• 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:
    PROCESS FOR CARRYING OUT A METALLIC REINFORCEMENT OF A TURBOMACHINE BLADE The present invention relates to a process for making a solid part, successively comprising a step (240) of deformation by forging a metal bar (40) through two dies, in order to obtain an intermediate piece (50) comprising two fins (51) on both sides of a full part (53) able to form the base (39) of this metallic reinforcement (30), these two fins (51) presenting an opening angle? ; a step (250) of deformation of these fins (51) of this intermediate piece (50), modifying the opening angle (Alpha), in order to obtain the final shape of the metallic reinforcement (30) of the leading edge or edge of leakage of turbomachine blades.
    公开号:BR112012032828B1
    申请号:R112012032828-0
    申请日:2011-06-23
    公开日:2020-12-01
    发明作者:Christine Hottier；Bertrand Lamaison；Jacques Abousefian
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a process for carrying out a metallic reinforcement of a composite or metallic turbomachine blade.
    [0002] More particularly the invention relates to a process of making a metallic reinforcement of the leading edge of a turbomachine blade.
    [0003] The field of the invention is that of turbomachinery and more particularly that of fan blades, in composite or metallic material, of turbomachinery and whose leading edge includes a metallic structural reinforcement.
    [0004] However, the invention is also applicable for the realization of a metallic reinforcement intended to reinforce, terrestrial or aeronautical, and notably a helicopter turbomotor or an airplane turbo-reactor.
    [0005] The invention is also applicable to the realization of any massive pieces of complex geometric shape.
    [0006] Remember that the leading edge corresponds to the front part of an aerodynamic profile that faces the air flow and that divides the air flow into a soffit air flow and an outflow air flow. The trailing edge corresponds to the rear part of an aerodynamic profile where the soffit and extrados flow are joined.
    [0007] The turbomachine blades, and especially the fan blades, undergo important mechanical stresses, notably linked to the speed of rotation, and must satisfy strict conditions of weight and volume. One of the options considered to discard the blades is the use of composite materials for their manufacture.
    [0008] It is known to equip the fan blades of a turbomachinery made of composite materials, of a metallic structural reinforcement that extend throughout the height of the blade and, in addition, of its leading edge as mentioned in the document EP 1908919 deposited by SNECMA . This reinforcement allows to protect the set of composite blades, when a foreign body impacts on the fan, such as, for example, a bird, hail or stones.
    [0009] In particular, the metallic structural reinforcement protects the leading edge of the composite blade, avoiding risks of delamination, fiber breakage or damage by fiber / matrix separation.
    [0010] Classically, a turbomachine blade comprises an aerodynamic surface extending, according to a first direction, between a leading edge and a trailing edge and, according to a second direction substantially perpendicular to the first direction, between a base and a top of the shovel. The metallic structural reinforcement takes the shape of the leading edge of the blade's aerodynamic surface and extends along the first direction beyond the leading edge of the blade's aerodynamic surface to take on the shape of the soffit and soffit profile and according to the second direction between base and top of the blade.
    [0011] In a known way, the metallic structural reinforcement is a titanium metal part made entirely by milling from a block of material.
    [0012] However, the metallic reinforcement of a blade leading edge is a complex piece to make, requiring numerous retaking operations and complex tools, implying significant realization costs.
    [0013] In this context, the invention aims to solve the problems mentioned above, proposing a process of making a metallic reinforcement of the leading edge or trailing edge of the turbomachine blade, allowing to significantly reduce the costs of making that part and of simplify the manufacturing range.
    [0014] For this purpose, the invention proposes a process for carrying out a metallic reinforcement of the leading edge or trailing edge of a turbomachine blade, comprising: -a deformation step by forging a metal bar through two dies, in order to obtain an intermediate piece comprising two fins on both sides of a full part capable of forming the base of this metallic reinforcement, these two fins having an opening angle a; -a step of deformation of these fins of this intermediate piece, modifying the opening angle a, in order to obtain the final shape of the metallic reinforcement of the leading edge or trailing edge of turbomachine blades.
