• 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:
    The invention relates to a method for producing a turbomachine blade (16) comprising a lower surface wall (17) and an extrados wall (18) separated from each other, said blade (16) comprising a top with a closure wall joining the intrados (17) and extrados (18) walls in the region of this summit to delimit the bottom (23) of a bathtub shape located at the top of the blade, the method comprising a molding step implementing a core defining the bath shape. According to the invention, there is provided a step of supplying metal material on the bottom (23) of the bath with a process of Direct Additive Laser Construction, to deposit on the bottom of the bath of the material to form in this bath an internal partition (28) carried by its bottom (23).
    公开号:FR3037974A1
    申请号:FR1556065
    申请日:2015-06-29
    公开日:2016-12-30
    发明作者:Matthieu Jean Luc Vollebregt；Coralie Guerard；Patrick Emilien Paul Emile Huchin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The invention relates to the manufacture of a turbine engine type aircraft engine blade, such as for example a turbojet engine or a turboprop engine. STATE OF THE PRIOR ART In such an engine, indicated by 1 in FIG. 1, air is admitted into an inlet sleeve 2 to pass through a fan comprising a series of rotating blades 3 before splitting into a central primary flow. and a secondary stream surrounding the primary stream. The primary flow is compressed by turbines 4 and 6 before reaching a combustion chamber 7, after which it relaxes through turbines 8, before being evacuated by generating a thrust. The secondary flow is propelled directly by the blower to generate a complementary thrust.
    [0002] Each turbine 8 comprises series of blades oriented radially and regularly spaced around a rotation shaft AX carried by an outer casing 9 surrounding the assembly. The cooling of the blades is ensured by circulating in each blade air taken upstream of the combustion and admitted at the bottom of the blade, this air being evacuated by holes through the walls of these blades. Such a blade, which is indicated by 11 in FIG. 2, comprises a foot P through which it is fixed to a rotating body, and a blade 12 carried by this foot P, the foot and the blade being separated by a platform 13. The blade 12 has a left twisted shape about an axis EV said span axis which is perpendicular to the axis AX. It comprises a base by which it is connected to the platform 13 and which extends radially to a vertex S which is the free end of this blade. The two main walls of the blade are its intrados wall 14 and its extrados wall which are spaced apart from each other. The top S of the blade 11 has a closing wall perpendicular to the direction EV, and which connects the walls of the intrados and extrados. This non-visible closure wall in FIG. 2 is recessed towards the axis AX with respect to the free edges of the intrados and extrados walls. It delimits jointly with these edges a hollow portion open in the opposite direction to the axis AX, called bathtub which is located at the head of the blade, that is to say at its top. Such a blade is manufactured by molding a metallic material, in particular using a core comprising a first core element and a second core element to delimit on the one hand the internal space of the blade body and on the other hand the internal space of the bathtub. These two core elements are spaced from each other along the span direction EV by a small distance. The increased performance requirements lead to optimizing the cooling of the bath, for example by providing wall or internal partitions carried by the bath floor. These partitions or ribs are designed to optimize aerodynamics in the bathtub to improve cooling at the top of the blade, including limiting leaks from the lower surface to the upper surface. The addition of such ribs or partitions significantly complicates the development of the second core member. Indeed, it is manufactured with a core box, that is to say a mold in two parts that open apart from each other, but in a demolding direction that s extends in a plane normal to the span axis of the blade. The constraint of this demoulding direction which results from manufacturing requirements means that slots delimiting the ribs for the bottom of the tub can not be provided at the end of the second core member. Such slots would constitute undercuts making it impossible to demold the second core element during its manufacture, because their orientations differ from the demolding direction.
