WO2019192635A1 - Procédé de fabrication d'une aube d'une turbomachine - Google Patents

Procédé de fabrication d'une aube d'une turbomachine Download PDF

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Publication number
WO2019192635A1
WO2019192635A1 PCT/DE2019/000093 DE2019000093W WO2019192635A1 WO 2019192635 A1 WO2019192635 A1 WO 2019192635A1 DE 2019000093 W DE2019000093 W DE 2019000093W WO 2019192635 A1 WO2019192635 A1 WO 2019192635A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
blank
turbomachine
positioning
edge
Prior art date
Application number
PCT/DE2019/000093
Other languages
German (de)
English (en)
Inventor
Nicole Feiling
Roland Huttner
Max Niegl
Markus ZEIS
Original Assignee
MTU Aero Engines AG
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 AG filed Critical MTU Aero Engines AG
Publication of WO2019192635A1 publication Critical patent/WO2019192635A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/10—Working turbine blades or nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H11/00—Auxiliary apparatus or details, not otherwise provided for
    • B23H11/003—Mounting of workpieces, e.g. working-tables
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H3/00—Electrochemical machining, i.e. removing metal by passing current between an electrode and a workpiece in the presence of an electrolyte

Definitions

  • the present invention relates to a method for producing a blade for a turbomachine.
  • the turbomachine may, for example.
  • the turbomachine is divided into compressor, combustion chamber and turbine.
  • the turbomachine is divided into compressor, combustion chamber and turbine.
  • the turbine has several stages, each of which is made up of a guide vane ring and a downstream rotor blade ring. In the individual stages, energy is proportionately withdrawn from the flowing hot gas and converted into a rotation of the rotor blade rings (this can then be used, for example, at least proportionally to drive the compressor).
  • Each blade ring is constructed from a plurality of blades, which are arranged circumferentially successively.
  • the blade in the hot gas duct (turbine) or in the compressor gas duct (compressor) is arranged.
  • a respective airfoil has an inflow and outflow edge, also referred to as leading and trailing edges. Between these edges extend in each case the side surfaces of the airfoil, which form the suction and the pressure side with a corresponding curvature.
  • the blades usually an inner shroud or a blade root on, radially outside an outer shroud can be arranged (which, however, for example, is not mandatory for blades).
  • the present invention is based on the technical problem of specifying a particularly advantageous method for producing a blade for a turbomachine.
  • the blade is worked out in its final form (with inflow and outflow edge) materi alabtragend from a blank.
  • a first step (i) in this case an intermediate form is exposed, from which then in a second step (ii) the final shape is machined out by electrochemical removal.
  • the intermediate form produced in the first step (i) is precontoured, namely, the material is removed from the blank in such a way to the inflow and / or outflow edge that the outer wall surface of the intermediate form thus exposed has a predefined distance from the corresponding edge.
  • the blank is first brought into the precontoured form.
  • the edges of the airfoil can be critical with respect to the electrochemical removal, which is why at any rate a predefined distance is set there, preferably both at the inflow and at the outflow edge (see below in detail).
  • precontouring according to the first step (i) opens up the possibility of working out the final shape by electrochemical removal in the second step (ii).
  • the component may also be further processed overall (for example, smoothing of the surface, grinding, etc.), but ideally, it is no longer necessary to process the flow. and trailing edge are worked out or defined in a separate step.
  • the process conditions within a respective component and also from component to component can be homogenized, which ultimately also permits a high degree of automation.
  • the distance between the outer wall surface of the intermediate mold and the respective edge can, for example, be taken in an axis-parallel section along a tangential extension of the skeleton line of the airfoil.
  • the skeleton line is extended straightforward (tangential to the skeleton line) and the distance between the leading edge of the final shape and the front outer wall surface of the intermediate form is taken along this line.
  • the skeleton line is extended backwards analogously away from the trailing edge and the distance to the rear outer wall surface of the intermediate form is taken along this line.
  • the electrochemical removal in the second step (ii) preferably takes place simultaneously on both side surfaces of the airfoil. In each case, a large area, corresponding to the profile of the airfoil, is formed on each side surface. placed electrode. Overall, the erfmdungswashe procedure can also reduce the processing time.
  • the outer wall surface which has been precontoured in the first step (i) has a rectilinear extent in an axis-parallel section.
  • the precontouring z may be relatively easy to incorporate, as well as advantages in terms of inspection (eg, optical inspection) of the intermediate form prior to the second step (ii).
  • the removal of material in the first step (i) may, for example, also be carried out by water jet cutting or spark erosion, in particular wire cutting.
  • the material-removing machining in the first step (i) is a machining, which is particularly preferably carried out with a tool having a geometrically determined cutting edge.
  • machining in a cutting tool can be advantageous, in which the material of the blank is then removed from the front and / or the rear outer wall surface and, for example, also a positioning and / or contact structure is produced becomes.
  • deburred after the machining This can help with the subsequent electrochemical removal, for example. Field tips and thus irregularities in the removal preventions.
  • the blank is clamped during the machining in the first step (i) on the blade, on its soflä- Chen.
  • the inflow and outflow edges of the machining process are accessible and, on the other hand, parts arranged radially inside or outside the blade leaf can also be processed without retooling (attachment of contact surfaces or positioning marks).