    [0015] Forging step by forging is understood as a forming operation of metals by forging, consisting of pushing a ductile material (made ductile by heating) through an orifice, or a die. Thus, during the first stage of forging deformation of the metal bar, the heated solid metal is placed in a tool, in order to push the material out through an orifice or die adjusted (a) in the tool by plastic flow.
    [0016] The forging deformation stage is similar to a deformation stage by direct or inverse spinning which consists of placing heated solid metal, at the spinning temperature of the material, that is, in an environment at a temperature at least equal to 250 degrees Celsius, in a tool and make it come out through an orifice, usually a die, which exerts an impulse. After a certain effort, there is a plastic flow of the metal through the die.
    [0017] The forging deformation process, according to the invention, is therefore different from a modeling process that consists of deforming the material to fill an impression. In addition, modeling is a deformation process that consists of displacing the metallic material perpendicularly in the touch direction of the tool.
    [0018] Thanks to the invention, the metallic structural reinforcement in a complex way is manufactured, in a simple and fast way, from a simple metal bar and a succession of simple forging steps, thus allowing to significantly reduce the manufacturing costs of that part , notably for the use of simple tools and machines.
    [0019] In addition, the realization of a metallic structural reinforcement of a turbomachine blade, from a metallic bar and not from metallic plates, also allows to minimize the falls of materials and, therefore, the costs of manufacturing that reinforcement. .
    [0020] This process of realization thus allows to get rid of the complex realization of reinforcement by milling in the mass from parts that need a large volume of material and, therefore, allows a reduction in the quantities of raw material used.
    [0021] The process of making a metallic reinforcement of a turbomachine blade, according to the invention, can also present one or more of the characteristics below, considered individually or according to all technically possible combinations; -this metal deformation stage of this metal barrier, the realization process includes a bending stage of this metal bar, in a direction perpendicular to the longitudinal axis of that bar; -previously to this stage of deformation by the forging of this metal bar, the realization process includes a stage of filling this metal bar in a tool that presents an impression corresponding to the final shape of the full base of this metallic reinforcement; -this stage of filling of this metal bar and this stage of forging deformation of this metal bar are carried out in the same tool by means of a plurality of punches; -this metal bar filling stage is carried out hot; -this metal bar filling stage, this forging deformation stage of this metal bar is carried out continuously without cooling the tool; -this arching stage of this metal bar, this stage of forging deformation of this metal bar and this stage of deformation of this intermediate part are carried out hot; -this arching step of this metal bar comprises: .a first arching sub-step of this metal bar according to a first direction perpendicular to the longitudinal axis of that bar; .a second sub-step of arching of this metal bar, according to a second direction perpendicular to that first direction and perpendicular to the longitudinal axis of that bar; -this process comprises a stage of making a preform on this metal bar, in order to facilitate the positioning of the tool on this bar, during this stage of deformation by forging; -this forging deformation step is a reverse spinning step; -this forging deformation stage is carried out by means of at least one punch in two successive operations; -this deformation stage of these fins of this intermediate part simultaneously performs the final twist of this intermediate part; -this stage of deformation of these fins of this intermediate part performs, simultaneously: -the completion of the shape of the internal radius of the metallic reinforcement; -the formation of the lateral flanks and the metallic reinforcement; -the completion of the twist of this metallic reinforcement.
    [0022] The present invention also relates to an intermediate piece obtained by the process of making, according to the invention;
    [0023] The present invention also relates to a metallic part, characterized by the fact that it comprises two fins on both sides of a full part capable of forming the base of a metallic reinforcement of leading edge or trailing edge of blade. turbomachinery.
    [0024] Other characteristics and advantages of the invention will stand out more clearly from the description given below, by way of indication and in no way limiting, with reference to the attached figures, among which: -Figure 1 represents a side view of a shovel comprising a metallic reinforcement of the leading edge obtained by means of the realization process, according to the invention; figure 2 represents a partial sectional view of figure 1, according to a section plane AA; figure 3 represents a synoptic diagram showing the main stages of carrying out a metallic reinforcement of the leading edge of the turbomachine blade of the carrying out process, according to the invention; figures 4A, 4B, 4C, 4D, 4E illustrate the structural evolution of the metallic reinforcement, during the different stages of the realization process illustrated in figure 3; figures 5A, 5B represent partial cross-sectional views of the metallic reinforcement of the leading edge of the turbomachine blade, during the third stage of the process illustrated in figure 3; figure 6 and figure 7 represent partial sectional views of the metallic reinforcement of the leading edge of the turbomachine blade, during the process step, illustrated in figure 3; figure 8 represents a partial perspective view of the metallic reinforcement of the leading edge of a turbomachine blade, during the fifth stage of the process illustrated in figure 3.
