EP1614487B1 - Verfahren zur geometrischen Konstruktion eines Grats eines geschmiedeten Werkstückes mit komplexer Form - Google Patents

Verfahren zur geometrischen Konstruktion eines Grats eines geschmiedeten Werkstückes mit komplexer Form Download PDF

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Publication number
EP1614487B1
EP1614487B1 EP05105968A EP05105968A EP1614487B1 EP 1614487 B1 EP1614487 B1 EP 1614487B1 EP 05105968 A EP05105968 A EP 05105968A EP 05105968 A EP05105968 A EP 05105968A EP 1614487 B1 EP1614487 B1 EP 1614487B1
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EP
European Patent Office
Prior art keywords
sections
flash
blade
land
gutter
Prior art date
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Active
Application number
EP05105968A
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English (en)
French (fr)
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EP1614487A1 (de
Inventor
Jean-Claude Plazanet
Yvon Marie Joseph Louesdon
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Publication of EP1614487A1 publication Critical patent/EP1614487A1/de
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
    • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
    • B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
    • B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
    • 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
    • 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
    • Y10T29/49764—Method of mechanical manufacture with testing or indicating
    • Y10T29/49771—Quantitative measuring or gauging

Definitions

  • the present invention relates to the geometrical construction of the engravings of the press dies and more precisely the burrs cords and their clearances provided on the periphery of the etchings for forging complex parts, here turbomachine blades.
  • Burr is the means by which the filling of the engraving by the material is perfected during the forging of the pieces. By providing a suitable burr cord, it is ensured that the enclosed material has an obligation to first fill the cavity of the etching before escaping. The burr cord allows the evacuation of surplus material at the end of the engraving.
  • This optimization depends in particular on the temperature of the part and the tools, their coefficient of mutual friction, and the shape of the blank of the part before the forging.
  • the definition of the shape of the forged part is used in particular.
  • various bead bead parameter determinations are made by varying the said parameters in the reference sections.
  • the blade of the turbomachine blade having a leading edge and a trailing edge, the sections of the burrs and clearance corresponding to the leading and trailing edges are determined simultaneously.
  • the intermediate sections of the burr cord and its clearance can thus be largely calculated automatically, which allows a considerable saving of time.
  • a polynomial interpolation is used.
  • the stripping reliefs are rectified in order firstly to prevent the creation of undercuts or substantially vertical surfaces which can weaken the matrix, and secondly to reduce the differences in the height of the apex. 'dawn.
  • a turbine engine blade blade 10 comprises the two intrados and extrados surfaces comprised between a leading edge BA and a trailing edge BF, on the one hand, and a blade tip 9 and a blade root 8, on the other hand.
  • the dawn consists of a material 1 forged by means of a forging machine (not shown) of given power and acting on a press tool consisting of two matrices which will be evoked by the following.
  • the blade 10 is geometrically defined by plane Si sections located in predetermined planes Pi, at the intersection of these planes with the intrados 2 "and the extrados 2 '.
  • a first initial step it is necessary to choose at least three planes 8, 10, 9 of reference Pa, Pb and Pc, providing three sections Sa, Sb, Sc.
  • the three reference sections make it possible to determine parameters of cord construction. This is what has been done in FIG. 2, the three reference sections being the sections S2, S6, S11 corresponding to the foot, middle and top of the blade.
  • the burr cords 5 are geometrically constructed and their corresponding clearance 6 only for the sections Sa, Sb and Sc, on the BA side and on the BF side.
  • the construction is based on the geometric elements shown in FIG. 3, on which the intersections of the intrados 2 "and the extrados 2 'are recognized with a reference plane Pj taken from the set Pa, Pb and Pc, and the trace on Pj of the leading edge BA or leakage BF.
  • the segments 15 'defined by the points 13'-14', 20 'defined by the points 14'-16', the right half 21 'on the one hand, and the segments 15 "defined by the points 13" -14 " , 20 “defined by the points 14" -16 ", the half-right 21” on the other hand determine the section, called optimal theoretical, of the burr cord 5 and the corresponding flash clearance 6 in the plane Pj.
  • a third step called choice, the parameters l and d are determined, then the connections R1 and R2 in the sections Pa, Pb, Pc. These variable parameters will make it possible to obtain the length ⁇ of the burr cord best suited to the part.
  • the interpolation, automatic can be linear, quadratic, cubic, in polynomial summary, and the optimal sections 5 and 6 of FIG. 2 are thus obtained for all the planes Pi. These optimal sections are also shown in FIG. detail of the segments 15 ', 15 ", 20', 20" of the plane Pi.
  • the sections of the burr cords corresponding to the leading and trailing edges can be calculated simultaneously, but with different parameters, such as the theoretical length l of the bead, the withdrawal distance defining its thickness ⁇ , the height h, the angle ⁇ , etc .
  • the result of the automatic interpolation can, for certain extreme values of i, near the root of the blade, for example, not be acceptable and provide segments, such as C13, which are misdirected. relative to the orientation of the Fo strike of the forging machine.
  • the matrix can not push the material back into the clearance angle.
  • the segments C10 and C20 of the reference section are projected on the previous or next section, represented C'10, depending on whether one is towards the foot or the top of the blade.
  • C'10 previous or next section
  • the parallels are taken at C'10 and C'20 respectively, then the bisectors between C11 and C" 10 parallel to C'10 passing through are constructed.
  • point 18, on the one hand and C21 and C in the same way by point 18" on the other hand.
  • These segments are the new flash clearances so the reference segments are projected on the previous or next section and so on.
  • a program provided for this purpose can make several attempts to choose the reference sections that give the best result. The recovery of the flash clearances is thus achieved in a single operation.
  • the matrix 120 is represented by the same corresponding elements, the surfaces corresponding to X 'being here marked X ".
  • Figure 7 shows the matrix 120 alone by its elements already shown in Figure 6.