  • the blank may, for example, also be a formed part, for example produced by casting. In a preferred embodiment, it is a formed part, preferably a forged part. In this case, there may be a varying geometry from component to component in particular, for which reason conversely the advantages of the present subject matter come to bear in particular.
  • the intermediate form for the second step (ii) is provided with a positioning structure.
  • This is worked out of the blank in the first step (i), in which also the outer wall surfaces or surfaces are exposed at the edge (s). This therefore takes place in the course of the same process, for example when the blank is clamped to the blade as described above.
  • the integration into the same setup process is advantageous insofar as the outer wall surface (s) and the positioning structure can be introduced relative to one another with high accuracy, which also increases the accuracy in the subsequent electrochemical removal.
  • the positioning structure is arranged offset radially to the blade, particularly preferably radially within the inner cover strip or outside the outer cover strip.
  • the positioning structure preferably has a plurality of positioning marks, wherein in each case at least one positioning mark is provided both radially inside the blade leaf and radially outside thereof. In general, for example, webs or edges can also be used as positioning marks.
  • holes are introduced as positioning marks, for example through holes.
  • the holes can be introduced, for example, in each case as a bore, at this centering hole, the intermediate form can then be clamped for the electrochemical ablation.
  • a contact structure is also exposed, via which the intermediate form is contacted during electrochemical ablation.
  • the exposure of the contact structure may, for example, be advantageous insofar as large contact surfaces can be achieved over a large area.
  • the contact surfaces can also be used as date areas, ie provided with a marking (eg lot number, etc.) for internal processing.
  • the contact structure has a plurality of contact surfaces, wherein in each case at least one of the contact surfaces is arranged both radially inwardly and radially outside of the airfoil. During electrochemical removal, the intermediate form is then contacted correspondingly on both sides of the blade.
  • those parts of the intermediate mold on which the contact surfaces or positioning marks are provided are removed after the electrochemical removal.
  • the contact surfaces and positioning marks are introduced to parts of the blank, which are then no longer part of the finished blade.
  • material is removed from the blank both at the leading edge and at the trailing edge.
  • a defined outer wall surface is exposed both at the inflow and at the outflow edge.
  • the invention also relates to the production of a module for a Strömungsmaschi- ne, which has one or more blade rings. In this case, at least some of the blades are produced in a presently described, two-stage manner. Furthermore, the invention also relates to the production of a turbomachine, in particular an aircraft engine, wherein at least some of the blades are produced in a manner described here.
  • a turbomachine in particular an aircraft engine
  • Figure 1 shows a schematic representation of a turbofan engine in an axial section
  • FIG. 2 shows a blank of a blade in a side view
  • Figure 3 shows the blank according to Figure 2 in a section, wherein also a final shape of the blade is marked;
  • Figure 4 shows the blank according to Figures 2 and 3 in an axis-parallel
  • FIG. 5 shows an intermediate shape produced from the blank according to FIGS. 2-4 in an axis-parallel section analogous to FIG. 4;
  • FIG. 6 shows the intermediate form according to FIG. 5 in a side view;
  • Figure 7 shows the intermediate form according to Figures 5 and 6 in a section.
  • turbomachine 1 shows a turbomachine 1 in a schematic axial section (relative to a longitudinal axis 2), specifically a turbofan engine.
  • the turbomachine 1 is divided functionally into compressor la, combustion chamber 1b and turbine lc.
  • compressor la the intake air is compressed over several stages, in the combustion chamber lb it is burnt with mixed kerosene, the expansion then takes place in the turbine lc, also over several stages.
  • both in the compressor la and in the turbine lc each stage is composed of a master and a Blade set up, each blade ring is composed of several circumferentially successive blades together.
  • FIG. 2 shows a blank 20 from which, in the following, a blade is worked out in a material-removing manner.
  • the blank 20 is made by forming, namely as a forging.
  • FIGS. 3 and 4 An end shape of the blade 30 is indicated by dashed lines in FIGS. 3 and 4.
  • the blade 30 has an airfoil 30.1 and an inner shroud 30.2 and an outer shroud 30.3. It can be seen from FIG. 4 that the blade 30.1 has a leading edge 30.1.1 and a trailing edge 30.1.2, as well as two side surfaces, namely a suction side surface 30.1.3 and a pressure side surface 30.1.4.
  • FIG. 5 shows, in an axis-parallel section analogous to FIG. 4, an intermediate mold 50 which is machined out of the blank 20 by cutting material removal.
  • material is removed both to the leading edge 30.1.1 and to the trailing edge 30.1.2, so that the respective exposed outer wall surface 51.1, 51.2 has a defined distance 52.1, 52.2 to the respective edge 30.1.1, 30.1.2 ,
  • the final shape is machined out of the intermediate mold 50 by electrochemical ablation, which is quite possible on account of this precontouring.
  • FIG. 6 also shows the intermediate mold 50, wherein a positioning structure 60 and a contact structure 61 can be seen radially inside and outside the blade.
  • the positioning structure 60 comprises a plurality of positioning marks 60.1-60.3, which are presently introduced as through-holes, also compare the synopsis with Figure 7.
  • the intermediate mold 50 can be clamped for the electrochemical ablation, they are shared with the exposure the outer wall surfaces 51.1, 51.2 introduced machined.
  • the contact structure 61 which has contact surfaces 61.1, 61.2 on both sides of the airfoil.
  • the intermediate mold 50 can be electrically contacted over a large area and reliably during electrochemical removal. LIST OF REFERENCE NUMBERS

