• 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:
    Method for manufacturing a turbomachine part (7) in which a first raw casting element (8) which comprises a first face (81) and a second face opposite to each other is assembled by the second face on an orifice that has a second element (9) of said part (7), characterized in that the method comprises the steps of: • machining a cavity (83) through the first element (8) which opens to the first face (81) and the second face of the first element (8); Machining the first face (81) of the first element (8) so as to form a zone adapted to ensure the attachment of a conduit to the first element (8), the machining of the cavity (83) and the first face (51) being made using a machining reference linked to the second element (9).
    公开号:FR3046951A1
    申请号:FR1650492
    申请日:2016-01-21
    公开日:2017-07-28
    发明作者:Nicolas Pommier；Mathieu Bissardon；Mathieu Delalandre；Stephane Nicolas Piron；Olivier Renon
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL FIELD
    The present invention relates to a method for manufacturing a part of a turbomachine, and in particular to aircraft turbomachines, making it possible to obtain a final shape of the final piece that is as close as possible to the shape determined during the design of the engine. said room.
    The present invention also relates to the part that is obtained by the manufacturing process. The part may in particular be an exhaust casing of a turbomachine.
    More specifically, the present invention relates to a manufacturing method in which the part is obtained by assembling two elements, the two elements possibly being in particular an outer shell of an exhaust casing and a mouth for fixing a tube of output of a transient exhaust valve of the turbomachine.
    STATE OF THE ART
    During the manufacture of a part of a turbomachine which requires the assembly of a first element and a second element, it is known to produce the manufacture of said part according to the following steps: - Provide the first element and the second element, the first element being foundry. The first element comprises a gross foundry cavity in its center which integrally passes through said first element. - Assemble the first and the second element, for example by welding the first element on the second element. More specifically, the assembly of the two elements is achieved by positioning the first element on a hole that is made in the second element, so that once the two elements assembled, the cavity formed in the first element passes through said first element and than the second element. - Machining a first face of the first element so that the first face is adapted to be attached to a conduit. The machining may for example consist of a surfacing of said first surface to flatten it, followed by the production of several holes that can be tapped which form means for fixing with the conduit. In order to ensure the correct alignment of the raw casting cavity of the first element and of the conduit which will be fixed to the first face of said first element, machining of the bores is carried out using a machining reference system linked to the walls of the cavity foundry gross of the first element.
    However, such a manufacturing method does not make it possible to obtain a machining of the first satisfactory element, and therefore does not make it possible to obtain the precision necessary to assemble the conduit to the first element. Indeed, the deformations of the first element and the second element due to the assembly (especially when the assembly is done by welding) can cause inaccuracies in the machining of the first face of the first element, in particular in the positioning of the bores. . These inaccuracies in machining may subsequently require the use of corrective solutions that complicate the room, can weigh down, and lead to additional manufacturing costs.
    This problem of precision is found in machining especially for the manufacture of exhaust casing (or Turbine Rear Frame, TRF, according to the English terminology) for a turbomachine, and in particular for an aircraft turbine engine where the weight of the turbomachine is a very important parameter.
    FIGS. 1 to 3 illustrate an exhaust casing 1 of a turbomachine which has already been manufactured by the applicant. In the example illustrated in Figures 1 to 3, the exhaust casing 1 is obtained by assembling a mouth 2 (which corresponds to the first element) to an outer shell 3 of the exhaust casing 1 (which corresponds to the second element ), said mouth 2 being adapted to fix an outlet tube 4 of a transient exhaust valve of the turbomachine on said outer shell 3. The transient exhaust valve of the turbomachine (or Transient Bleed Valve, TBV, according to the Anglo-Saxon terminology) is a valve that allows to unload a high-pressure compressor from the turbomachine during startup and accelerations of the turbomachine. In the example illustrated in Figures 1 to 3, the exhaust casing 1 comprises four mouths 2 which are fixed on the outer shell 3. The outer shell 3 is a hollow and cylindrical part of revolution which defines the outer surface of the housing The outer shell 3 is connected by a plurality of arms 5 to an inner hub 6, said inner hub 6 also being a cylindrical hollow part of revolution which delimits the inner surface of the exhaust casing 1.