    [0025] In all figures, common elements bear the same reference numbers, unless otherwise specified.
    [0026] Figure 1 represents a side view of a blade that includes a metallic structural reinforcement of the leading edge obtained through the realization process, according to the invention.
    [0027] The blade 10 illustrated is, for example, a mobile blowing blade of a turbomachine (not shown).
    [0028] The paddle 10 has an aerodynamic surface 12 that extends, according to a first axial direction 14 between a leading edge 16 and a trailing edge 18 and according to a second radial direction 20 substantially perpendicular to the first direction 14 between a base 22 e4 a top 24.
    [0029] The aerodynamic surface 12 forms the extruder face 13 and soffit 11 of the paddle 10, only the extruder face 13 of the paddle 10 is shown in figure 1. The soffit 11 and extruder 13 form the side faces of the paddle 10 that connect the edge leading 16 to trailing edge 18 of paddle 10.
    [0030] In this embodiment, paddle 10 is a composite paddle typically obtained by covering a woven composite material. As an example, the composite material used can be composed of a bond of woven carbon fibers and a resinous matrix, the whole being formed by molding by means of a RTM type vacuum resin injection process (for Resin Transfer Molding).
    [0031] The blade 10 comprises a metallic structural reinforcement 30, glued at the level of its leading edge 16 and which extends at the same time according to the first direction 14 beyond the leading edge 16 of the aerodynamic surface 12 of the blade 10 and according to second direction 20 between the base 22 and the top 24 of the blade.
    [0032] As shown in figure 2, the structural reinforcement 30 takes the form of the leading edge 16 of the aerodynamic surface 12 of the blade 10 which extends to form a leading edge 31, said reinforcement leading edge.
    [0033] Classically, structural reinforcement 30 is a monoblock piece comprising a substantially V-shaped section that has a base 39 that forms the leading edge 31 and extended by two lateral flanks 35 and 37 that take shape respectively the soffit 11 and the soffit 13 of the aerodynamic surface 12 of the blade. Flanks 35, 37 have a tapered or narrowed profile towards the trailing edge of the blade.
    [0034] The base 39 comprises a rounded internal profile 33 able to take the rounded shape of the leading edge 16 of the blade 10.
    [0035] The structural reinforcement 30 is metallic and preferably based on titanium. This material, in fact, has a great capacity for absorbing energy due to shocks. The reinforcement is glued to the paddle 10 using glue known to the technician, such as, for example, cyanoacrylic glue or even epoxy.
    [0036] This type of metallic structural reinforcement 30 used for the reinforcement of a turbomachine composite blade is more particularly described notably in patent application EP 1908919.
    [0037] The process, according to the invention, allows a structural reinforcement to be carried out, as shown in figure 2, figure 2 illustrating the reinforcement 30 in its final state mounted on a mobile fan blade 10.
    [0038] Figure 3 represents a synoptic scheme, illustrating the main steps of a process 200, according to the invention, for the realization of a metallic structural reinforcement 30 of the leading edge of the blade 10, as illustrated in figures 1 and two.
    [0039] The first step 210 of the realization process 200 is a forging step of a straight metal bar 40 (illustrated in figure 4A), allowing to bend that bar 40, in a direction perpendicular to the longitudinal axis AA of bar 40, as shown in figure 4B.
    [0040] Metal bar 40 is a titanium bar with a circular section of the order of a few millimeters in diameter; the diameter of the section varies depending on the user's needs and the thickness of the material needed to make the final piece.