    [0003] One possibility is to fabricate the second core member into a plurality of ceramic portions bonded to one another by gluing. This significantly complicates the manufacture and consequently tends to increase the scrap rate, in addition to giving rise to a core element having insufficient strength. The object of the invention is to provide a manufacturing process for achieving a wide variety of internal shapes at the bath without penalizing the scrap rate. SUMMARY OF THE INVENTION To this end, the subject of the invention is a method for manufacturing a turbomachine blade comprising a lower surface wall and an extrados wall spaced from one another, this blade comprising a top with a closure wall joining the intrados and extrados walls in the region of this apex to delimit a bottom of a bathtub shape located at the top of the blade, the method comprising a molding step implementing a core element delimiting the bath shape, characterized in that it comprises a step of supplying metal material on the bottom of the bath with an additive manufacturing process by adding metal material, in particular by depositing metal powder, to deposit on the bottom of the bath of the material to form in this bath an internal partition 20 by its bottom. According to the invention, the additive manufacturing method which is usually used to completely form the geometry of a part is here exploited to complete a casting piece. With this solution, any form of partition can be formed on the bottom of bath, without affecting the molding operation or the shape of the core elements to implement. Various additive manufacturing processes can be used, such as the Direct Additive Laser Construction method, generally designated by the trademark CLAD, the so-called Laser Metal Deposition process generally designated by the acronym LMD, the so-called Direct Metal Deposition process generally designated by the acronym DMD, or the so-called Direct Laser Metal Deposition process generally referred to by the acronym DLMD. The invention also relates to a method thus defined, comprising after the material supply step, a machining step with a method such as a method of machining by electro erosion of the deposited material. The invention also relates to a method thus defined, in which the material is deposited so as to extend from an edge of the intrados wall, to an edge of the extrados wall. The invention also relates to a turbomachine blade obtained with the method thus defined. The invention also relates to a turbomachine comprising a blade thus defined. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 already described is an overall view of a double flow turbojet engine shown in lateral section; Figure 2 already described is an overview of a reactor blade; Figure 3 is partial perspective view of a dawn tub as foundry foundry; Figure 4 is a schematic representation of the process used in the invention for providing material on the bottom of the dawn tub; Figure 5 is a partial perspective view of a bath in the bottom of which was deposited a material according to the invention for a machining operation to put the deposited material in the form of partition; Figure 6 is a partial perspective view of a vane bath 25 according to the invention comprising a partition obtained by deposition of material and by machining. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS As can be seen in FIG. 1, a blade 16, such as a casting shell, comprises a lower surface 17 and an extrados wall 18 which extend substantially in the span direction. EV of this blade, and whose upper edges, marked by 19 and 21 delimit the top of the blade 16. These walls of suction and extrados 17 and 18 are spaced apart from each other while being connected to each other. 1 to the other on the one hand at the leading edge of the blade, marked by 22, and on the other hand at the trailing edge of the blade which does not appear in FIG. these two edges extending approximately parallel to the span direction EV. These walls are still connected to each other at the top of the blade by a so-called closure wall, marked by 23, which extends perpendicular to the span direction, while being offset along the direction span of a certain height from the vertices of the edges 19 and 21. The edges 19 and 21 thus protrude from the closure wall they surround, to delimit with it the bath 24 of the blade tip of which they constitute the edges and whose closing wall constitutes the bottom.
    [0004] The basis of the invention is to use a so-called additive manufacturing process for bringing the metallic material to the bottom of the dawn tub, such as a cast iron, so as to form an internal partition in this tub. . The method used is a process of the metal powder fusion laser powder type with successive layer deposition. Other metal deposition methods can be envisaged. One such method which is usually designated by the trademark CLAD, namely the Direct Additive Laser Construction method consists of using an apparatus 26 for generating a laser beam 27 in order to melt on a substrate which is here the bottom 23 of the bath 24, one or more metal powders 29 provided by a nozzle 31, so as to successively constitute deposition layers 32 of a metallic material. This nozzle is a coaxial nozzle capable of producing homogeneous injection of metal powders through a laser beam. With this process, the powder melted by the laser is a homogeneous and dense deposit on the surface or layer that carries them, which is also fused during the process. Since there is no contact especially between the nozzle and the substrate, the process is free of wear. The successive deposits or stacks are protected throughout the process by a neutral gas to prevent oxidation problems. This method makes it possible to make deposits by targeting with a certain precision the places where the material is brought. It is also possible to use two different feed metals to achieve if necessary an alloy with progressive proportions according to the height. This makes it possible to optimize various aspects such as the mass, the adhesion with the substrate, that is to say the dilution and the porosity, as well as the properties of abradability, abrasiveness, expansion or others.
