EP1617972B1 - Method for rounding part edges - Google Patents
Method for rounding part edges Download PDFInfo
- Publication number
- EP1617972B1 EP1617972B1 EP04722146A EP04722146A EP1617972B1 EP 1617972 B1 EP1617972 B1 EP 1617972B1 EP 04722146 A EP04722146 A EP 04722146A EP 04722146 A EP04722146 A EP 04722146A EP 1617972 B1 EP1617972 B1 EP 1617972B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- stream
- edge
- suction side
- pressure
- 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.)
- Expired - Lifetime
Links
- 238000000034 method Methods 0.000 title claims abstract description 27
- 239000002245 particle Substances 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 7
- 239000007789 gas Substances 0.000 claims description 6
- 238000003754 machining Methods 0.000 claims description 4
- 238000005422 blasting Methods 0.000 claims description 2
- 239000012159 carrier gas Substances 0.000 claims description 2
- 239000012530 fluid Substances 0.000 claims description 2
- 238000005242 forging Methods 0.000 claims description 2
- 238000003801 milling Methods 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims 3
- -1 for example Substances 0.000 claims 3
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 claims 2
- 239000010936 titanium Substances 0.000 claims 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims 1
- 240000008042 Zea mays Species 0.000 claims 1
- 235000005824 Zea mays ssp. parviglumis Nutrition 0.000 claims 1
- 235000002017 Zea mays subsp mays Nutrition 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 claims 1
- 239000000956 alloy Substances 0.000 claims 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims 1
- 239000000919 ceramic Chemical class 0.000 claims 1
- 229910017052 cobalt Inorganic materials 0.000 claims 1
- 239000010941 cobalt Substances 0.000 claims 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims 1
- 150000001875 compounds Chemical class 0.000 claims 1
- 235000005822 corn Nutrition 0.000 claims 1
- 229910052593 corundum Inorganic materials 0.000 claims 1
- 229910044991 metal oxide Inorganic materials 0.000 claims 1
- 150000004706 metal oxides Chemical class 0.000 claims 1
- 229910052759 nickel Inorganic materials 0.000 claims 1
- 150000002894 organic compounds Chemical class 0.000 claims 1
- 229920003023 plastic Polymers 0.000 claims 1
- 239000004033 plastic Substances 0.000 claims 1
- 150000003839 salts Chemical class 0.000 claims 1
- 239000011780 sodium chloride Substances 0.000 claims 1
- 229910052719 titanium Inorganic materials 0.000 claims 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 229910001845 yogo sapphire Inorganic materials 0.000 claims 1
- 238000005270 abrasive blasting Methods 0.000 description 4
- 238000002474 experimental method Methods 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
Images
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 blades of turbomachines, in particular guide vanes and rotor blades of gas turbines.
- edges on blades of turbomachines may be required for a variety of reasons. These include improving the strength and / or aerodynamics and avoiding the risk of injury.
- these may be sharp edges on components that are to be rounded to the adjacent surfaces of the component.
- the edges may also form planar or spatial surfaces that connect adjacent, generally significantly larger surfaces of the component. The latter case is usually present at relatively rough prefabricated edges on fluidically active blades of turbomachines, in particular on guide vanes and rotor blades of gas turbines, in which the blade edges to the adjacent pressure and / or suction side of the blade from strength and aerodynamics aspects are to round ,
- the rounding is in the case of blade edges, which are due to the production generally relatively rough preprocessed, carried out to date largely by hand, with possibly hand-held machines, such as belt grinders, etc., are used. This is associated with a high manpower and time, and with targeted control and testing ultimately no reproducible, consistent machining result is guaranteed.
- DE 197 20 750 C1 discloses a surface treatment method in which the surface is subjected to particle irradiation. 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.
- DE 697 12 613 T2 additionally shows a method for honing cutting edges, which are processed by abrasive fluid jets with abrasive blasting agents to introduce fine grooves in the surface.
- US 3,078,546 discloses a method for rounding edges wherein the jet consists at least largely of abrasive particles.
- the object of the invention is to provide a method for rounding edges on blades of turbomachinery, which allows a significant time and personnel savings by a machine, possibly automatable operation and reproducible Results.
- the latter should be as qualitatively flawless as possible at the lowest possible reject rate.
- the jet with its center is set approximately tangentially to the profile center line of the blade at the blade edge at which the rounding is to take place.
