• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A process for FI inertial friction welding of two parts of a turbomachine rotating subassembly, at least one of which has a plurality of hook teeth at its periphery and wherein one (24) of two parts to be welded to one another to the other is held by a clamp (16) and rotated by a motor (18) and the other (26) of the two parts to be welded is held by a torque recovery ring gear (22) mounted in a trolley (20) movable in translation, in which method to avoid any formation of cracks at the hooks of the teeth during welding, it is intended to cover the plurality of teeth with hooks damping means to shift frequency response vibratory of these hooks and thus create a damping.
    公开号:FR3016819A1
    申请号:FR1450610
    申请日:2014-01-24
    公开日:2015-07-31
    发明作者:Benoit Lardy；Dominique Bernard Lourdin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to the field of friction welding in the process of manufacturing turbine engine components (compressors, turbines, etc.) and more particularly to an inertial friction welding (IF) process between turbomachine high pressure compressor stage disks having at least one disk having a peripheral set of hook teeth for anchoring blade roots. It is known by tests instrumented by strain gauges that the FI welding used for the assembly of the turbomachine high-pressure compressor stage disks generates stresses which cause an appearance of cracks highlighted by bleeding control, in particular in the area of the hooks of these disks. However, this initiation of cracks is unacceptable on parts essential to the integrity of the turbomachine. There is therefore a need to improve the current FI welding process to suppress this crack initiation.
    [0002] OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to propose an FI welding process which overcomes this disadvantage. This object is achieved by an FI inertial friction welding process of two parts of a turbomachine rotating subassembly of which at least one has at its periphery a plurality of hook teeth and in which one of two parts to welding to one another is maintained by a clamp and rotated by a motor and the other of the two parts to be welded is held by a torque recovery ring gear mounted in a carriage movable in translation, characterized in in order to avoid any formation of cracks at the hooks of said teeth during welding, it is intended to cover said plurality of hook teeth with damping means able to frequency shift the vibratory response of said hooks and thus create a damping .
    [0003] Thus, with this damper assembly shifting in frequency the vibration response and damping the hooks, it ensures a sufficient energy absorption to avoid the creation of cracks on the disc. Preferably, said damping means comprise seven adjacent damping sectors completely covering said plurality of hooked teeth and each covering an angle of about 51 degrees. According to a first embodiment, each of said damping sectors comprises two lateral flanks conforming to the circumference of the disc and resting on the lateral edges of the teeth via a first viscoelastic gum, two upper flanges of these flanks resting on two clamping plates. in contact with the upper edges of the teeth via a second viscoelastic gum. Preferably, said plates are held tight by screws compressing spring means disposed between these two plates and acting as a return spring once they are loosened. According to a second embodiment, said damping means comprise an individual damper mounted on each of the teeth of said set of hooked teeth. Advantageously, said individual damper comprises a first blade, one end of which is terminated by a flange cooperating with one of the two hooks of a tooth and a second blade, one end of which is terminated by a flange cooperating with the other of the two hooks of said tooth, the other end of said first and second blades being secured to each other by fastening means.
    [0004] For, by applying clamping in two directions, allow the flanges to grip the corresponding hooks and thus mechanically retain said individual damper against said tooth, said other ends of said first and second blades each end with a slope.
    [0005] Preferably, said first blade has length and width substantially corresponding to the length and width of a tooth and said second blade has a length substantially corresponding to the height of a tooth and a width substantially corresponding to the width of a tooth. Advantageously, said first and second blades are covered on their inner face in contact with said teeth by viscoelastic gums. BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate an embodiment of the invention which is in no way limiting in nature and in which: FIGS. and 1B are detailed sectional views respectively of the mandrel and the carriage of an inertial friction welding machine known as FI suitable for carrying out the method of the invention; FIGS. 2 and 2A to 2C illustrate a first embodiment of damping means used in the method of the invention; and FIGS. 3A and 3B illustrate a second embodiment of damping means implemented in the method of the invention. DETAILED DESCRIPTION OF THE EMBODIMENT FIGS. 1A and 1B respectively represent the mandrel and the carriage of an FI inertial friction welding machine capable of carrying out the process according to the FI welding invention of two 25 stage discs of high pressure compressor of a turbomachine. Of course, it is more generally applicable to FI welding of two parts of a rotating subassembly of such a turbomachine. The machine 10 essentially consists firstly of a mandrel 12 coupled to flywheels 14 and in which one of the two parts of the sub-assembly to be welded is held by a clamp 16 and rotated by a motor 18 (Figure 1A) and on the other hand a carriage 20 movable in translation and on which is mounted a sole 22 in the toothed gear ring (or the jaw 24) which is maintained the other 28 of two parts of the sub-assembly to be welded.