Claims (5)

  1. Verfahren zur geometrischen Konstruktion einer in einer Matrize (110, 120) zum Formschmieden einer Turbomaschinen-Schaufel vorzusehenden Gratbahn (5) in Abhängigkeit von bestimmten Parametern (l, d, ε, α, h), wobei die Schaufel ein Schaufelblatt (10) aufweist und das Schaufelblatt mit ebenen Querschnitten (Si) gemäß vorbestimmten Ebenen (Pi) gebildet ist, und wobei die Gratbahn (5) und ihr Gratkantenauslauf gemäß diesen vorbestimmten Ebenen geformt werden müssen, um ebene Querschnitte des Schaufelblatts und der Gratbahn zu erhalten,
    dadurch gekennzeichnet,
    dass
    - mindestens drei Bezugsquerschnitte (Sa, Sb, Sc) des Schaufelblatts gemäß Bezugsebenen (Pa, Pb, Pc), die dem unteren Teil, dem mittleren Teil und der Spitze des Schaufelblatts entsprechen, gewählt werden,
    - in den genannten Bezugsebenen die Länge (λ) der Gratbahn und eine Schwindstrecke (d) für die drei Bezugsquerschnitte bestimmt wird,
    - in den genannten bestimmten Ebenen durch Interpolation die zwischenliegenden Querschnitte der Gratbahn und des Gratkantenauslaufs von diesen Bezugsquerschnitten aus konstruiert werden.
  2. Verfahren nach Anspruch 1, wobei vor der Berechnung der zwischenliegenden Querschnitte der Gratbahn und ihres Gratkantenauslaufs verschiedene Bestimmungen von Gratbahn-Parametern ausgeführt werden, indem diese Parameter in den Querschnitten variiert werden.
  3. Verfahren nach einem der Ansprüche 1 und 2, wobei die Querschnitte der Gratbahn und des Gratkantenauslaufs, die der Vorderkante (BA) und der Hinterkante (BF) entsprechen, simultan berechnet werden.
  4. Verfahren nach einem der Ansprüche 1 bis 3, wobei zur Bestimmung der zwischenliegenden Querschnitte der Gratbahn und des Gratkantenauslaufs eine Polynominterpolation verwendet wird.
  5. Verfahren nach den Ansprüchen 1 bis 4, wobei nach Interpolation die Ausrichtung der Querschnitte des Gratkantenauslaufs (20', 20") im Gesenk gerichtet wird, um Unterschneidungen dessen oder im Wesentlichen vertikale Wände zu beseitigen.
EP05105968A 2004-07-09 2005-06-30 Verfahren zur geometrischen Konstruktion eines Grats eines geschmiedeten Werkstückes mit komplexer Form Active EP1614487B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0451497A FR2872721B1 (fr) 2004-07-09 2004-07-09 Procede de construction geometrique d'un cordon de bavure de forgeage de piece complexe