    [0041] During this first stage of forging, the metal bar 40 is deformed, in order to present a first bending, according to a first Z direction by means of a press, for example, an isothermal press brought to a temperature comprised between 700 ° C and 940 ° C to have good titanium deformation properties at low deformation speed.
    [0042] The second step 220 of the process 200 is a forging step of the arcuate metal bar 40 'obtained during the previous step (illustrated in figure 4B0, in order to obtain a second arching of that bar 40, in a direction that it is perpendicular to the longitudinal axis AA 'and to the Z axis. Thus, according to the reference illustrated in figure 4B, the second arch of the bar 40 is carried out in the Y direction, in order to obtain a metal bar 40' 'with a double arch (that is, according to two directions), as illustrated in figure 4C.
    [0043] This step can also be performed, for example, by means of an isothermal press brought to a temperature between 700 ° C and 940 ° C to have good deformation properties of Titanium under low deformation speed. As an example, the first and second stages can be carried out using a screw press and a punch / die tool.
    [0044] These first two steps 210, 220 allow to twist the metallic bar 40 substantially straight, according to the neutral fiber of the final metallic reinforcement 30, as illustrated in figures 1 and 2.
    [0045] The third step 230 of the process 200 is a forging step of the metal bar 40 "doubly arched by a press operation of the metal bar 40" in a tool 100, as illustrated in figures 5A and 5B.
    [0046] This step 230 is performed by pre-placing the 40 "twisted metal bar on tool 100, as shown in figure 5A. The 40" metal bar is then deformed by a filler under the action of a movable punch 120, in order to fill the impression 140 of a matrix 110, as illustrated in figure 5B. A 40 ”piece is then obtained, whose shape corresponds to the shape of the impression 140 of the matrix 110. The punch 120 has a substantially flat contact surface 121 able to contact the 40 ”metal bar inserted in the tool and able to deform it, in order to insert it in the impression 140 under the pressure exerted by the punch 120.
    [0047] The impression 140 of the tool 100 shows the final double arching of the leading edge 31 of the metallic reinforcement of the turbomachine blade and corresponds to the final shape of the base 39 of the metallic reinforcement 30.
    [0048] This third step 230 is performed under a press, typically by means of a screw press, at a temperature in the order of 940 ° C. At this temperature, titanium has an elongation rate greater than 35%, which allows important deformations to be made without degrading the properties of titanium.
    [0049] The fourth step 240 of the process 200 is a forging step of that metal bar 40 ’’ ’obtained after filling by deformation operation of the metal bar through dies, such as a spinning forging operation.
    [0050] Spinning is a method of forming metals by forging. It consists of pushing a ductile material (made ductile by heating) through the hole, or a die. Spinning consists of placing solid metal heated to the said spinning temperature in a tool and making it exit through an orifice, usually a spinneret, exerting an impulse. After a certain effort, there is a plastic flow through the spinneret.
    [0051] There are two variants of wiring: direct wiring, reverse wiring.
    [0052] Direct wiring consists of displacing the heated material previously placed on the tool, by means of a punch towards the die. Reverse wiring consists of moving the tool and the metal towards the die at the same time, which allows to get rid of the friction between the material and the tool.
    [0053] Advantageously, step 240 is a reverse spinning step, allowing the material to rise through the spinners. However, step 240 can also be a direct spinning step.
    [0054] In the case of direct wiring, and prior to this step 240, it is possible to make a preform 41 on the metal bar 40 by machining, as illustrated in figure 9, in order to facilitate the spinning step, notably by improved tool orientation.
    [0055] Preferably, this step of making a preform 41 on the metal bar 40 is carried out prior to the bending steps 210 and 220 of the process, according to the invention. This reverse spinning forging step is performed on the same tool 100 as the one used when the previous step. However, the punch 120 which has a flat contact surface 121 is replaced by a punch 160, the contact surface of which is more tapered, substantially V-shaped, as illustrated in figure 6.
    [0056] The specific shape of the punch 160 makes it possible to exert an impulse on the material of the metal bar 40 ’’ ’, deform it and push it inside the dies 130 located between the punch 160 and the matrix 110.