    [0006] The principle of operation of this machine is based on the fact that the heat required for welding is generated by the friction between two parts in relative motion relative to each other. The motor 18 drives the chuck 12 in rotation allowing kinetic energy to accumulate in the flywheels 14 until the motor has reached a predetermined speed to allow it to disengage. The advance of the carriage 20 is then actuated causing contact of the two parts of the subassembly 26, 28 to be welded. The friction caused by the rotation and the axial pressure of these two parts will cause a heating increasing the temperature which in a relatively short time will reach the temperature (forging temperature) required for welding. At the same time, there is a gradual decrease in the speed of rotation to a complete stop once the energy accumulated in the flywheels consumed. The axial pressure maintained until the cooling of the part is at the origin of the welding bead characteristic of this type of friction welding. This process, which is within the abilities of a person skilled in the art, will not be described further by calculating the parameters, rotational speed, axial pressure, resistive torque and carriage advance, necessary for welding two pieces of given dimensions formed into one or two specific materials. In the aeronautical field, FI welding is used in particular for welding titanium or nickel-based compressor or turbine discs as well as for steel-based turbine shafts. More particularly, FIG. 1A shows a mandrel 12 whose clip 16 squeezes a titanium-based high pressure compressor stage disk of an aircraft engine having at its periphery a plurality of hooked teeth for anchoring the aircraft. blade feet in the compressor and Figure 1B shows a carriage 20 whose jaw 24 clamps all adjacent disks of the other titanium-based stages of a high pressure compressor of an aircraft turbine engine. Of course, this is only an example of welded discs among many other conceivable.
    [0007] During a welding operation F1, the relative rotational movement of the discs to be welded and the associated friction generate vibrations to which the structure of these discs, the tooling and the machine respond in the form of a structural vibratory response. These vibrations, which depend on the geometry of the disks to be welded, the conditions of holding in position, the welding parameters and the material or materials of these disks, can, depending on their frequency, lead to the initiation of cracks on disks, especially at the hooks of the teeth. According to the invention, it is proposed to dampen these vibrations by covering the plurality of hook teeth with damping means 30, 40 in order to frequency shift the vibratory response of the hooks of these teeth and thus prohibit any crack initiation. . Figures 2, 2A, 2B and 2C illustrate a first embodiment in which the damping means 30 are formed of several damping sectors evenly distributed around the disk.