    [0005] In general, the deposited material is itself chosen as a function of the substrate to have a suitable mechanical strength, abradability, as well as compatibility with the substrate which are appropriate in particular for dilution and porosity. As can be seen in FIG. 1, the tub of the raw casting blade 15 comprises a bottom 23 which is plane, and according to the invention, an internal partition is formed on this flat bottom, by adding material according to the CLAD process, then by machining the material thus added to give it a surface condition and a rating corresponding to predefined criteria. As can be seen in FIG. 5, the material added by the CLAD method is deposited according to the trajectory and the shape of the partition to be produced, so as to constitute a supply of material 25 having a general shape corresponding to that of the partition to be obtained. As shown in FIG. 5, the material provided constitutes a deposit that can be relatively coarse in view of the tolerances to be obtained as regards the geometric definition of the finished partition. These dimensional tolerances are dictated by the aerodynamic stresses to which the dawn tub must respond in operation. The metal deposit, indicated by 25 in FIG. 5, thus constitutes the raw material from which the partition will be formed. This deposit is then machined to form the final partition, itself, which appears in Figure 6 in which it is marked 28. This machining can be achieved by electro erosion, according to the method known by the acronym EDM 3037974 7 meaning Electrical Discharge Machining, that is, machining by electric discharge. This machining can also be ensured by means of cutting tools of the milling cutter type or the like, which makes it possible to produce the form finish making it possible to constitute the partition 28 as such.
    [0006] The invention has been described with an additive process by layer-layer deposition laser powder melting, but other methods can be used. In particular, the SWET process, which means Superallow Welding at Elevated Temperature, can also be envisaged. In general, the method according to the invention thus makes it possible to manufacture a blade comprising at its bath level a wall that can have any type of shape, without thereby adding additional stress to the molding process involved in the manufacture of this dawn. 15
    权利要求:
    Claims (5)
    [0001]
    REVENDICATIONS1. A method of manufacturing a turbomachine blade (16) comprising a lower pressure surface (17) and an extrados wall (18) spaced apart from each other, said blade (16) comprising an apex with a wall closure system joining the intrados (17) and extrados (18) walls in the region of this apex to define a bottom (23) of a bathtub shape (24) situated at the top of the blade, the method comprising a molding step using a core element delimiting the bath shape, characterized in that it comprises a step of supplying metal material on the bottom (23) of the bath with an additive manufacturing process by adding metal material in particular by deposition of metal powder, to deposit on the bottom of the bath of the material (25) to form in this bath an internal partition (25, 28) carried by its bottom (23).
    [0002]
    2. Method according to claim 1, comprising after the step of adding material, a machining step, with a method such as a machining process by electro erosion of the material (25) deposited.
    [0003]
    The method of claim 1 or 2, wherein the material (25) is deposited to extend from an edge (19) of the intrados wall (17) to an edge (21) of the extrados wall (18).
    [0004]
    4. Turbomachine blade obtained with the method according to one of claims 1 to 3.
    [0005]
    5. Turbomachine comprising a blade according to claim 4.
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    同族专利:
    公开号 | 公开日
    CN107848204B|2020-05-05|
    EP3313597B1|2020-06-17|
    US20180193920A1|2018-07-12|
    FR3037974B1|2017-07-21|
    EP3313597A1|2018-05-02|
    CN107848204A|2018-03-27|
    WO2017001751A1|2017-01-05|
    引用文献:
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    法律状态:
    2016-06-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-30| PLSC| Publication of the preliminary search report|Effective date: 20161230 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1556065A|FR3037974B1|2015-06-29|2015-06-29|METHOD FOR MANUFACTURING A VANE COMPRISING A BATHTUB INTEGRATING A WALL|FR1556065A| FR3037974B1|2015-06-29|2015-06-29|METHOD FOR MANUFACTURING A VANE COMPRISING A BATHTUB INTEGRATING A WALL|
    PCT/FR2016/051580| WO2017001751A1|2015-06-29|2016-06-27|Method for manufacturing a blade comprising a squealer tip integrating a small wall|
    US15/741,146| US20180193920A1|2015-06-29|2016-06-27|Method for manufacturing a blade comprising a bathtub tip integrating a small wall|
    EP16750892.8A| EP3313597B1|2015-06-29|2016-06-27|Method for manufacturing a blade comprising a squealer tip integrating a small wall|
    CN201680038370.1A| CN107848204B|2015-06-29|2016-06-27|Method for manufacturing a blade comprising a concave tip integrated with a small wall|
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