US20130180304A1 - "multi-effect" forming tooling for high-temperature forming - Google Patents

"multi-effect" forming tooling for high-temperature forming Download PDF

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Publication number
US20130180304A1
US20130180304A1 US13/876,721 US201113876721A US2013180304A1 US 20130180304 A1 US20130180304 A1 US 20130180304A1 US 201113876721 A US201113876721 A US 201113876721A US 2013180304 A1 US2013180304 A1 US 2013180304A1
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US
United States
Prior art keywords
tooling
moving
dies
forming
translational movement
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.)
Abandoned
Application number
US13/876,721
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English (en)
Inventor
Stéphane André Leveque
Dominique Magnaudeix
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
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 SNECMA SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LEVEQUE, STEPHANE ANDRE, MAGNAUDEIX, DOMINIQUE
Publication of US20130180304A1 publication Critical patent/US20130180304A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
    • B21D22/02—Stamping using rigid devices or tools
    • B21D22/022—Stamping using rigid devices or tools by heating the blank or stamping associated with heat treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J13/00—Details of machines for forging, pressing, or hammering
    • B21J13/02—Dies or mountings therefor
    • B21J13/025—Dies with parts moving along auxiliary lateral directions
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/25—Manufacture essentially without removing material by forging

Definitions

  • the present invention relates to a “multi-effect” forming tooling for high-temperature forming of metal workpieces such as for example a metal reinforcement for a composite or metal turbine engine blade.
  • the “multi-effect” forming tooling according to the invention is particularly suitable for shaping workpieces with a complex geometrical shape such as a metal reinforcement for the leading edge of a turbine engine blade.
  • the field of the invention is particularly that of turbine engines and more specifically that of turbine engine fan blades, in composite or metallic material, wherein the leading edge comprises a metal structural reinforcement.
  • the invention is also applicable to the production of any workpieces with a complex geometrical shape and to the production of metal reinforcements intended to reinforce a leading edge or a trailing edge of a blade from any type of turbine engine, whether terrestrial or aeronautical, particularly a helicopter turboshaft or a jet turbine engine.
  • leading edge corresponds to the anterior part of an aerodynamic profile that faces the flow of air and divides the air flow into a lower surface air flow and an upper surface air flow.
  • the trailing edge corresponds to the posterior part of an aerodynamic profile where the lower surface and upper surface flows meet.
  • Turbine engine blades particularly fan blades, undergo significant mechanical stresses, particularly connected to the rotation speed, and must satisfy strict weight and volume conditions.
  • One of the options contemplated for reducing the blade weight is the use of composite materials for their manufacture.
  • Equipping fan blades of a turbine engine made in composite materials, with a metal structural reinforcement extending over the entire height of the blade and beyond their leading edge as mentioned in document EP1908919 filed by SNECMA is known.
  • a reinforcement enables the composite blading to be protected during an impact by a foreign body on the fan, such as, for example, a bird, hail or else stones.
  • the metal structural reinforcement protects the leading edge of the composite blade by preventing delamination and fiber breakage risks or else damage by fiber/matrix debonding.
  • a turbine engine blade comprises an aerodynamic surface extending, in a first direction, between a leading edge and a trailing edge and, in a second direction substantially perpendicular to the first direction, between a foot and a top of the blade.
  • the metal structural reinforcement follows the form of the leading edge of the aerodynamic surface of the blade and extends in the first direction beyond the leading edge of the aerodynamic surface of the blade to follow the profile of the lower surface and the upper surface of the blade and in the second direction between the foot and the top of the blade.
  • the metal structural reinforcement is a metal workpiece in titanium made entirely by milling from a block of material.
  • the metal reinforcement for the leading edge of the blade is a complex piece to make, necessitating many refinishing operations and complex equipment involving significant production costs.
  • the invention aims to resolve the problems mentioned above, by proposing a “multi-effect” forming tooling capable of forming metal workpieces at high temperature, such as a metal reinforcement of the leading edge or trailing edge of a turbine engine blade enabling simplification of the manufacturing process and a significant reduction in the costs of producing such a workpiece by proposing a “multi-effect” tooling implemented by a single action press.
  • a “multi-effect” forming tooling capable of forming metal workpieces at high temperature, such as a metal reinforcement of the leading edge or trailing edge of a turbine engine blade enabling simplification of the manufacturing process and a significant reduction in the costs of producing such a workpiece by proposing a “multi-effect” tooling implemented by a single action press.
