• 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 manufacturing a turbomachine blade (25) comprising a lower surface and an upper surface separated from each other by an internal cooling air circulation space, this blade (25) comprising a top (S) with a closing wall (29) joining the walls of the suction and suction surface in the region of this peak (S) to define a bathtub shape, this closure wall having through holes. The molded closure wall (29) has a large nominal thickness with wells locally reducing (36, 37) this thickness at each through hole to facilitate etching removal of alumina rods delimiting these holes. The closure wall (29) thus having a high nominal thickness, it can then be machined to form reliefs or complex shapes inside the bath.
    公开号:FR3030333A1
    申请号:FR1462614
    申请日:2014-12-17
    公开日:2016-06-24
    发明作者:Dominique Coyez；Christian Bariaud；Sami Benichou；Jean-Claude Marcel Augsute Hanny
    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 or a turboprop engine. SUMMARY OF THE INVENTION . 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. 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.
    [0002] 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.
    [0003] 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 closing wall that is not visible in FIG. 2 is set back 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. Such a blade is made by molding a metal material, in particular using a first and a second core 17 and 18 to delimit its internal space and the bath area, as illustrated schematically in Figure 3. These two cores 17 and 18 are spaced from each other along the span direction EV by a small distance, denoted d, and which corresponds to the closure wall marked by 19 in FIG. 3. The second core 18 is traversed by alumina rods 21 parallel to the axis EV, which pass through the region of the closure wall 19, and whose ends are taken in the first core 17. These rods allow one hand to maintain in position these nuclei the one against the other during the casting operation, and they also allow to form holes ensuring dedusting when the blade is then in operation. After casting and cooling of the alloy constituting the blade, cores 17 and 18 are removed by etching, which leads to the situation of FIG. 4, where portions of alumina rods still pass through the closure wall. 19. The removal of the remaining portions of alumina rods, called shake, is achieved with a second etching. The dawn is then, as can be seen in FIG. 5, completely cleared of the devices used for its molding, and it has at its closure wall 19 two through holes 22 corresponding to the removed alumina rods. These holes 22 are the dedusting holes ensuring the evacuation of any dust to prevent them from accumulating inside the blade when it is in operation.
    [0004] The increased performance requirements lead to optimizing the cooling of the bath, for example by providing ribs or internal partitions carried by the bath floor, that is to say the closing wall 19. These partitions or ribs identified by 23 and 24 in the symbolic example of Figure 6 are to optimize the aerodynamics in the bath to subject the air flow to homogenize its cooling. The addition of such ribs or partitions significantly complicates the development of the second ceramic core 18. In fact, it is manufactured with a core box, that is to say a mold in two parts that open. deviating from each other, but in a demolding direction and which extends in a plane normal to the span axis of the blade. This demolding direction is represented by the arrows D in FIG. 6. The constraint of this demoulding direction, which results from manufacturing requirements, makes it possible for slots defining the ribs for the bottom of the bath to be end of the second core. Such slots would constitute undercuts making it impossible to demold the second core during its manufacture, because their orientations differ from the demolding direction. One possibility would be to manufacture a second core of several ceramic parts assembled to each other by gluing. This significantly complicates the manufacture and consequently tends to increase the scrap rate. The object of the invention is to provide a manufacturing method for achieving a wide variety of internal shapes at the bath without penalizing the cost and 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 separated from one another by an internal space of cooling air flow, this blade comprising a top with a closing wall joining the walls of the suction and suction surface in the region of this peak to define a bathtub shape, this closure wall comprising through holes, the method comprising a molding step using a core defining the bath shape and alumina rods delimiting each through hole, an etching operation of the core and an etching operation of the alumina rods to remove this core and these rods after molding, characterized in that the core is provided with bumps at each through-hole to provide the closure wall as a molding compound with a nominal thickness greater than the thickness of the other walls of the blade and a reduced thickness at each through hole, and in that the method comprises a machining operation of the closure wall to form one or more shapes in relief in the bottom bathtub. This manufacturing method thus makes it possible to manufacture a blade having a bath having a complex internal shape without involving a fundamental modification of the operations and tools specific to the molding of the blank from which the blade is formed.
    [0005] The invention also relates to a method thus defined, wherein the core is shaped to give the closure wall a nominal thickness and a reduced thickness at through holes which are such that the ratio of the nominal thickness to the thickness reduced is greater than or equal to 2.5. The invention also relates to a method thus defined, wherein the core is shaped to give the closure wall thicknesses such that the ratio of the nominal thickness to the reduced thickness is greater than or equal to 5. The invention concerns also a method thus defined, wherein the machining operation of the closure wall is arranged to form one or more ribs or internal partitions.