    [0057] This step 240 of reverse wiring can be performed twice with two different successive punches. A first punch 160, as previously described and illustrated in figure 6, and a second punch 170 illustrated in figure 7, which has a more pointed and tapered contact surface than the previous punch 160, in order to push more material into the die. 130 'between punch 170 and die 110.
    [0058] Typically, the shape of the punch 170 corresponds to the final shape of the internal profile 33 of the base 39 of the metal reinforcement 30 (illustrated in figure 2), that is, the rounded shape of the leading edge 16 of the blade 10.
    [0059] This step 240 of reverse wiring can be carried out in a single operation or in several operations with different punches. The choice of the number of operations will depend on the amount of material to sharpen, as well as on the complexity of the part to be manufactured.
    [0060] Advantageously, the different operations of step 240 are carried out successively without excessive manipulation by the operator and without significant variation in temperature (that is, without cooling the part and the tool). Similar to the previous step, step 240 of reverse spinning is carried out at a temperature of the order of 940 ° C (plus or minus 10 ° C) using a hydraulic press, screw press, etc.
    [0061] The reverse spinning step thus allows to obtain, by means of the limited number of operations, important deformations of the material in order to form an intermediate part 50 illustrated in figure 4D.
    [0062] The intermediate piece 50 is a substantially V-shaped or Y-shaped piece (Y-shape shown in figures 4E and 7) comprising two lateral fins 51 located on both sides of a full part 52 corresponding to the shape end of the base 39 of the metallic reinforcement 30, notably at the leading edge 31.
    [0063] At the ends of the intermediate part 50, trunnions 53, resulting from the initial metal bar 20, allow to maintain the part, when the different steps and operations are necessary, and also allow to make a reference in the different tools used.
    [0064] The intermediate part 50 is made in the tool 100, so that the two lateral fins 51 have an opening angle of approximately between 60 ° and 90 °, this to fulfill the requirements of metallurgical specification.
    [0065] The thicknesses of the lateral fins 51 correspond substantially to the thicknesses of the soffit and soffit flanks of the metal reinforcement 30, the fins 51 therefore have a profile that tapers progressively in the opposite direction to the leading edge of the intermediate piece 50. To do so, the dies 130 of the tool 100 are dimensioned, in order to obtain the profile and the thickness of the fins required for the realization of the metallic reinforcement 30.
    [0066] The fifth step 250 of the process 200 is a forging step, modifying the opening angle a of the side fins 51. When of this step 250, the two side fins 51 of the intermediate part 50 are approximated, that is, the angle a is reduced in order to obtain the final shape of the metallic reinforcement 30 of the leading edge of the turbomachine blade.
    [0067] This step 250 is performed on a 300-shaped tool (illustrated in figure 8) presenting the final and definitive shape of the metallic reinforcement 30 and by means of a classic press, such as hydraulic press, screw press, ... For this purpose, the tool 300 includes an impression 310 corresponding to the profile of the turbomachine blade to which the metallic reinforcement 30 is intended, as well as a counter-impression (not shown) that presents the external shape of the metallic reinforcement 30 and notably the profile the lateral flanks 35 to 37 taking the shape of the soffit 11 and the soffit 13 of the aerodynamic surface 12 of the blade 10, respectively.
    [0068] According to the embodiment shown as an example in figure 8, the intermediate part 50 is positioned on the tool 300, in order to rest on the impression 310.
    [0069] The two fins 51 are then folded in the direction of the impression 210 by the counter-impression, in order to reduce the angle a and form the final profile of the metallic reinforcement 30.
    [0070] Advantageously, the intermediate part 50 is twisted simultaneously with the deformation of the fins 51 by means of the tool 300, in order to end the twisting of the part.
    [0071] This step 250 therefore allows, simultaneously, to: -finalize the shape of the internal radius 33 of the metallic reinforcement 30; -form the lateral flanks 35 and 37 of the metallic reinforcement 30; -finalize the torsion of the metallic reinforcement 30.
    [0072] However, according to another embodiment, these different operations can be carried out independently, if necessary.
    [0073] Similar to the previous steps 230, 240, step 250 is carried out at a temperature in the order of 940 ° C.