    As can be seen in FIGS. 1 to 3, the mouths 2 are generally in the form of a hollow pentahedron with a first face 21 and a second face (not visible in FIGS. 1 to 3) which generally form rectangles and which are inclined one to the other. relative to each other (in other words the first face 21 and the second face are not parallel), as well as three lateral faces 22, 23 and 24. Among the three lateral faces 22, 23 and 24, the two faces 22 and 23 are generally of triangular shape and are parallel to each other, and the face 24 is of generally rectangular shape and is perpendicular to the first face 21 and the two side faces 22 and 23 of triangular shape.
    The mouths 2 comprise a cavity 25 which passes through them integrally, opening into the center of the first face 21 and the center of the second face.
    The mouths 2 are fixed on the outer shell 3 by placing each of said mouths 2 opposite a bore made in said outer shell 3 and welding the contour of the second face of the mouths 2 to the edges of said bore. The second face of the mouths 2 is directed towards the inner hub 6 and is located between two arms 5. The cavity 25 therefore completely crosses the mouth 2 and the outer shell 3 so that a flow of air entering the mouth 2 through the first face 21 extends from said mouth 2 by its second face through the outer shell 3. The air flow entering the mouth 2 by the first face 21 is thus expelled between the outer shell 3 and the inner hub 6.
    The first face 21 of each of the mouths 2 comprises four attachment lugs 26 which are located at the four vertices of the first face 21 and which comprise a threaded hole 27 which is situated in their center. These attachment ears 26 and the holes 27 allow the attachment of the outlet tube 4 of the transient exhaust valve to the mouths 2.
    The exhaust casing 1 illustrated in FIGS. 1 to 3 is manufactured according to the following manufacturing method: - The 2 raw foundry mouths are welded to the outer shell 3. The 2 raw mouths already have their pentahedron shape and include the However, the attachment lugs 26 do not yet include the holes 27. Once the mouths 2 have been assembled to the outer shell 3, the first surface 21 of the said mouths 2 is machined while performing a surfacing. in order to correct the asperities of said first face 21 and to make said first surface 21 functional, and by making the holes 27 in the center of the attachment lugs 26. The surfacing of the first face 21 is made using machining reference as the reference the outer shell 3. In other words, the path that the machining tool must perform on the workpiece is spotted in space relative to the outer shell 3. The holes 27 are in turn made using a machining reference linked to the walls 28 of the cavity 25.
    However, such a manufacturing method may cause inaccuracy in the position of the holes 27. This inaccuracy may result in a shift between the position of the holes 27 during the design of the exhaust casing 1 and the positon of the holes 27 on the exhaust casing 1 once produced. This offset in the position of the bores leads to a misalignment with the additional bores made on the outlet tube 4 of the transient exhaust valve.
    It is known to solve this misalignment by using a ball joint or sealing plates.
    However, these solutions complicate the system, increase its size and make it heavier.
    Another known solution is to characterize the shape of the walls 28 of the cavity 25 of the mouths 2 by probing.
    However, the additional probe step thus imposed adds a step in the manufacturing process and is also very time consuming.
    GENERAL PRESENTATION OF THE INVENTION
    A general object of the invention is to propose a simple solution for ensuring precise machining of the first assembly of the part to be manufactured in order to ensure the absence of a gap between the first assembly and the conduit which must be fixed to said first assembly. together. The invention is particularly useful for the manufacture of an exhaust casing of a turbomachine, in particular for an aircraft turbomachine.
    More particularly, according to a first aspect, the invention proposes a method of manufacturing a turbomachine part in which a first raw casting element which comprises a first face and a second opposite face to each other is assembled by the second face on an orifice that has a second element of said part, characterized in that the method comprises the steps of: machining a through cavity in the first element which opens to the first face and the second face of the first element; machining the first face of the first element so as to form a zone adapted to ensure the attachment of a conduit on the first element, the machining of the cavity and the first face being achieved using a machining reference linked to the second element.