  • the invention proposes a “multi-form” forming tooling capable of high temperature forming of metal workpieces, said tooling comprising a fixed part and a moving part set in action by a one-way press, in a first direction, said tooling varying between an open position and a closed position in which the moving part applies pressure to said fixed part;
  • said moving part comprises moving means capable of initiating deformation of said metal workpiece through a translational movement of said means in a second direction Y simultaneous with the translational movement of said means in said first direction during said closure of said tooling, said moving means being capable of moving away from said metal workpiece through a reverse translational movement of said moving means, in said second direction, simultaneously with the translational movement of said moving means, in said first direction, during said opening of said tooling.
  • One-way press is understood to refer to a single action press only comprising one working axis, generally the vertical axis with relation to the bearing plane of the press, as opposed to double or else triple action presses, respectively comprising two or three working axes oriented in different directions.
  • Multi-effect is understood to refer to deformation in several directions intervening in several places on the workpiece simultaneously in opposition to single action deformation resulting from a single stress applied locally in a single direction.
  • the invention it is possible to carry out multi-effect deformation (i.e., simultaneously in different directions) by means of an inexpensive single action press, under high temperature conditions, i.e., the temperatures necessary for forging the workpieces to be produced.
  • the workpiece is deformed and twisted in several directions in a single operation with a single action press at a temperature greater than 850° C. (on the order of 940° C. for the production of a titanium reinforcement). Therefore, the tooling according to the invention obviates the need for a complex production of reinforcements by a method of milling in the mass from flats requiring large volumes of material and, consequently, the tooling enables the quantities of raw materials necessary for producing such a metal reinforcement to be reduced.
  • the metal reinforcement with a complex shape is made in a simple and quick manner from a preform obtained from a simple metal bar and a succession of forging steps such as described, in particular, in patent application SNECMA FR1055066.
  • the preform is then shaped in a three-dimensional manner at high temperature in the “multi-effect” tooling by means of a single action press.
  • the tooling according to the invention enables multi-effect deformation (i.e., simultaneously in different directions) to be carried out by means of an inexpensive single action press, under high temperature conditions, i.e., beyond 850° C.
  • the “multi-effect” tooling according to the invention may also present one or more of the characteristics below, considered individually or according to all technically possible combinations:
  • FIG. 1 is a perspective view of the forming tooling according to the invention illustrated in its open position
  • FIG. 2 is a side view of the tooling according to the invention during a closing phase
  • FIG. 3 is a side view of the forming tooling according to the invention in its closed position
  • FIG. 4 is a side view of the forming tooling according to the invention illustrating the tooling during an opening phase
  • FIG. 5 is a side view of the tooling according to the invention illustrating the forming tooling in its open position.
  • FIG. 1 is a perspective view of the forming tooling 100 according to the invention illustrated in its open position.
  • the forming tooling 100 is conventionally formed by a lower part 110 , representing the fixed part of tooling 100 , and an upper part 120 , representing the moving part of tooling 100 .
  • the forming tooling 100 represented, by way of example, in all figures is a tooling enabling a titanium reinforcement for the leading edge of a turbine engine blade to be made.
  • the tooling is intended to be assembled on a single action press (not represented), of the forging press type, comprising a single working axis, generally the vertical axis, illustrated in FIG. 1 by the Z axis.
  • the tooling may also be mounted on any type of pressure forging machine comprising a single working axis.
  • a forged workpiece is fabricated by placing a preform or a blank between two dies, an upper die and a lower die, each comprising an appropriate imprint (or cavity), and then by moving the two dies closer together with a pressure sufficient to deform the preform until a workpiece whose geometry corresponds to that of the imprints is obtained, the forging operation being carried out with the heated tooling, i.e. a tooling at a temperature greater than 850° C. for producing a titanium workpiece and advantageously at a temperature on the order of 940° C. (plus or minus 10%).
  • the heated tooling i.e. a tooling at a temperature greater than 850° C. for producing a titanium workpiece and advantageously at a temperature on the order of 940° C. (plus or minus 10%).
  • the lower part 110 of the tooling comprises, in particular:
  • FIG. 2 illustrating a side view of the forming tooling according to the invention illustrated in its open position, some elements, such as the support plates 116 , are not represented in order to enable the layout of the lower die 112 to be seen more clearly.
  • the lower die 112 is formed by:
  • the second upper part 112 a is connected to the first part by connection means 132 forming pins and traversing both the first lower part 112 a at the level of the longitudinal grooves 119 and the positioning lugs 118 of the upper part 112 b.
  • the lower die 112 comprises a punch 114 , the upper part of which forms an imprint 113 in conformance with the inner geometry of the leading edge of the turbine engine blade.