- non-clashing surfaces which are connected for example by an edge in the form of a flat or spatial surface, such as the pressure and suction side of a rough prefabricated edge of a blade of a gas turbine
- tangents are placed on the two surfaces on such an edge and the Profile centerline set between the intersecting tangents.
- this bisector affects the profile center line of the blade at the edge, ie in the stagnation point.
- relatively small particles of 0 to 500 mesh size preferably 180 to 320 mesh size, are used.
- the method generates a material removal for rounding and prevents cracks or roughness on the surfaces.
- the beam is generated by means of a nozzle with a defined exit diameter and defined exit angle.
- the relative movement between nozzle and component can preferably take place in a defined, variable distance between nozzle and blade edge.
- the distance is generally adapted in the case of flat edges with varying width over their length in a corresponding manner continuously.
- the direction of the center of the jet to the profile center line of the blade at the blade edge can be set at an angle ⁇ and / or set laterally offset relative to the profile center line in the direction of the pressure or suction, for example.
- Aerodynamics form desired contour asymmetries on the edge to be rounded.
- 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 in the best possible way to the desired contour. This also assumes that the blade edges 2, 3, i. the leading edge and the trailing edge of the blade 1, the adjacent surfaces, i. the pressure and suction side 4.5, aerodynamically connect. In addition to the aerodynamic requirements, aspects of strength and wear also play an important role in the blade edges 2, 3. Typically, the leading and trailing edges of blades are designed to be rounded to meet all these requirements.
- Blades having a relatively thin profile and relatively acute entry and exit edges such as, in particular, compressor blades of axial compressors, are often manufactured by forging and / or milling and / or electrochemical machining (ECM), wherein the blade edges are initially geometrically made relatively coarse, i. with flat surfaces, corners, bevels etc.
- ECM electrochemical machining
- the large-area pressure and suction sides 4.5 often correspond relatively well to the desired contour, so that there, if any, only a fine machining with little or no material removal is necessary.
- the prefabricated entry and exit edges are rounded in such a way that they pass without kinks, steps or other impurities in the pressure and suction sides 4,5.
- FIG. 1 shows a nozzle 8 of a jet device, not shown, from which a jet 7 emerges, which consists of abrasive particles and a carrier gas or a carrier liquid. At least a significant portion of the abrasive particles impinges at high speed perpendicular or approximately perpendicular to the only pre-machined, more or less still angular blade edge 2 whose initial state is indicated by dashed lines in Figure 1.
- the center of the beam direction R runs here tangentially to the profile center line 6 of the blade 1 at the blade leading edge 2 and thus at least approximately corresponds to the later flow during operation.
- an asymmetric removal with focus on the pressure or suction side can be achieved, which may be useful in certain circumstances.
- 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 beam 7, the jet direction R, and the local exposure time as a function of the blade edge parallel, relative feed rate between the nozzle 8 and the component 1.
- factors are to be optimized depending on the blade geometry and the blade material, which usually requires practical experiments will be. If, for example, the distance between the blade edge 2, 3 and the nozzle 8 is too small, a concave hollowing of the blade edge 2, 3 with maximum removal in the region of the stagnation point may occur instead of a rounding, which must be avoided at all costs.
- the inventive method is in principle applicable to all types of blades of turbomachinery.
Abstract
Description
Die Erfindung betrifft ein Verfahren zum Verrunden von Kanten an Schaufeln von Turbomaschinen, insbesondere von Leit- und Laufschaufeln von Gasturbinen.The invention relates to a method for rounding edges on blades of turbomachines, in particular guide vanes and rotor blades of gas turbines.
Das Verrunden von Kanten an Schaufeln von Turbomaschinen, insbesondere von Leit- und Laufschaufeln von Gasturbinen, 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.The rounding of edges on blades of turbomachines, in particular guide vanes and rotor blades of gas turbines, may be required for a variety of reasons. These include improving the strength and / or aerodynamics and avoiding the risk of injury. Depending on the component, these may be sharp edges on components that are to be rounded to the adjacent surfaces of the component. Alternatively, the edges may also form planar or spatial surfaces that connect adjacent, generally significantly larger surfaces of the component. The latter case is usually present at relatively rough prefabricated edges on fluidically active blades of turbomachines, in particular on guide vanes and rotor blades of gas turbines, in which the blade edges to the adjacent pressure and / or suction side of the blade from strength and aerodynamics aspects are to round ,
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 Kontrolle und Prüfung letztlich kein reproduzierbares, gleichbleibendes Bearbeitungsergebnis gewährleistet ist.The rounding is in the case of blade edges, which are due to the production generally relatively rough preprocessed, carried out to date largely by hand, with possibly hand-held machines, such as belt grinders, etc., are used. This is associated with a high manpower and time, and with targeted control and testing ultimately no reproducible, consistent machining result is guaranteed.