    Such a method makes it possible, on the one hand, to simplify the manufacture of the part by using a single reference system for machining the first element, and on the other hand to obtain precise machining of the first face of the first element because the deformations created by the assembly of the first element to the second element are compensated both by machining the cavity in the first element and by using a machining reference linked to the second element.
    According to an additional characteristic, the assembly of the first element to the second element is carried out by welding.
    According to another characteristic, the second element comprises a connecting device adapted to fix said second element to the rest of the turbomachine, the machining reference being linked to said connecting device.
    According to an additional characteristic, fixing lugs are made on the first face of the first element, said fixing lugs being adapted to ensure the attachment of the conduit to the first element.
    According to a particular characteristic, the machining of the first face of the first element is achieved by leaving a safety distance between the attachment lugs and an outer edge of the first element.
    According to another characteristic, the part is an exhaust casing, the second element is an outer shell of the exhaust casing, and the first element is a mouth which is adapted to be fixed to an outlet tube of a diverter valve. transient exhaust of the turbomachine so that a flow of air exiting the transient exhaust valve passes through the mouth through the cavity.
    According to a second aspect, the invention proposes a turbomachine part comprising a first raw casting element which comprises a first face and a second face opposite to each other and which is assembled by the second face on an orifice that presents a second element, characterized in that said part is made according to the manufacturing method according to any one of the preceding characteristics, and in that the first element comprises a machined through cavity, the first face of the first element forming a zone adapted for fixing a conduit on said first element.
    According to a particular characteristic, the first face of the first element comprises attachment lugs so as to fix the first element to the conduit by keyed sockets.
    According to an additional feature, the part is an exhaust casing, the second element is an outer shell of the exhaust casing, and the first element is a mouth adapted to be attached to an outlet tube of an exhaust valve. transient of the turbomachine so that a flow of air out of the transient exhaust valve through the mouth through the cavity.
    According to a third aspect, the invention proposes a turbomachine comprising a part according to any one of the preceding characteristics.
    DESCRIPTION OF THE FIGURES Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given as non-limiting examples and in which: FIG. 1 represents an exhaust casing for a turbomachine according to the state of the art; FIG. 2 represents a detailed view of the attachment of an outlet tube of a transient exhaust valve to the mouth of the exhaust casing illustrated in FIG. 1; FIG. 3 represents a detailed view of a mouth of the exhaust casing of FIGS. 1 and 2; FIG. 4 represents a flowchart of the steps of a first implementation of the manufacturing method; FIG. 5 represents a possible embodiment in which the part to be manufactured is an exhaust casing of a turbomachine, the first element is a mouth for fixing an outlet tube of a transient exhaust valve. , and the second element is an outer shell of said exhaust casing; FIG. 6 represents a view from above of FIG. 5; • Figure 7 shows the embodiment illustrated in Figures 5 and 6 wherein the mouth is attached to an outlet tube of a transient exhaust valve.
    DESCRIPTION OF ONE OR MORE EXAMPLES OF
    PRODUCTION
    FIG. 4 shows a first implementation of a method for manufacturing a part for a turbomachine, in particular an aircraft turbomachine.
    The method of manufacturing the part comprises a first step 100 of assembling a first member and a second member together. The assembly of the first element on the second element must in particular allow to fix a conduit to the workpiece by fixing said conduit to the first element. The assembly can for example be performed by welding the first element on the second element. The assembly is carried out with a first raw set of foundry. By foundry crude is meant that no step modifying the first element has been performed after the casting of said first element. The first and second elements can be of various shapes. The method is particularly adapted to allow to assemble a member forming a mouth or an inlet on which is fixed a conduit on a more massive element, so as to allow the fluid flowing in the conduit to penetrate into said more massive element by passing by said mouth or entrance. Thus, preferably, the first element is a mouth or an inlet adapted to be attached to a conduit, and the second element is a hollow element whose size is larger than that of the first element.