    [0008] In the illustrated example corresponding to a 70-tooth high-pressure compressor stage disk 3, there are seven adjacent sectors each extending about 51 degrees, each sector covering ten teeth. Each damping sector has two curved lateral flanks 32, 34 in the form of an inverted r (L), matching the circumference of the disc and intended, when tightened against each other, to bear against the lateral edges of the flanges. teeth via a first viscoelastic gum 40A, the two upper flanges 32A, 34A of these flanks bearing on two clamping plates 36, 38 also curved along the circumference of the disc and in contact with the upper edges of the teeth via a second eraser viscoelastic 40B. The plates are held tight by screws 42 compressing spring means 44 disposed between these two plates and acting as a return spring once these loosened. Screws 46 maintain the side flanks on the clamping plates. FIGS. 3A and 3B illustrate a second embodiment in which the damping means 50 are individualized and each cover a tooth 52 of the disk. Each individual damper thus comprises a first blade 54 whose length and width correspond substantially to the length and width of a tooth and whose first end is terminated by a flange 54A intended to cooperate with the one 52A of the two hooks of this tooth. , preferably the hook behind the tooth, and a second blade 56 of a length corresponding substantially to the height of the tooth 35 but of the same width as the first and whose one end is terminated by a flange 56A intended to cooperate with the other 52B of the two 3016 819 6 hooks of the tooth (the one in front of the tooth accessible on the front of the carriage), the second sloped ends 54B, 56B of these first and second blades being secured together by means of fastening, typically a screw-nut assembly 58. Thus, tightening the nut 5 bringing the two blades closer to one another will allow the flanges 54A, 56A to grip the corresponding hooks 52A, 52B and thus mechanically retain the damper against the tooth. This is an elegant technical means for applying a tightening in two directions: by sliding on the slope 54B of the first blade, the second blade 56 10 rises along the axis of the screw 58 and also moves perpendicularly relative to this axis. Of course, as before, to ensure the damper-tooth contact and to promote absorption of energy by damping, these two blades are covered on their inner face in contact with the teeth by gums or viscoelastic materials of smactane® type or analogue for example. In practice, care should be taken to ensure sufficient damping of the dampers on the teeth by a regular change of these materials, especially when a visual check will appear a degradation of their appearance.
    [0009] The change of the frequency response of the hooks by mechanical restraint carried out with the method of the invention made it possible to solve the problem of cracks.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. FI inertial friction welding process of two parts of a turbomachine rotating subassembly of which at least one has at its periphery a plurality of hook teeth and in which one (24) of two parts to be welded to one another is held by a clamp (16) and rotated by a motor (18) and the other (26) of the two parts to be welded is held by a torque recovery ring gear (22) mounted in a carriage (20) movable in translation, characterized in that to avoid any formation of cracks at the hooks of said teeth during welding, it is intended to cover said plurality of hook teeth with damping means (30). , 50) able to shift in frequency the vibratory response of said hooks and thus create a damping. 15
    [0002]
    2. FI welding method according to claim 1, characterized in that said damping means comprise seven adjacent damping sectors completely covering said plurality of hook teeth and each covering an angle of about 51 degrees. 20
    [0003]
    3. A method of welding FI according to claim 2, characterized in that each of said damping sectors comprises two lateral flanks (32, 34) conforming to the circumference of the disk and resting on the lateral edges of the teeth via a first viscoelastic gum 25 ( 40A), two upper flanges (32A, 34A) of these flanks bearing on two clamping plates (36, 38) in contact with the upper edges of the teeth via a second viscoelastic gum (40B).
    [0004]
    4. FI welding method according to claim 3, characterized in that said plates are held tight by screws (42) compressing spring means (44) arranged between these two plates and acting as a return spring once these loose.
    [0005]
    FI welding method according to claim 1, characterized in that said damping means comprise an individual damper (50) mounted on each of said plurality of hook teeth.
    [0006]
    6. A method of welding FI according to claim 5, characterized in that said individual damper comprises a first blade (54) whose end is terminated by a flange cooperating with one of the two hooks of a tooth and a second blade (56) one end (54A, 56B) is terminated by a flange cooperating with the other of the two hooks of said tooth, the other end (54B, 56B) of said first and second blades being secured to each other by means of fastening means (58).
    [0007]
    7. FI welding method according to claim 6, characterized in that said other ends of said first and second blades 15 each end with a slope (54A, 56B) for, applying a clamping in two directions, allow the edges (54A , 56A) to grip the corresponding hooks (52A, 52B) and thus mechanically retain said individual damper against said tooth. 20
    [0008]
    8. FI welding process according to claim 6, characterized in that said first blade has length and width substantially corresponding to the length and width of a tooth and said second blade has a length substantially corresponding to the height of a tooth and a width substantially corresponding to the width of a tooth.
    [0009]
    9. FI welding method according to claim 8, characterized in that said first and second blades are covered on their inner face in contact with said teeth by viscoelastic gums (60).