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 surface treatment method in which the surface is subjected to particle irradiation. 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.
Außerdem 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 also known to roughen surfaces before coating operations by abrasive blasting to clean the surfaces and improve adhesion to the layer. DE 697 12 613 T2 additionally shows a method for honing cutting edges, which are processed by abrasive fluid jets with abrasive blasting agents to introduce fine grooves in the surface.
US 3,078,546, offenbart ein Verfahren zum Verrunden von Kanten wobei der Strahl zumindest großteils aus abrasiven Partikeln besteht.US 3,078,546 discloses a method for rounding edges wherein the jet consists at least largely of abrasive particles.
Angesichts dieser bekannten Verfahren und ihrer Nachteile bzw. ihrer anwendungstechnischen Grenzen besteht die Aufgabe der Erfindung darin, ein Verfahren zum Verrunden von Kanten an Schaufeln von Turbomaschinen 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 limits, the object of the invention is to provide a method for rounding edges on blades of turbomachinery, which allows a significant time and personnel savings by a machine, possibly automatable operation and reproducible Results. The latter should be as qualitatively flawless as possible at the lowest possible reject rate.
Die Aufgabe wird durch die in Patentanspruch 1 gekennzeichneten Merkmale gelöst.The object is solved by the features characterized in
Überraschenderweise hat sich herausgestellt, dass durch abrasives Strahlen unter Beachtung definierter Bearbeitungsparameter und Düsendefinitionen relativ genaue, gerundete Oberflächengeometrien an den Kanten von relativ grob vorbearbeiteten Schaufeln herstellbar sind. Die Funktionstüchtigkeit dieses Verfahrens sowie seine Reproduzierbarkeit wurden in Versuchen bestätigt.Surprisingly, it has been found that relatively accurate, rounded surface geometries can be produced at the edges of relatively rough pre-machined blades by abrasive blasting, taking into account defined processing parameters and nozzle definitions. The functionality of this method and its reproducibility have been confirmed in experiments.
Beim erfindungsgemäßen Verfahren wird der Strahl mit seiner Mitte etwa tangential zur Profilmittellinie der Schaufel an der Schaufelkante, an der die Verrundung erfolgen soll, eingestellt. 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 Profilmittellinie 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 jet with its center is set approximately tangentially to the profile center line of the blade at the blade edge at which the rounding is to take place. In non-clashing surfaces, which are connected for example by an edge in the form of a flat or spatial surface, such as the pressure and suction side of a rough prefabricated edge of a blade of a gas turbine, tangents are placed on the two surfaces on such an edge and the Profile centerline set between the intersecting tangents. In the latter case, one to the pressure and suction side of a blade to the verrandenden edge this bisector affects the profile center line of the blade at the edge, ie in the stagnation point.
Zur Reduzierung einer etwaigen Nachbearbeitung der verrundeten Kanten werden relativ kleine Partikel mit einer Größe von 0 bis 500 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 reworking of the rounded edges, relatively small particles of 0 to 500 mesh size, preferably 180 to 320 mesh size, are used. As a result, the method generates a material removal for rounding and prevents cracks or roughness on the surfaces.
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, for generating a beam with defined geometry and energy in terms of cross-section, shape, etc., the beam is generated by means of a nozzle with a defined exit diameter and defined exit 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 nozzle and component can preferably take place in a defined, variable distance between nozzle and blade edge.
Der Abstand wird im allgemeinen bei flächigen Kanten mit sich über deren Länge ändernder Breite in entsprechender Weise stufenlos angepasst.The distance is generally adapted in the case of flat edges with varying width over their length in a corresponding manner continuously.
Bevorzugt kann die Richtung der Mitte des Strahls zur Profilmittellinie der Schaufel an der Schaufelkante in einem Winkel β 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.Preferably, the direction of the center of the jet to the profile center line of the blade at the blade edge can be set at an angle β and / or set laterally offset relative to the profile center line in the direction of the pressure or suction, for example. Aerodynamics form desired contour asymmetries on the edge to be rounded.