Publications (2)

Publication Number Publication Date
EP1614487A1 EP1614487A1 (de) 2006-01-11
EP1614487B1 true EP1614487B1 (de) 2007-01-17

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US (1) US7565851B2 (de)
EP (1) EP1614487B1 (de)
JP (1) JP4705423B2 (de)
CN (1) CN100462160C (de)
DE (1) DE602005000465T2 (de)
FR (1) FR2872721B1 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103136426B (zh) * 2013-03-01 2015-07-01 西北工业大学 航空叶片圆弧形前后缘工艺模型生成方法
CN103691866B (zh) * 2013-12-15 2015-10-14 无锡透平叶片有限公司 一种提高叶片坯料在模具上定位稳定性的方法
CN104960217B (zh) * 2015-05-18 2017-03-29 天津赛象科技股份有限公司 用于胎面缠绕的胶条堆叠仿真模拟方法
CN105041386B (zh) * 2015-07-21 2016-08-31 南京航空航天大学 一种圆弧和直线段混合异型孔
CN105170809B (zh) * 2015-10-13 2017-03-08 中国南方航空工业(集团)有限公司 一种压气机静子叶片冲切模具的制造方法
CN105215622B (zh) * 2015-10-13 2017-06-13 中国南方航空工业(集团)有限公司 一种压气机静子叶片冲切模具的修理方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1932426A (en) * 1931-06-22 1933-10-31 Claud L Stevens Method of making dies
GB584623A (en) * 1945-01-11 1947-01-20 Herman Aron Improvements in or relating to the forging of turbine blades
US2503630A (en) * 1945-10-29 1950-04-11 Thompson Prod Inc Method of making impeller bucket dies
US2987806A (en) * 1956-05-24 1961-06-13 Thompson Ramo Wooldridge Inc Method of making turbine blades and the like
US5187967A (en) * 1991-09-16 1993-02-23 General Electric Company Laser trimming of forgings
US5288209A (en) * 1991-12-19 1994-02-22 General Electric Company Automatic adaptive sculptured machining
JPH06328180A (ja) * 1993-03-26 1994-11-29 Mazda Motor Corp 鍛造用金型の製作方法
FR2724127B1 (fr) * 1994-09-07 1996-12-20 Snecma Procede de fabrication d'une aube creuse de turbomachine
JP2834433B2 (ja) * 1996-02-29 1998-12-09 中小企業事業団 鍛造品の前工程での形状決定方法および鍛造用金型の設計方法
US7433799B2 (en) * 2003-11-17 2008-10-07 Agency For Science, Technology And Research Method of determining shape data

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Publication number Publication date
US20060005386A1 (en) 2006-01-12
CN1772410A (zh) 2006-05-17
DE602005000465D1 (de) 2007-03-08
CN100462160C (zh) 2009-02-18
US7565851B2 (en) 2009-07-28
EP1614487A1 (de) 2006-01-11
JP2006021251A (ja) 2006-01-26
DE602005000465T2 (de) 2007-08-23
FR2872721B1 (fr) 2006-09-22
FR2872721A1 (fr) 2006-01-13
JP4705423B2 (ja) 2011-06-22

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