    [0010]
    10. FI welding process according to any one of claims 1 to 9, characterized in that it is implemented between turbomachine high pressure compressor stage disk 35 having at least one peripheral assembly of hook teeth for the anchoring of blade roots in the compressor.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3016819A1|2015-07-31|INERTIAL FRICTION WELDING PROCESS OF TWO PARTS OF A TURBOMACHINE ROTATING SUBASSEMBLY
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    CA2521265C|2011-06-07|Excess turbine speed limitation device in a turbine engine
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    EP2483007B1|2013-07-10|Repairing compressor blades by cold compacting
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    同族专利:
    公开号 | 公开日
    GB2536392B|2019-05-08|
    WO2015110746A1|2015-07-30|
    GB201612137D0|2016-08-24|
    US20160339539A1|2016-11-24|
    US9597748B2|2017-03-21|
    FR3016819B1|2016-02-12|
    GB2536392A|2016-09-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20040108358A1|2002-12-04|2004-06-10|General Electric Company|Method and apparatus for reducing component vibration during inertia welding|
    EP1598524A1|2004-05-17|2005-11-23|Snecma|Assembly method for unitary vaned rotors and device for the damping of vane vibrations|
    EP1927722A1|2006-11-28|2008-06-04|General Electric Company|Rotary assembly components and methods of fabricating such components|
    FR2963577A1|2010-08-06|2012-02-10|Snecma|PROCESS FOR PRODUCING A TURBOMACHINE DRUM|
    WO2014118464A1|2013-01-31|2014-08-07|Snecma|Auxiliary device for welding spindle disks, having a damping belt, and friction welding method|
    US8163399B2|2004-10-08|2012-04-24|GM Global Technology Operations LLC|Damped products and methods of making and using the same|
    US8758902B2|2007-07-20|2014-06-24|GM Global Technology Operations LLC|Damped product with an insert having a layer including graphite thereon and methods of making and using the same|
    US20120064255A1|2010-09-09|2012-03-15|Aps Materials, Inc.|Vibration damping coating|US10082184B2|2015-03-02|2018-09-25|Rolls-Royce Corporation|System and method for eliminating adverse clutch vibratory responses|
    GB201505631D0|2015-04-01|2015-05-13|Rolls Royce Plc|Friction welding vibration damping|
    GB201602685D0|2016-02-16|2016-03-30|Rolls Royce Plc|Manufacture of a drum for a gas turbine engine|
    EP3238868A1|2016-04-27|2017-11-01|MTU Aero Engines GmbH|Method for producing a rotor blade for a fluid flow engine|
    CN109611375B|2018-12-10|2020-09-25|中国航发四川燃气涡轮研究院|Outer ring hook structure for inhibiting vibration of stator blades with small aspect ratio|
    CN111719108A|2020-05-18|2020-09-29|南阳浩帆车辆部件有限公司|Heat treatment process and machining method of high-speed rail reducer gear|
    CN112496521B|2020-11-10|2021-12-24|中国航发沈阳黎明航空发动机有限责任公司|Improve Ti2Welding and heat treatment method for welding seam quality of AlNb alloy|
    法律状态:
    2015-01-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-11| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-03| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450610A|FR3016819B1|2014-01-24|2014-01-24|INERTIAL FRICTION WELDING PROCESS OF TWO PARTS OF A TURBOMACHINE ROTATING SUBASSEMBLY|FR1450610A| FR3016819B1|2014-01-24|2014-01-24|INERTIAL FRICTION WELDING PROCESS OF TWO PARTS OF A TURBOMACHINE ROTATING SUBASSEMBLY|
    US15/112,610| US9597748B2|2014-01-24|2015-01-16|Inertia friction welding method for welding together two portions of a rotary subassembly of a turbine engine|
    PCT/FR2015/050112| WO2015110746A1|2014-01-24|2015-01-16|Method for inertia friction welding of two parts of a rotating sub-assembly of a turbomachine|
    GB1612137.8A| GB2536392B|2014-01-24|2015-01-16|An inertia friction welding method for welding together two portions of a rotary sub-assembly of a turbine engine|
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