  • the lower part 112 b of the die 112 presents a flare, substantially in the shape of an isosceles trapezoid, capable of receiving the base of the punch 114 , also in a trapezoidal shape, and capable of centering the punch 114 in die 112 .
  • the base of the punch 114 is trapped between the lower part 112 a and the upper part 112 b of the die 112 , and more specifically in a space 114 bordered on the one hand by the flare of the lower part 112 a and on the other hand by two horizontal lugs 133 projecting inside the upper part of tooling 110 .
  • these two horizontal lugs 133 of the upper part 112 b perform a stop function only allowing a certain vertical displacement (i.e., in the Z axis represented in FIG. 1 ) of the base of punch 114 in the defined space 115 .
  • the clearance thus created advantageously enables a calibrated displacement between these different pieces of die 112 , creating a punch 114 floating in space 115 that is capable of facilitating the unmolding of the workpiece made in tooling 100 .
  • Support plates 116 are connected to the lower part 112 a of die 112 by conventional connection means used in this type of forging press tooling.
  • the upper part 120 of the tooling comprises, in particular:
  • the two upper dies 121 and 122 have the characteristic of generating a complex movement different from the displacement imposed by the single action press.
  • FIG. 2 more specifically illustrates the respective movements of the two dies 121 , 122 , by arrows referenced 150 , during closing of the press, in which the opening/closing displacement is symbolized by vertical arrows 160 .
  • the two upper dies 121 , 122 perform a translational movement in the Y axis, during displacement of the upper support 123 in the Z axis.
  • the translational movement of upper dies 121 , 122 during closing of the press is allowed by the complementary shape of upper dies 121 , 122 and the lower die 112 .
  • Face 131 of the lower die 112 that inwardly faces tooling 100 forms a slope on which upper dies 121 , 122 slide during closing of the press, by generating a transverse displacement complementary to the vertical displacement in the Z axis.
  • upper dies 121 , 122 The transverse movement of upper dies 121 , 122 is relatively guided by a guide 134 , for example a free cylindrical pin, enabling the two upper dies 121 , 122 to be guided during closing and during opening of the press.
  • a guide 134 for example a free cylindrical pin
  • the two upper dies 121 , 122 initiate the deformation and possibly the twisting of preform 10 , introduced in the tooling, during the closing of the tooling and from the start of the closing phase of tooling 100 .
  • the upper dies 121 and 122 comprise a bearing surface 135 on their upper part, on which the support 123 transmits the thrust of the press.
  • This bearing surface is oriented substantially perpendicularly to the direction of thrust of the upper dies 121 , 122 , illustrated by arrows 150 .
  • the orientation of this bearing surface 135 limits the torque generated on upper dies 121 , 122 and thus prevents the upper dies 121 , 122 from twisting when the press is closed.
  • FIG. 3 illustrates the forming tooling 100 described previously in the closed position.
  • two spacers 141 integral with the upper support 123 enable, by virtue of their shape, the two upper dies 121 , 122 to be moved away from the forged workpiece.
  • the spacers 141 present an outer beveled surface 136 forming a slope and producing a bearing surface capable of sliding on upper dies 121 , 122 during opening of tooling 100 . Therefore, during the upward movement of upper tooling 120 , the spacers 141 rise vertically, according to the arrow referenced 161 , illustrated in FIG. 4 , enter in contact with upper dies 121 , 122 and then push in this manner upper dies 121 , 122 in a transverse direction, perpendicular to the direction of opening of tooling 100 .
  • FIGS. 4 and 5 respectively illustrate the tooling in the low position during the upward movement phase of the press and the tooling in the high position during the upward movement phase of the press.
  • the upper dies are positioned supported on spacers 141 by means of horizontal stops 138 and slopes 137 . Therefore, the device is operational for forming the next workpiece.
  • the automatic spacing (as opposed to manual spacing by an operator) enables the tooling to be quickly prepared to form the next workpiece without operator intervention and without cooling of the tooling.
  • imprint 113 may be constituted of a plurality of movable or removable sections capable of being individually disassembled.
  • this protective layer may be a layer of aluminum oxide.
  • the invention was particularly described for making a metal reinforcement for a composite turbine engine blade; however, the invention is also applicable for making a metal reinforcement for a metal turbine engine blade.
  • the invention was particularly described for making a metal reinforcement for a leading edge of a turbine engine blade; however, the invention is also applicable for making a metal reinforcement of a trailing edge of a turbine engine blade.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Forging (AREA)
  • Press Drives And Press Lines (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/876,721 2010-09-30 2011-09-27 "multi-effect" forming tooling for high-temperature forming Abandoned US20130180304A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1057918A FR2965496B1 (fr) 2010-09-30 2010-09-30 Outillage de forme « multi-effets » apte au formage a haute temperature.
FR1057918 2010-09-30
PCT/FR2011/052249 WO2012042164A2 (fr) 2010-09-30 2011-09-27 Outillage de forme " multi-effets " apte au formage a haute temperature