    So that the attachment of the conduit to the mouth is sealed, it is necessary that the machining of said mouth is accurate.
    The first element comprises a first face on which the duct is fixed to said first element, a second face which is fixed to the second element, and a flange which connects the first face to the second face. The first and second faces are opposite and parallel. The fact that the walls are parallel facilitates the machining of the first face of the first element when said first element is fixed on the second element.
    The first element is assembled to the second element by its second face on the edges of an orifice that has said second element. The assembly can be achieved by welding the second face of the first element to the edges of the orifice of the second element.
    The method includes a second step 200 of machining the first member to form a cavity within said first member whose walls are machined. The cavity thus produced completely traverses the first element. The machining performed during the second step 200 is performed using a machining reference which is linked to the second element. In other words, the path of the machining tool on the first element in order to machine it is spotted in space with respect to the second element. According to a first possible variant, the first raw casting element may comprise, prior to the second step 200, a preformed cavity at its center obtained during the foundry operation. In this first variant, the second step 200 consists of machining the walls of the preformed cavity, so as to form a cavity in the center of the first element whose walls are machined. According to a second possible variant, the first element is a solid part, that is to say not including a preformed cavity. Thus, in this second variant, the second machining step 200 consists of digging a cavity in the center of the first element, the cavity thus excavated thus comprising machined walls.
    The manufacturing method comprises a third step 300 of machining a first face of the first element to form fastening means, so as to form a suitable area to ensure the attachment of the conduit on the first element. The machining of the first face of the first element during the third step 300 is performed using the same machining reference as in the second step 200, that is to say the machining reference which is related to the second element .. According to a possible variant, the machining during the third step 300 is performed by performing a surfacing of the first face of the first element, by making several holes on said first face, and by tapping said holes made on said first face . According to another possible variant, the machining performed during the third step 300 comprises producing ears on the first face of the first element by digging said first face of the first element, and that the holes that are made on said first face when the third step 300 are located in the center of said ears. The ears are portions of the first face of the first element which project from the remainder of said first face and which have at least partly a rounded or generally rounded shape. The ears allow the attachment of the first element to a conduit by screwing a threaded element in the threaded holes located in the center of said ears, for example a key sleeve. The third step 300 may also consist only of making holes on the first face of the first element. Preferably, the machining of the first face of the first element during the third step 300 is achieved by leaving a safety distance between the ears and the outer rim of the first element, so even if the first element is deformed during assembly with the second element, the ears can be integrally formed in the first face of the first element without being trimmed. This variant is particularly preferred when the assembly of the first element to the second element is made by welding because the welding deforms the second element and the first element.
    The fact of using the second element as a machining reference for the second step 200 and the third step 300 makes it possible to simplify the manufacturing process by keeping a single reference frame for the machining of said first element. The fact of using the second element as a machining reference for the third step 300 also makes it possible to increase the precision of the machining of the fastening means with respect to the state of the art. Indeed, the machining reference is not related to a gross foundry surface. Moreover, the fact of machining the walls of the cavity during the second step 200 before forming fastening means during the third step 300 makes it possible to compensate for the deformations created during the assembly of the first and second elements, thus ensuring a good alignment of the cavity with the fixing means formed during the third step 300.
    According to a possible variant, the second element comprises a connecting device, for example a fixing flange, for fixing said second element to the rest of the turbomachine. Preferably, the machining reference system for the second step 200 and the third step 300 is linked to the connecting device of the second element. The fact that the machining reference frame for the second step 200 and the third step 300 is linked to the fixing means of the second element makes it possible to ensure a better accuracy in the positioning of the cavity formed during the second step 200 and the means fasteners formed during the third step 300 relative to the rest of the turbomachine, and thus a better accuracy in positioning relative to the conduit. Indeed, the positioning of the second element relative to the rest of the turbomachine is determined by the positioning connecting device connecting said second element to the rest of the turbomachine.