    [0074] The metallic reinforcement 30 thus obtained when step 250 is demoulded, preferably hot, in order to facilitate the demoulding of the piece. However, demoulding can also be carried out cold.
    [0075] In order to facilitate the demoulding of the metallic reinforcement 30, notably in the cold, the impression 310 can be constituted by a plurality of movable or removable sections and able to be disassembled individually.
    [0076] In order to facilitate demoulding, it is also possible to initially prepare the tool 300, depositing a protective layer on the impression 310 in order to prevent the reinforcement 30 from sticking on the tool 300. As an example, this layer protective layer may be a layer of lu oxide.
    [0077] Finally, the sixth step 260 of the process of making 200 is an optional step of finishing and resumption of reinforcement 30 by machining. This finishing step 260 consists notably: -in the resumption of flanks 35, 37 (this step consists notably in deviations from flanks 35, 37 and in the tapering of the soffit and soffit flanks 35, 37); - when polishing the reinforcement 30, in order to obtain the required surface condition.
    [0078] Figure 4E illustrates the reinforcement 30 in its final state obtained by the realization process, according to the invention.
    [0079] In association with these main stages of realization, the process, according to the invention, can also include non-destructive control steps of the reinforcement 30, allowing to ensure the geometric and metallurgical conformity of the obtained set. As an example, non-destructive controls can be performed by a process of control by optical rays (by white light) or non-contact ultrasound.
    [0080] The process, according to the invention, has been described mainly for a metallic structural reinforcement based on titanium; however, the process, according to the invention, is also applicable with nickel-based or steel-based materials.
    [0081] The process, according to the invention, was mainly described for making a metallic reinforcement from a titanium-based metal bar; however, the invention is also applicable with the use of a metal bar previously reinforced, for example, by SiC-Ti.
    [0082] An example of making a titanium-reinforced metal bar would be, for example, a metal bar that contains a core reinforced by SiC-Ti and a titanium wrap. This reinforced metal bar can be obtained, for example, by a co-spinning process that consists of passing a Sic-Ti bar inside a spinneret (that is, a reduction cone), surrounded by a titanium sleeve. . The forces of compression and heating, generated by the friction between the two materials with their interface, ensure an intimate connection between the two materials.
    [0083] The SiC-Ti core can advantageously be positioned on the metal bar, so as to follow or not the deformation of the metal bar, during the process, according to the invention.
    [0084] The process, according to the invention, can also include previously a machining step of the reinforced metal bar obtained, before carrying out the forging steps, for example, by mechanical or chemical machining.
    [0085] Of course, it is also considered to make a reinforced metal bar, comprising a non-reinforced core and a reinforced wrap.
    [0086] Advantageously, the different bending, filling, spinning and twisting operations are carried out on a piece that forms metallic reinforcement carried at a temperature of the order of 940 ° C, at about ten percent, the environment and the tool can adopt different temperatures than those mentioned in the example described above.
    [0087] The invention has been particularly described for the realization of a metallic reinforcement of a composite turbomachine blade; however, the invention is also applicable for the realization of a metallic reinforcement of a metal turbomachine blade.
    [0088] The invention has been particularly described for the realization of a metallic reinforcement of a leading edge of a turbomachine blade; however, the invention is also applicable for making a metallic reinforcement of a trailing edge of a turbomachine blade.
    [0089] The other advantages of the invention are notably the following: -reduction of realization costs; -reduction in the realization time; -simplification of the manufacturing range; -reduction of tool costs; -reduced material costs.
    权利要求:
    Claims (13)
    [0001]
    1. Process of making (200) a metallic reinforcement (30) of the leading edge or trailing edge of the turbomachine blade (10), characterized by the fact that it comprises: -a deformation step (240) by forging a metallic bar (40), the metal being pushed in a direction essentially perpendicular to the longitudinal axis of the bar through two dies, in order to obtain an intermediate piece (50) comprising two fins (51) on both sides of a full part ( 53) able to form the base (39) of said metallic reinforcement (30), said two fins (51) having an opening angle a; -a step (250) of deformation of said fins (51) of said intermediate piece (50), modifying the opening angle a, in order to obtain the final shape of the metallic reinforcement (30) of the leading edge or edge of Turbomachine blade leak.