In den Unteransprüchen sind bevorzugte Ausgestaltungen sowie Anwendungen des Verfahrens und der Vorrichtung beschrieben.In the subclaims preferred embodiments and applications of the method and the device are described.
Die Erfindung wird nachfolgend anhand der Zeichnung mit Bezug auf Ausführungsbeispiele näher erläutert:
- Fig. 1
- zeigt in vereinfachter, nicht maßstäblicher Darstellung die Bearbeitung einer Eintrittskante einer Schaufel;
- Fig. 2
- zeigt in entsprechender Darstellung wie Fig. 1 ein alternatives Ausführungsbeispiel für die Bearbeitung.
- Fig. 1
- shows in simplified, not to scale representation, the processing of an entrance edge of a blade;
- Fig. 2
- shows in a similar representation as Fig. 1 shows an alternative embodiment for processing.
Anwendungsfälle liegen insbesondere überall dort, wo scharfe Kanten an Schaufeln zu angrenzenden Oberflächen hin zu verrunden sind oder wo vorgefertigte Kanten zur Gestaltung des Übergangs zwischen angrenzenden Oberflächen mit definierter Gestalt zu verrunden sind.Applications are especially where sharp edges on blades are to be rounded off to adjacent surfaces or where prefabricated edges to shape the transition between adjacent surfaces with a defined shape to round.
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 with reference to an edge on a fluidically active blade of a gas turbine, wherein a relatively rough prefabricated blade edge is to be rounded 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
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 having a relatively thin profile and relatively acute entry and exit edges, such as, in particular, compressor blades of axial compressors, are often manufactured by forging and / or milling and / or electrochemical machining (ECM), wherein the blade edges are initially geometrically made relatively coarse, i. with flat surfaces, corners, bevels etc. The large-area pressure and suction sides 4.5 often correspond relatively well to the desired contour, so that there, if any, only a fine machining with little or no material removal is necessary. Thus, the prefabricated entry and exit edges are rounded in such a way that they pass without kinks, steps or other impurities in the pressure and
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. Zumindest 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 β 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 processing method with targeted removal of the blade material. FIG. 1 shows a
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.The removal result depends on several factors, such as the jet pressure, the exit angle α of the
Das erfindungsgemäße Verfahren ist prinzipiell bei allen Arten von Schaufeln von Turbomaschinen anwendbar.The inventive method is in principle applicable to all types of blades of turbomachinery.
- 11
- Bauteil/SchaufelComponent / blade
- 22
- Kante/SchaufelkanteEdge / blade edge
- 33
- Kante/SchaufelkanteEdge / blade edge
- 44
- Oberfläche/DruckseiteSurface / printed page
- 55
- Oberfläche/SaugseiteSurface / suction side
- 66
- Winkelhalbierende/ProfilmittellinieBisecting / profile center line
- 77
- Strahlbeam
- 88th
- Düsejet
- AA
- Abstanddistance
- DD
- AustrittsdurchmesserOutlet diameter
- RR
- Strahlrichtungbeam direction
- αα
- Austrittswinkelexit angle
- ββ
- Winkelangle
Claims (13)
- Method for rounding edges on blades of turbomachines having a pressure side (4), a suction side (5) and a profile centre line (9) which extends therebetween, in particular vanes and rotor blades of gas turbines, a prefabricated blade edge (2, 3) being intended to be rounded towards the adjacent pressure side (4) and suction side (5) of the blade (1), a stream (7) at least largely comprising abrasive particles being adjusted with the centre thereof substantially tangential relative to the profile centre line (6) of the blade (1) at the blade edge (2, 3), and the stream (7) and the blade edge (2, 3) being moved relative to each other along the blade edge (2, 3) in such a manner that the rounding is carried out towards the pressure side (4) and suction side (5).
- Method according to claim 1, characterised in that the stream (7) comprises abrasive particles, a carrier gas and/or a carrier fluid, such as, for example, water.
- Method according to claim 1 or 2, characterised in that metal oxides, such as Al2O3 or SiO, other ceramic compounds, salts, such as NaCl, or organic compounds, such as plastics materials or ground corn, are used as abrasive particles.
- Method according to any one of the preceding claims, characterised in that particles are used having a size of from 0 to 500 mesh, preferably from 180 to 320 mesh.