    FIGS. 5 to 7 illustrate an example in which the manufacturing process is used to fabricate an exhaust casing 7 of an aircraft turbomachine by assembling a mouth 8 for fixing an outlet tube 10 of a transient exhaust valve to an outer shell 9 of said exhaust casing 7. Figures 5 to 7 show the exhaust casing 7 once the finished manufacturing process.
    In the example illustrated in FIGS. 5 to 7, the part described previously corresponds to the exhaust casing 7, the first set corresponds to the mouth 8, the second set corresponds to the outer shell 9, and the duct which is attached to the said casing 8 first element corresponds to the outlet tube 10 of the transient exhaust valve. In the example illustrated in Figures 5 to 7, the outer shell 9 is identical to the outer shell 3 of the exhaust casing 1 of the state of the art.
    In the variant shown in FIGS. 5 to 7, the mouth 8 is a hollow hexahedron of rectangular section which comprises a first face 81, a second face parallel to the first face 81 (not visible in FIGS. 5 to 7), as well as four side faces 82 which are perpendicular to the first face 81 and the second face. The mouth 8 also comprises a cavity 83 at its center which opens to the first face 81 and to the second face of said mouth 8. According to a possible variant, the cavity 83 is of rectangular shape.
    In this example illustrated in Figures 5 to 7, the mouth 8 is fixed to the outer shell 9 by welding during the first step 100 of the manufacturing process. During step 100, when the mouth 8 is welded to the outer shell 9, the mouth 8 is still foundry. The mouth 8 rough foundry is for example a hexahedron whose six faces are flat. The raw mouth 8 comprises a preformed cavity resulting from the manufacture of said mouth 8 by casting, this preformed cavity opens to the first face 81 and the second face of said mouth 8. However, according to one possible variant, the mouth 8 foundry blank may be full (without preformed cavity resulting from the manufacture of said mouth 8 by foundry). For the assembly of the mouth 8 on the outer shell 9, the mouth 8 is placed opposite an orifice which is formed in the outer shell 9. The orifice formed in the outer shell 9 has a length and a width substantially identical to the length and width of the second face of the mouth 8. The periphery of the second face of the mouth 8 is then welded to the edges of the orifice formed in the outer shell 9. Once assembled to the outer shell 9, the mouth 8 projects from the outer shell 9 extending radially outwardly of said outer shell 9.
    Once the mouth 8 assembled to the outer shell 9, said mouth 8 is machined during the second step 200. To do this, the mouth 8 is machined so as to form the cavity 83 whose walls 84 are machined in the second step 200. In the case where the rough casting mouth 8 comprises a preformed cavity, the walls of the preformed cavity are machined by milling to remove material to enlarge said preformed cavity and obtain the cavity 83 visible in FIGS. 7. This step of removal of material during the second step 200 makes it possible to compensate for the deformations produced during the first step 100. The machining operation performed during the second step 200 uses a machining reference linked to the outer ferrule 9. In other words, the path made by the machining tool during the milling of the mouth 8 is spotted in space with respect to the outer shell 9. Preferably, the repository machining of this machining operation is linked to a fastening flange 91 of the outer shell 9 through which the exhaust casing 7 is attached downstream of the low-pressure turbine of the turbomachine. If the mouth 8 does not include a preformed cavity, the cavity 83 is entirely hollowed into said mouth 8.
    Following the second step 200 in which the walls 84 of the cavity 83 are machined, the first face 81 is machined so as to form a zone adapted to ensure the attachment of the mouth 8 with the outlet tube 10 of the valve. transient escape. This machining is performed using the machining reference linked to the outer shell 9 which was previously used during the second step 200. In other words, the path performed by the machining tool during the machining operation of the machine. third step 300 is located in the space relative to the outer shell 9. Preferably, the machining reference of this machining operation is linked to a fastening flange 91 of the outer shell 9 by which the casing Exhaust 7 is attached downstream of the low pressure turbine of the turbomachine. In the variant shown in FIGS. 5 to 7, the machining carried out during the third step 300 comprises a milling of the first face 81 so as to form ears 85 (six ears 85 in FIGS. 5 to 7) and the production of a piercing 86 in the center of said lugs 85. A surfacing of the first face 81 can also be performed during the third step 300 in order to correct the flatness defects of said first face 81, thus improving the sealing of the fastener with the exit 10.