Publications (1)

Publication Number Publication Date
US20130180304A1 true US20130180304A1 (en) 2013-07-18

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Family Applications (1)

Application Number Title Priority Date Filing Date
US13/876,721 Abandoned US20130180304A1 (en) 2010-09-30 2011-09-27 "multi-effect" forming tooling for high-temperature forming

Country Status (8)

Country Link
US (1) US20130180304A1 (fr)
EP (1) EP2621648A2 (fr)
CN (1) CN103140307B (fr)
BR (1) BR112013007578A2 (fr)
CA (1) CA2812809A1 (fr)
FR (1) FR2965496B1 (fr)
RU (1) RU2013120020A (fr)
WO (1) WO2012042164A2 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2017148813A (ja) * 2016-02-22 2017-08-31 日立金属株式会社 熱間鍛造用金型及び熱間鍛造方法
US10155260B2 (en) 2013-09-02 2018-12-18 Safran Aircraft Engines Method for the high-temperature shaping of a metal blade reinforcement
US10668523B2 (en) 2015-02-19 2020-06-02 Safran Aircraft Engines Method for high temperature forging of a preformed metal part, and shaping equipment suitable for forging
CN116174560A (zh) * 2023-03-13 2023-05-30 上海交通大学 超快分区接触加热铝合金热冲压成形装置及方法
CN120228152A (zh) * 2025-06-03 2025-07-01 德州国豪空调设备有限公司 一种风机叶轮的制造加工装置
WO2025172673A1 (fr) 2024-02-15 2025-08-21 Safran Aircraft Engines Procede de fabrication d'une aube pour une turbomachine d'aeronef

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104308481B (zh) * 2014-10-27 2017-01-11 西安航空动力股份有限公司 一种航空发动机无安装板压气机静子叶片加工方法
CN107962360B (zh) * 2017-12-05 2020-07-28 成都市鸿侠科技有限责任公司 一种航空发动机封严叶片加工工艺及成型模具
CN114082857B (zh) * 2021-11-11 2024-08-06 中国航发贵州黎阳航空动力有限公司 一种用于航空发动机叶片与内环装配的单端扩口销扩口工装以及扩口装配方法

