (2,3) zu den Oberflächen (4,5) hin zu verrunden ist und ein zumindest großteils aus abrasiven Partikeln bestehender Strahl (7) verwendet wird, dadurch gekennzeichnet, dass der Strahl mit seiner Mitte etwa tangential zur von den Oberflächen (4,5) an der Kante (2,3) definierten Winkelhalbierenden (6) eingestellt wird und der Strahl (7) und die Kante (2,3) mit definiertem Vorschub in der Weise relativ zueinander längs der Kante (2,3) bewegt werden, dass ein definierter Abtrag des Bauteilmaterials unter Verrundung zu den Oberflächen (4,5) hin erfolgt.1. A method for rounding edges on components, in particular of turbomachinery, wherein an edge (2, 3) generated by at least two adjoining surfaces (4, 5) of the component (1) is to be rounded towards the surfaces (4, 5) and an at least largely abrasive particle beam (7) is used, characterized in that the center of the jet is set approximately tangentially to the bisector (6) defined by the surfaces (4, 5) on the edge (2, 3) and the jet (7) and the edge (2, 3) are moved along the edge (2, 3) with a defined feed in such a way that a defined removal of the component material rounding off to the surfaces (4, 5) he follows.
2. Verfahren nach Anspruch 1, wobei die Bauteile Schaufeln von Turbomaschinen, insbesondere Leit- und Laufschaufeln von Gasturbinen, sind, und wobei eine vorgefertigte Schaufelkante (2,3) zur angrenzenden Druck- und Saugseite (4,5) der Schaufel (1) hin zu verrunden ist, dadurch gekennzeichnet, dass der Strahl (7) mit seiner Mitte etwa tangential zur Profilmittellinie (6) der Schaufel (1) an der Schaufelkante (2, 3) eingestellt wird und der Strahl (7) und die Schaufelkante (2,3) in der Weise relativ zueinander längs der Schaufelkante (2,3) bewegt werden, dass die Verrundung zur Druck- und Saugseite (4,5) hin erfolgt.2. The method according to claim 1, wherein the components are blades of turbomachinery, in particular guide and rotor blades of gas turbines, and wherein a prefabricated blade edge (2,3) to the adjacent pressure and suction side (4,5) of the blade (1) is rounded, characterized in that the jet (7) is set approximately tangentially to the profile center line (6) of the blade (1) at the blade edge (2, 3) and the jet (7) and the blade edge (2 , 3) are moved relative to one another along the blade edge (2, 3) in such a way that the rounding takes place toward the pressure and suction side (4, 5).
3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Strahl (7) aus abrasiven Partikeln, einem Trägergas und/oder einer Trägerflüssigkeit, wie z.B. Wasser, besteht.3. The method according to claim 1 or 2, characterized in that the jet (7) of abrasive particles, a carrier gas and / or a carrier liquid, such as. Water.
4. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass als abrasive Partikel Metalloxide, wie AI203 oder SiO, andere keramische Verbindungen, Salze, wie NaCI, oder organische Verbindungen, wie Kunststoffe oder Maiskolbenschrot, verwendet werden. 4. The method according to any one of the preceding claims, characterized in that the abrasive particles are metal oxides, such as Al 2 0 3 or SiO, other ceramic compounds, salts, such as NaCl, or organic compounds, such as plastics or corncob meal.
5. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass Partikel mit einer Größe von 0 bis 500 mesh, vorzugsweise von 180 bis 320 mesh, verwendet werden.5. The method according to any one of the preceding claims, characterized in that particles with a size of 0 to 500 mesh, preferably from 180 to 320 mesh, are used.
6. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Strahl (7) mittels einer Düse (8) mit definiertem Austrittsdurchmesser (D) und definiertem Austrittswinkel (α) erzeugt wird, wobei insbesondere ein Teil des Strahlquerschnitts zumindest weitgehend von Partikeln freigehalten wird.6. The method according to any one of the preceding claims, characterized in that the jet (7) by means of a nozzle (8) with a defined outlet diameter (D) and a defined outlet angle (α) is generated, in particular a part of the beam cross section at least largely kept free of particles becomes.
7. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Druck des Strahls (7) auf etwa 3 bis 3,5 bar eingestellt wird.7. The method according to any one of the preceding claims, characterized in that the pressure of the jet (7) is set to about 3 to 3.5 bar.
8. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Relativbewegung von Düse (8) und Bauteil (1) mit einem definierten, variierbaren Abstand (A) zwischen der Düse (8) und der Kante (2,3) erfolgt.8. The method according to any one of the preceding claims, characterized in that the relative movement of the nozzle (8) and component (1) takes place with a defined, variable distance (A) between the nozzle (8) and the edge (2,3).
9. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass auf die abrasive Bearbeitung mindestens eine weitere Bearbeitung, wie Scheuern oder Kugelstrahlen, folgt.9. The method according to any one of the preceding claims, characterized in that the abrasive processing is followed by at least one further processing, such as scrubbing or shot peening.
10. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es zur Bearbeitung von durch Schmieden und/oder Fräsen und/oder elektrochemischen Bearbeiten (ECM) vorgefertigten Bauteilen, insbesondere Schaufeln (1), aus Legierungen auf Basis von Titan (Ti) Nickel (Ni) oder Kobalt (Co) verwendet wird, insbesondere von Verdichterschaufeln in Axialbauart.10. The method according to any one of the preceding claims, characterized in that it is used for machining components prefabricated by forging and / or milling and / or electrochemical machining (ECM), in particular blades (1), from alloys based on titanium (Ti) nickel (Ni) or cobalt (Co) is used, in particular of compressor blades in axial design.
1 1. Verfahren nach einem der Ansprüche 2 bis 10, dadurch gekennzeichnet, dass es zur Bearbeitung von Einzelschaufeln, von Schaufelsegmenten oder von integral beschaufelten Scheiben oder Ringen verwendet wird.1 1. The method according to any one of claims 2 to 10, characterized in that it is used for processing individual blades, blade segments or integrally bladed discs or rings.
12. Verfahren nach einem der Ansprüche 2 bis 1 1, dadurch gekennzeichnet, dass die Richtung (R) der Mitte des Strahls (7) zur Profilmittellinie (6) der Schaufel (1) an der Schaufelkante (2,3) in einem Winkel (ß) angestellt und/oder zur Profilmittellinie (6) in Richtung Druck- oder Saugseite seitlich versetzt eingestellt wird.12. The method according to any one of claims 2 to 1 1, characterized in that the direction (R) of the center of the beam (7) to the profile center line (6) of the blade (1) on the Blade edge (2, 3) is set at an angle (β) and / or set laterally offset in relation to the profile center line (6) in the direction of the pressure or suction side.
13. Verfahren nach einem der Ansprüche 2 bis 12, dadurch geicennzeichnet, dass die zu verrundenden Schaufelkanten (2,3) eine zumindest annähernd quer zur angrenzenden Druck- und/oder Saugseite (4,5) stehende Fläche sowie mehr oder weniger eckige Übergänge zur Druck- und/oder Saugseite (4,5) aufweist und der Strahl (7) senkrecht oder annähernd senkrecht auf die Fläche der Schaufelkante (2,3) gelenkt wird.13. The method according to any one of claims 2 to 12, characterized in that the blade edges to be rounded (2, 3) have an at least approximately transverse surface to the adjacent pressure and / or suction side (4, 5) and more or less angular transitions to Has pressure and / or suction side (4,5) and the jet (7) is directed perpendicularly or approximately perpendicularly to the surface of the blade edge (2,3).
14. Verfahren nach Anspruch 13, dadurch geicennzeichnet, dass die Richtung (R) der Mitte des Strahls (7) etwa tangential zur Profilmittellinie (6) der Schaufel (1) an der Schaufelkante (2,3) eingestellt wird. 14. The method according to claim 13, characterized in that the direction (R) of the center of the beam (7) is set approximately tangentially to the profile center line (6) of the blade (1) on the blade edge (2,3).
EP04722146A 2003-04-27 2004-03-20 Method for rounding part edges Expired - Lifetime EP1617972B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10319020A DE10319020B4 (en) 2003-04-27 2003-04-27 Method of rounding edges on blades of turbomachinery
PCT/DE2004/000581 WO2004096493A1 (en) 2003-04-27 2004-03-20 Method for rounding part edges

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EP1617972A1 true EP1617972A1 (en) 2006-01-25
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US7950121B2 (en) 2011-05-31
DE10319020A1 (en) 2004-11-25
EP1617972B1 (en) 2007-05-09
DE10319020B4 (en) 2006-06-14
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RU2005136898A (en) 2007-06-10
DE502004003770D1 (en) 2007-06-21

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