    The ears 85 are portions of the first face 81 which comprise at least one circular or generally circular portion, and which project from the remainder of said first face 81. The ears 85 are flat surfaces forming a fastening flange on which a flange complementary attachment of the outlet tube 10 of the transient exhaust valve is configured to be fixed. The complementary fixing flange of the outlet tube 10 comprises ears which are located in front of the lugs 85 when the outlet tube 10 is fixed to the mouth 8. The lugs made in the outlet tube 10 comprise bores which are located in face of the holes 86 when the outlet tube 10 is attached to the mouth 8.
    The milling of the first face 81 of the third step 300 in the variant illustrated in FIGS. 5 to 7 is carried out in the following manner: A first pass is made by removing the material from the first face 81 so as to form the ears 85, thus forming a first planar surface 87 comprising the lugs 85 and a second flat surface 88 which is offset from the first surface 87 by being hollowed out in the thickness of the mouth 8. The first surface 87 comprises six portions protruding from the remainder of said first surface 87 which form the ears 85. - A second pass is made by again removing the material of the first face 81 following the contour of the ears 85 formed in the first pass, thereby forming a third flat surface 89 which is offset relative to the second surface 88 being hollowed in the thickness of the mouth 8. The second pass tends to su puncture the second surface 88 by digging to form the third surface 89 and gain mass. As can be seen in FIGS. 5 to 7, it is possible for a portion of the second surface 88 to remain at the end of the third machining area 300 because the second pass may not be made on the entire contour of the first surface 87.
    The holes 86 may be tapped in order to allow the outlet tube 10 to be fastened to the mouth 8 by means of keyed sleeves or by simple bolting. A key sleeve is a fastener comprising a threaded body which threads into a threaded hole and which comprises at least one key which can be driven into a groove in the thread of the key body so as to block the rotation of said keyway. threaded body within said threaded hole to prevent said body from unscrewing. In FIG. 7, only screws 11 are visible, these screws 11 each cooperating with a key sleeve located inside a bore 86 of the mouth 8.
    The mouths 8 illustrated in FIGS. 5 to 7 are less massive than the mouths 2 of the state of the art illustrated in FIGS. 1 to 3, thus making it possible to lighten the exhaust casing 7 manufactured with the mouths 8.
    Furthermore, in order to take into account the deformations of the outer shell 9 and the mouth 8 due to the welding operation, the machining of the first face 81 during the third step 300 is performed by providing safety distances for machining during the design of the mouth 8. For example, a minimum safety distance A is provided between the contour of the lugs 85 and the outer rim of the mouth 8 formed by the side faces 82. This safety distance A ensures that even if the mouth 8 is deformed following welding, the ears 85 may still be formed integrally in the first face 81 without being trimmed.
    The mouth 8 according to the variant illustrated in Figures 5 to 7 comprises six ears 85 and six holes 86, while the mouth 2 according to the prior art illustrated in Figures 1 to 3 comprises only four ears and four holes, because the fact that the first face 81 and the second face of the mouth 8 are parallel makes the surface of the first face 81 of the mouth 8 more important than the surface of the first face 21 of the mouth 2 of the state of the art (having the same surface for the second faces of the mouth 8 and mouth 2 of the state of the art). The fact of increasing the number of lugs 85 and holes 86, and thus of keyed sockets 11 or bolts, makes it possible to maintain the same level of tightness for a larger surface area.