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US5378205A (en) * 1992-08-05 1995-01-03 Gohl; Allen P. Extruded metal chain pin
US6457341B1 (en) * 1998-06-29 2002-10-01 Eric Wirgarth Forging die
US20070079643A1 (en) * 2003-12-04 2007-04-12 Juergen Dohmann Steering rack manufacture

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GB1168210A (en) * 1968-05-17 1969-10-22 Rolls Royce Improvements relating to the Forging of a Flanged Article
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JP3840954B2 (ja) * 2001-10-25 2006-11-01 日産自動車株式会社 クランクシャフトの鍛造型構造
RU2282517C2 (ru) * 2004-05-31 2006-08-27 Открытое акционерное общество "Чепецкий механический завод" (ОАО ЧМЗ) Способ радиальной ковки заготовок и четырехбойковое ковочное устройство для его осуществления
CN1290639C (zh) * 2004-09-29 2006-12-20 刘清云 一种拉伸模具
KR100614211B1 (ko) * 2004-12-08 2006-08-21 주식회사 신일 개폐식 금형을 이용한 단조장치
FR2906320B1 (fr) 2006-09-26 2008-12-26 Snecma Sa Aube composite de turbomachine a renfort metallique
WO2010090284A1 (fr) * 2009-02-09 2010-08-12 本田技研工業株式会社 Procédé et appareil pour produire un arbre de vilebrequin
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2544447A (en) * 1944-11-24 1951-03-06 Curtiss Wright Corp Apparatus for producing shaped sections
US4715210A (en) * 1982-06-04 1987-12-29 Bishop Arthur E Method for making steering rack bars
US5378205A (en) * 1992-08-05 1995-01-03 Gohl; Allen P. Extruded metal chain pin
US6457341B1 (en) * 1998-06-29 2002-10-01 Eric Wirgarth Forging die
US20070079643A1 (en) * 2003-12-04 2007-04-12 Juergen Dohmann Steering rack manufacture

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10155260B2 (en) 2013-09-02 2018-12-18 Safran Aircraft Engines Method for the high-temperature shaping of a metal blade reinforcement
US10668523B2 (en) 2015-02-19 2020-06-02 Safran Aircraft Engines Method for high temperature forging of a preformed metal part, and shaping equipment suitable for forging
JP2017148813A (ja) * 2016-02-22 2017-08-31 日立金属株式会社 熱間鍛造用金型及び熱間鍛造方法
CN116174560A (zh) * 2023-03-13 2023-05-30 上海交通大学 超快分区接触加热铝合金热冲压成形装置及方法
WO2025172673A1 (fr) 2024-02-15 2025-08-21 Safran Aircraft Engines Procede de fabrication d'une aube pour une turbomachine d'aeronef
FR3159340A1 (fr) * 2024-02-15 2025-08-22 Safran Aircraft Engines Procede de fabrication d’une aube pour une turbomachine d’aeronef
CN120228152A (zh) * 2025-06-03 2025-07-01 德州国豪空调设备有限公司 一种风机叶轮的制造加工装置

Also Published As

Publication number Publication date
WO2012042164A2 (fr) 2012-04-05
CA2812809A1 (fr) 2012-04-05
EP2621648A2 (fr) 2013-08-07
FR2965496A1 (fr) 2012-04-06
RU2013120020A (ru) 2014-11-10
CN103140307A (zh) 2013-06-05
CN103140307B (zh) 2016-08-24
WO2012042164A3 (fr) 2012-05-24
FR2965496B1 (fr) 2013-07-12
BR112013007578A2 (pt) 2016-08-02

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Owner name: SNECMA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:LEVEQUE, STEPHANE ANDRE;MAGNAUDEIX, DOMINIQUE;REEL/FRAME:030122/0106

Effective date: 20130320

STCB Information on status: application discontinuation

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