- Method according to any one of the preceding claims, characterised in that the stream (7) is produced by means of a nozzle (8) having a defined outlet diameter (D) and a defined outlet angle (α), in particular a portion of the stream cross-section being kept free of particles at least to a large extent.
- Method according to any one of the preceding claims, characterised in that the pressure of the stream (7) is set to approximately from 3 to 3.5 bar.
- Method according to any one of the preceding claims, characterised in that the relative movement of the nozzle (8) and the component (1) is carried out with a defined variable spacing (A) between the nozzle (8) and the edge (2, 3).
- Method according to any one of the preceding claims, characterised in that, following the abrasive processing operation, at least one other processing operation, such as abrading or shot-blasting, is carried out.
- Method according to any one of the preceding claims, characterised in that it is used for processing components which are prefabricated by means of forging and/or milling and/or electrochemical machining (ECM), in particular blades (1), composed of alloys based on titanium (Ti), nickel (Ni) or cobalt (Co), in particular compressor blades of the axial type.
- Method according to any one of the preceding claims, characterised in that it is used for the processing of individual blades, blade segments, or integrally bladed discs or rings.
- Method according to any one of the preceding claims, characterised in that the direction (R) of the centre of the stream (7) is adjusted so as to be positioned at an angle (β) relative to the profile centre line (6) of the blade (1) at the blade edge (2, 3) and/or to be laterally offset relative to the profile centre line (6) in the direction towards the pressure or suction side.
- Method according to any one of the preceding claims, characterised in that the blade edges (2, 3) to be rounded have a face which is at least substantially transverse relative to the adjacent pressure and/or suction side (4, 5) and more or less angular transitions to the pressure and/or suction side (4, 5) and the stream (7) is directed perpendicularly or substantially perpendicularly on the face of the blade edge (2, 3).
- Method according to claim 12, characterised in that the direction (R) of the centre of the stream (7) is adjusted substantially tangentially relative to the profile centre line (6) of the blade (1) at the blade edge (2, 3).
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1617972A1 EP1617972A1 (en) | 2006-01-25 |
| EP1617972B1 true EP1617972B1 (en) | 2007-05-09 |
Family
ID=33393920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP04722146A Expired - Lifetime EP1617972B1 (en) | 2003-04-27 | 2004-03-20 | Method for rounding part edges |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US7950121B2 (en) |
| EP (1) | EP1617972B1 (en) |
| DE (2) | DE10319020B4 (en) |
| RU (1) | RU2348505C2 (en) |
| WO (1) | WO2004096493A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005054866A1 (en) * | 2005-11-17 | 2007-05-31 | Mtu Aero Engines Gmbh | Method for producing metallic components, in particular for turbomachinery, with small edge radii |
| US8613641B2 (en) * | 2008-10-22 | 2013-12-24 | Pratt & Whitney Canada Corp. | Channel inlet edge deburring for gas diffuser cases |
| EP2465636A1 (en) | 2010-12-16 | 2012-06-20 | MTU Aero Engines AG | Method and device for forming a section of a component with a predefined contour |
| US10155298B2 (en) * | 2011-12-21 | 2018-12-18 | Sikorsky Aircraft Corporation | Alpha case removal process for a main rotor blade spar |
| US9162301B2 (en) | 2012-08-06 | 2015-10-20 | General Electric Company | Electrochemical machining tools and methods |
| US8906221B2 (en) | 2012-08-06 | 2014-12-09 | General Electric Company | Electrochemical grinding tool and method |
| GB2506357B (en) * | 2012-09-26 | 2015-01-28 | Rolls Royce Plc | Machining of an article |
| JP6253533B2 (en) * | 2014-07-01 | 2017-12-27 | 株式会社神戸製鋼所 | Cutting tool manufacturing method |
| RU2757171C1 (en) * | 2021-04-06 | 2021-10-11 | Общество с ограниченной ответственностью Управляющая компания "Алтайский завод прецизионных изделий" | Method for shot blasting of high pressure fuel pump plunger bushings |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3078546A (en) * | 1960-06-13 | 1963-02-26 | Bruce E Kiernan | Cutting tool |
| EP0616564B1 (en) * | 1991-12-11 | 1996-09-18 | DIAT, Christian | Method for micro-cleaning a support and apparatus for implementing same |
| KR0127666B1 (en) * | 1992-11-25 | 1997-12-30 | 모리시다 요이찌 | Ceramic electronic device and method of producing the same |
| US5709587A (en) * | 1996-03-25 | 1998-01-20 | Kennametal Inc. | Method and apparatus for honing an elongate rotary tool |