    [0002]
    2. Realization process (200), according to claim 1, characterized by the fact that, prior to said step (240) of forging deformation of said metal bar (40), the realization process (200) comprises a step (210, 220) of bending said metal bar (40), in a direction perpendicular to the longitudinal axis of said bar (40).
    [0003]
    3. Realization process (200), according to either of claims 1 or 2, characterized in that, prior to said step (240) of forging deformation of said metal bar (40), the realization process (200 ) comprise a step (230) of filling said metal bar (40) in a tool (100) showing an impression (140) corresponding to the final shape of the base (39) full of said metal reinforcement (30).
    [0004]
    4. Realization process (200), according to claim 3, characterized in that said step (230) of filling said metal bar (40) and said step (240) of forging deformation of said metal bar (40) be carried out on the same tool (100) by means of a plurality of punches (120, 160, 170).
    [0005]
    Process for carrying out (200) according to either of claims 3 or 4, characterized in that said step (230) of filling said metal bar (40) is carried out hot.
    [0006]
    Process for carrying out (200) according to any one of claims 3 to 5, characterized in that said step (230) of filling said metal bar (40), said step (240) of deformation by forging said metal bar (40) are carried out continuously without cooling the tool (100).
    [0007]
    Process for carrying out (200) according to any one of claims 2 to 6, characterized in that said step (210, 220) of bending said metal bar (40), said step (240) of deformation by forging said metal bar (40) and said deformation step (250) of said intermediate piece (50) to be carried out in the hot state.
    [0008]
    8. Realization process (200) according to any one of claims 2 to 7, characterized in that said step (210, 220) of bending said metal bar (40) comprises: -a first sub-step of arching of said metal bar (40), according to a first direction perpendicular to the longitudinal axis of said bar (40); - a second sub-step (220) of bending said metal bar (40), according to a second direction perpendicular to said first direction and perpendicular to the longitudinal axis of said bar (40).
    [0009]
    9. Realization process (200), according to any one of claims 1 to 8, characterized in that said process comprises a stage of realization of a preform (41) on said metal bar (40), of in order to facilitate the positioning of the tool on said bar (40), during said deformation step by forge (240).
    [0010]
    10. Process (200), according to any one of claims 1 to 8, characterized in that the said deformation step by forging is a reverse spinning step.
    [0011]
    11. Execution process (200) according to any one of claims 1 to 10, characterized in that said deformation step by forging is carried out by means of at least one punch in two successive operations.
    [0012]
    12. Implementation process (200), according to any one of claims 1 to 11, characterized in that said step (250) of deformation of said fins (51) of said intermediate part simultaneously performs the final twisting of the said intermediate part (50).
    [0013]
    13. Realization process (200), according to any one of claims 1 to 12, characterized in that said step (250) of deformation of said fins (51) of said intermediate piece performs simultaneously: -the finalization the shape of the internal radius (33) of the metallic reinforcement (30); -the formation of the lateral flanks (35) and (37) of the metallic reinforcement (30); - the completion of the torsion of said metallic reinforcement (30).
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    同族专利:
    公开号 | 公开日
    CN102947596A|2013-02-27|
    WO2011161385A1|2011-12-29|
    RU2568229C2|2015-11-10|
    RU2013103015A|2014-07-27|
    CN102947596B|2016-04-20|
    US9027245B2|2015-05-12|
    FR2961866A1|2011-12-30|
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    CA2802943A1|2011-12-29|
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    EP2585721B1|2016-10-05|
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    EP2585721A1|2013-05-01|
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    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-06-16| B06A| Notification to applicant to reply to the report for non-patentability or inadequacy of the application according art. 36 industrial patent law|
    2020-11-10| B09A| Decision: intention to grant|
    2020-12-01| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 23/06/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1055066|2010-06-24|
    FR1055066A|FR2961866B1|2010-06-24|2010-06-24|PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT|
    PCT/FR2011/051454|WO2011161385A1|2010-06-24|2011-06-23|Method for producing a metal reinforcement for a turbomachine blade|
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