    [0006] The invention also relates to the molding means for the manufacture of a blade thus defined, comprising a core box arranged to manufacture a core thus defined. The invention also relates to a turbomachine turbine comprising a blade manufactured according to a method thus defined.
    [0007] The invention also relates to a turbomachine comprising a turbine thus defined. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 already described is an overview of a turbofan engine shown in lateral section; Figure 2 already described is an overview of a reactor blade; Figure 3 already described is a sectional view of a blade of the state of the art during its molding; Figure 4 already described is a sectional view of a blade of the state of the art after removal of the cores used for molding; Figure 5 already described is a sectional view of a blade of the state of the art after removal of the rods of alumina; Figure 6 is a top view of a dawn tub provided with additional internal ribs; Figure 7 is a sectional view of a blade according to the invention during its molding; Figure 8 is a sectional view of a blade according to the invention after removal of the cores used for molding; Figure 9 is a sectional view of a blade according to the invention after removal of alumina rods. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS The blade according to the invention, indicated by 25 in FIG. 7, also has a blade 26 carried by a foot and having a shape corresponding generally to that of the blade of FIGS. 2 to 6. The lower and upper terms used in the following mean depending on the orientation of the figures, wherein the blade is upwardly carried by a foot downwards although not shown. This blade also has a lower surface wall and an extrados wall spaced from one another and which are joined at the level of the blade crown S by a closure wall marked 29 in FIGS. 7 to 9. This closure wall is perpendicular to the span direction EV of the blade and recessed towards the axis AX of rotation of the blade, relative to the free edges of the walls of the lower and upper surfaces.
    [0008] This closure wall delimits jointly with the free edges of the intrados and extrados a hollow portion open in the opposite direction to the axis AX, called bathtub. The blade is also manufactured by molding a metallic material, with a first and a second core 27 and 28 defining the internal space and the bath, as shown in FIG. 7. These two cores 27 and 28 are spaced apart. of the other along the span direction EV, to delimit the closing wall marked by 29. This closure wall 29 here has a nominal thickness, noted D, significantly higher than in the case of the blades of the state of the art so as to be machined to form additional partitions or ribs such as those of Figure 6. This closure wall is traversed by two rods of alumina 31, 32, taken in the two cores 27 and 28 to hold them in position relative to each other during the casting of the alloy constituting the dawn per se. After casting and cooling of the alloy, the cores 27 and 28 are removed by etching, which leads to the situation of FIG. 8, where portions of alumina rods still pass through the closure wall 29. remaining portions of alumina stems, called shake, is made with a second chemical attack, which thus completely clears the dawn of the elements used for its molding.
    [0009] To make the shakeout operation possible, the thickness of the closure wall 29 is reduced at each alumina rod passage to a value d, which is significantly lower than the nominal thickness D of this wall. closure 29. The thickness d which corresponds to the stall thickness is preferably greater than six tenths of a millimeter and less than eight tenths of a millimeter, whereas the nominal thickness of the wall 29 may be of the order of two millimeters, and preferably greater than or equal to three millimeters. Thus, the ratio of the nominal thickness D of the closure wall 29 to the reduced thickness d of this wall at each passage of albumin stem 31, 32 is greater than or equal to 2.5 and preferably greater than or more than 5. More particularly, the lower face 33 of the closure wall 29, namely the face closest to the axis AX and which gives on the internal space of the blade is substantially flat, as well as the end of the core 27 which defines this face. The upper face 34 of this wall, namely the farthest from the axis AX and which delimits the bottom of the bath, has on the contrary a hollow or well at each passage of alumina rod, these wells being marked by 36 and 37. As is apparent from the figures, this particular form of the upper face, with wells, results from two corresponding reliefs or bumps made at the end of the core 28 at each passage of alumina rod. These bumps can be obtained simply by making recesses at the corresponding zone of the core box, that is to say the mold, used for the manufacture of the second core. Each well may have a flared conical cylindrical shape or another purpose of constituting for the shaking operation a reservoir receiving the shake liquid which is a basic bath. The thickness of the wall at the bottom of each well, noted d, corresponds to the maximum possible thickness to ensure the shake stems. In the example of the figures, each well has a hemispherical bottom extended by a cylindrical side, but different forms can be envisaged, depending in particular on the constraints due to the molding process which is provided for the manufacture of the blank intended to constitute the dawn. As shown diagrammatically in FIGS. 8 and 9, thanks to the wells 36 and 37, the closure wall 29 has a small thickness locally at each passage of alumina rod to allow the removal of these rods by basic attack in order to form the corresponding dusting holes, marked 38 and 39.