| DE19720756C1 (en) * | 1997-05-07 | 1998-09-24 | Tacr Turbine Airfoil Coating A | Method for aqua-blasting component surfaces |
-
2003
- 2003-04-27 DE DE10319020A patent/DE10319020B4/en not_active Expired - Fee Related
-
2004
- 2004-03-20 DE DE502004003770T patent/DE502004003770D1/en not_active Expired - Lifetime
- 2004-03-20 WO PCT/DE2004/000581 patent/WO2004096493A1/en active IP Right Grant
- 2004-03-20 US US10/554,612 patent/US7950121B2/en not_active Expired - Fee Related
- 2004-03-20 RU RU2005136898/02A patent/RU2348505C2/en not_active IP Right Cessation
- 2004-03-20 EP EP04722146A patent/EP1617972B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| RU2005136898A (en) | 2007-06-10 |
| WO2004096493A1 (en) | 2004-11-11 |
| DE10319020B4 (en) | 2006-06-14 |
| US20070050977A1 (en) | 2007-03-08 |
| US7950121B2 (en) | 2011-05-31 |
| DE10319020A1 (en) | 2004-11-25 |
| RU2348505C2 (en) | 2009-03-10 |
| DE502004003770D1 (en) | 2007-06-21 |
| EP1617972A1 (en) | 2006-01-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1914323B1 (en) | Method for introducing residual compressive stresses by shot peening | |
| EP2093021B1 (en) | Method and apparatus for controlled shot-peening of blisk blades | |
| EP2794181B1 (en) | Device for recontouring a gas turbine blade | |
| EP2353772B1 (en) | Method and device for fixing blisk blades to a surface | |
| CH703747A2 (en) | Component with at least one curved film cooling hole, and methods for their preparation. | |
| EP2106876A1 (en) | Method for aerodynamically shaping the leading edge of blisk blades | |
| EP2093012A2 (en) | Method and tooling for machining the annulus of a gas-turbine rotor provided with integrally formed blades | |
| DE4341869A1 (en) | Removal of hard coatings by ultra high pressure jets - involves nozzle set at certain distance from surface and producing flat pressurised jet | |
| EP1617972B1 (en) | Method for rounding part edges | |
| EP2794180A1 (en) | Device for recontouring a gas turbine blade | |
| DE19807637A1 (en) | Friction welding process for blading a rotor for a turbomachine | |
| WO2010046353A1 (en) | Manufacturing method for closed impellers | |
| EP2099585B1 (en) | Device and method for the surface peening of a component of a gas turbine | |
| EP2125292B1 (en) | Method and device for the surface peening of a partial element of a component of a gas turbine | |
| EP2229258B1 (en) | Method for producing integrally blade-mounted rotors | |
| EP1954421B1 (en) | Method for producing metallic components, particularly for turbo machines, having small edge radii, and component produced therewith | |
| EP3733348A1 (en) | Method for smoothing the surface of a workpiece | |
| DE102008014725A1 (en) | Method for producing a welded blisk drum | |
| DE102016100663A1 (en) | Apparatus and method for beam hardening of surface areas, in particular fir tree profiles | |
| EP3222812A1 (en) | Method for making or repairing a rotor blade, rotor blade, method for manufacturing or repairing a housing for a fluid flow machine and said housing | |
| EP2465636A1 (en) | Method and device for forming a section of a component with a predefined contour | |
| DE102020101472A1 (en) | Method and set of replacement parts for repairing a titanium aluminide low pressure turbine blade |
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: 20051018 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR |
|
| AX | Request for extension of the european patent |
Extension state: AL LT LV MK |
|
| DAX | Request for extension of the european patent (deleted) | ||
| RBV | Designated contracting states (corrected) |
Designated state(s): DE FR GB |
|
| GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
| GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
| REF | Corresponds to: |
Ref document number: 502004003770 Country of ref document: DE Date of ref document: 20070621 Kind code of ref document: P |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20070813 |
|
| ET | Fr: translation filed | ||
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed |
Effective date: 20080212 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 14 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20180326 Year of fee payment: 15 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20180326 Year of fee payment: 15 |
|
| GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190320 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190320 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190331 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230320 Year of fee payment: 20 |
|
| REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 502004003770 Country of ref document: DE |