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un procédé de fabrication d'une aube (10) d'une turbomachine (1), l'aube (30) présentant sous sa forme finale un aubage (30.1) comportant un bord d'attaque (30.1.1) et un bord de fuite (30.1.2) ainsi que des surfaces latérales (30.1.3, 30.1.4) qui s'étendent entre lesdits bords (30.1.1, 30.1.2). Selon le procédé, la forme finale est usinée à partir d'une ébauche (20) en ce que i.) une forme intermédiaire (50) est tout d'abord usinée à partir de l'ébauche (20) par enlèvement de matière et ii.) la forme définitive est ensuite usinée à partir de la forme intermédiaire (50) par usinage électrochimique. Dans l'étape selon le point i.), la matière est enlevée de l'ébauche (20) en direction d'un des bords (30.1.1, 30.1.2) de la forme finale dans une quantité telle qu'une surface de paroi extérieure (51.1, 51.2) de la forme intermédiaire (50) qui est ensuite amenée à l'étape selon le point ii.) présente une distance (52.1, 52.2) prédéfinie par rapport auxdits bords (30.1.1, 30.1.2).
PCT/DE2019/000093 2018-04-03 2019-04-01 Procédé de fabrication d'une aube d'une turbomachine WO2019192635A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102018002752 2018-04-03
DE102018002752.0 2018-04-03
DE102018217147.5A DE102018217147A1 (de) 2018-04-03 2018-10-08 Verfahren zum herstellen einer schaufel für eine strömungsmaschine
DE102018217147.5 2018-10-08

Publications (1)

Publication Number Publication Date
WO2019192635A1 true WO2019192635A1 (fr) 2019-10-10

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PCT/DE2019/000093 WO2019192635A1 (fr) 2018-04-03 2019-04-01 Procédé de fabrication d'une aube d'une turbomachine

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WO (1) WO2019192635A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11623290B2 (en) 2018-10-05 2023-04-11 Raytheon Technologies Corporation Method of machining gas turbine engine components

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3309294A (en) * 1962-05-07 1967-03-14 Rolls Royce Electrolytic shaping of metallic aerofoil blades
GB2021645A (en) * 1978-05-30 1979-12-05 Rolls Royce Electrochemical machining aerofoil blades
EP0327657A1 (fr) * 1988-02-11 1989-08-16 Leistritz Aktiengesellschaft Procédé de fabrication d'une roue à aubes
US5527435A (en) * 1993-09-16 1996-06-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for clamping a part and application to the machining of a turbine engine blade by electrochemistry
EP2022587A1 (fr) * 2007-08-06 2009-02-11 General Electric Company Usinage par électroérosion des aubes de turbine
DE102008004776A1 (de) * 2008-01-17 2009-07-23 Mtu Aero Engines Gmbh Verfahren zur Herstellung von integral beschaufelten Rotoren
EP2246139A1 (fr) * 2009-04-03 2010-11-03 United Technologies Corporation Appareil et procédé d'usinage de décharge d'électrode et procédé d'usinage d'une pièce

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3309294A (en) * 1962-05-07 1967-03-14 Rolls Royce Electrolytic shaping of metallic aerofoil blades
GB2021645A (en) * 1978-05-30 1979-12-05 Rolls Royce Electrochemical machining aerofoil blades
EP0327657A1 (fr) * 1988-02-11 1989-08-16 Leistritz Aktiengesellschaft Procédé de fabrication d'une roue à aubes
US5527435A (en) * 1993-09-16 1996-06-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for clamping a part and application to the machining of a turbine engine blade by electrochemistry
EP2022587A1 (fr) * 2007-08-06 2009-02-11 General Electric Company Usinage par électroérosion des aubes de turbine
DE102008004776A1 (de) * 2008-01-17 2009-07-23 Mtu Aero Engines Gmbh Verfahren zur Herstellung von integral beschaufelten Rotoren
EP2246139A1 (fr) * 2009-04-03 2010-11-03 United Technologies Corporation Appareil et procédé d'usinage de décharge d'électrode et procédé d'usinage d'une pièce

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11623290B2 (en) 2018-10-05 2023-04-11 Raytheon Technologies Corporation Method of machining gas turbine engine components

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Publication number Publication date
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