    [0010] The crude dawn which is shown in Figure 9 and has a bathtub at its top, but the bottom has a significant nominal thickness. It is thus possible to form in this bottom 29 ribs or partitions of complex shapes such as those of Figure 6, simply by machining the bath floor. In other words, the invention makes it possible to manufacture a blade having at its top a bath whose inner region can be provided with almost any type of rib, artifice, flow disturbance or the like, without complicating the molding process. Indeed, thanks to the bumps 36, 37 provided at the end of the second core 28, the closure wall 29 may have a high nominal thickness without the need for a specific process for removing the alumina rods of the closure wall after molding. The invention thus allows the manufacture of a complex bath dawn without penalizing the process of molding and manufacturing cores.
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. A method of manufacturing a turbomachine blade (25) comprising a lower surface wall and an extrados wall separated from each other by an internal cooling air circulation space, said blade (25) comprising an apex (S) with a closure wall (29) joining the intrados and extrados walls in the region of this apex (S) to define a bathtub shape, this closing wall (29) comprising through holes (38, 39), the method comprising a molding step using a core (28) delimiting the bath-shaped shape and alumina rods (31, 32) delimiting each through-hole (38, 39); etching of the core (28) and etching of the alumina rods (31, 32) to remove the core and rods after molding, characterized in that the core (18) is provided with bumps at the of each through-hole (38, 39) for imparting to the closure wall (29) as a molding product a nominal thickness (D) greater than the thickness of the other walls of the blade and a reduced thickness (d) at each through-hole (38, 39), and in that the method comprises a machining operation of the closing wall (29) for forming one or more raised shapes in the bottom of the bath.
    [0002]
    The method of claim 1, wherein the core (18) is shaped to provide the closure wall with a nominal thickness (D) and a reduced thickness (d) at through holes (38, 39) which are that the ratio of the nominal thickness (D) to the reduced thickness (d) is greater than or equal to 2.5.
    [0003]
    3. Method according to claim 2, wherein the core (18) is shaped to give the closure wall thicknesses (d, D) such as the ratio of the nominal thickness (D) to the reduced thickness (d). ) is greater than or equal to 5.
    [0004]
    4. Method according to one of claims 1 to 3, wherein the machining operation of the closure wall is arranged to form one or more ribs or internal partitions.
    [0005]
    5. Molding means for implementing the manufacturing method for the manufacture of a blade according to one of claims 1 to 4.
    [0006]
    Turbomachine turbine comprising a blade manufactured according to a process as defined in one of claims 1 to 4.
    [0007]
    7. A turbomachine comprising a turbine according to claim 6.
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    同族专利:
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    FR3030333B1|2017-01-20|
    US10533426B2|2020-01-14|
    CA2971289A1|2016-06-23|
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    CN107206473B|2019-07-12|
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    US20170328222A1|2017-11-16|
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    引用文献:
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    法律状态:
    2015-12-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-24| PLSC| Publication of the preliminary search report|Effective date: 20160624 |
    2016-12-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462614A|FR3030333B1|2014-12-17|2014-12-17|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE COMPRISING A TOP COMPRISING A COMPLEX TYPE BATHTUB|FR1462614A| FR3030333B1|2014-12-17|2014-12-17|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE COMPRISING A TOP COMPRISING A COMPLEX TYPE BATHTUB|
    CA2971289A| CA2971289A1|2014-12-17|2015-12-15|Method for manufacturing a turbine engine blade including a tip provided with a complex well|
    CN201580067848.9A| CN107206473B|2014-12-17|2015-12-15|It include the method for being equipped with the turbogenerator flabellum on top of Holes of Complicated Wells for manufacturing|
    JP2017532815A| JP6681904B2|2014-12-17|2015-12-15|Method of manufacturing a turbine engine blade including a tip with a complex well|
    EP15822972.4A| EP3233328B1|2014-12-17|2015-12-15|Method for manufacturing a turbine engine blade including a tip provided with a complex well|
    US15/536,475| US10533426B2|2014-12-17|2015-12-15|Method for manufacturing a turbine engine blade including a tip provided with a complex well|
    RU2017125136A| RU2706256C2|2014-12-17|2015-12-15|Method of making gas turbine engine blade comprising vertex with complex cavity|
    PCT/FR2015/053517| WO2016097586A1|2014-12-17|2015-12-15|Method for manufacturing a turbine engine blade including a tip provided with a complex well|
    BR112017012300-2A| BR112017012300B1|2014-12-17|2015-12-15|METHOD FOR MANUFACTURING A TURBINE ENGINE BLADE|
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