    Furthermore, the fact that the machining reference system for the second step 200 and the third step 300 is linked to the fastening flange 91 makes it possible to ensure a more precise positioning of the cavity 83 machined during the second step 200 and the fastening means created in the third step 300 with respect to the outlet tube 10 of the transient exhaust valve.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. A method of manufacturing a turbomachine part (7) in which a first raw casting element (8) which comprises a first face (81) and a second face opposite to each other is assembled by the second face on an orifice that has a second element (9) of said part (7), characterized in that the method comprises the steps of: • (200) machining a through cavity (83) in the first element (8) which opens out at the first face (81) and the second face of the first element (8); • (300) machining the first face (81) of the first element (8) so as to form a zone adapted to ensure the attachment of a duct (10) to the first element (8), the machining of the cavity ( 83) and the first face (81) being made using a machining reference linked to the second element (9).
    [2" id="c-fr-0002]
    2. Manufacturing process according to claim 1, characterized in that the assembly of the first element (8) to the second element (9) is performed by welding.
    [3" id="c-fr-0003]
    3. Manufacturing process according to one of the preceding claims, characterized in that the second element (9) comprises a connecting device (91) adapted to fix said second element (9) to the rest of the turbomachine, the reference system. machining being connected to said connecting device (91).
    [4" id="c-fr-0004]
    4. Manufacturing method according to one of the preceding claims, characterized in that fixing ears (85) are formed on the first face (81) of the first element (8), said attachment lugs (85) being adapted to secure the duct (10) to the first element (8).
    [5" id="c-fr-0005]
    5. Manufacturing process according to claim 4, characterized in that the machining of the first face (81) of the first element (8) is achieved by leaving a safety distance (A) between the attachment lugs (85) and an outer edge of the first element (8).
    [6" id="c-fr-0006]
    6. Manufacturing process according to one of the preceding claims, characterized in that the part is an exhaust casing (7), the second element is an outer shell (9) of the exhaust casing (7), and that the first element is a mouth (8) which is adapted to be fixed to an outlet tube (10) of a transient exhaust valve of the turbomachine so that an air flow exiting the valve of transient exhaust passes through the mouth (8) through the cavity (83).
    [7" id="c-fr-0007]
    7. Part (7) for a turbomachine comprising a first raw casting element (8) which comprises a first face (81) and a second opposite face to each other and which is assembled by the second face on an orifice that has a second element (9), characterized in that said part is produced according to the manufacturing method according to any one of claims 1 to 6, and in that the first element (8) comprises a machined through cavity (83) the first face (81) of the first element (8) forming a zone adapted for fixing a conduit (10) on said first element (8).
    [8" id="c-fr-0008]
    8. Part (7) according to claim 7, characterized in that the first face (81) of the first element (8) comprises fixing lugs (85), so as to fix the first element (8) to the duct ( 10) by keyed sockets (11).
    [9" id="c-fr-0009]
    9. Part according to any one of claims 7 and 8, characterized in that said part is an exhaust casing (7), the second element is an outer shell (9) of the exhaust casing (7), and that the first member is a mouth (8) adapted to be attached to an outlet tube (10) of a transient exhaust valve of the turbomachine so that an airflow exiting the valve of the transitory exhaust passes through the mouth (8) through the cavity (83). 10.Turbomachine comprising a part (7) according to any one of claims 7 to 9.
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    EP3444439B1|2021-02-17|Turbine for turbine engine comprising blades with a root having an exapnding form in axial direction
    EP3683450A1|2020-07-22|Turbine engine rotor assembly
    EP3464954B1|2020-09-09|Equipment for disassembling a planet carrier into two parts and associated planet carrier
    FR3041381A1|2017-03-24|EXHAUST CASE ASSEMBLY AND ANCHORED ELEMENT MOUNTED BY BAIONNETTE
    EP3568638B1|2021-03-31|Turbine engine combustion chamber
    FR3068383B1|2019-08-09|CONNECTION OF RADIAL ARMS TO A CIRCULAR VIROLE BY ILLUMINATION OF REPORTED PARTS
    EP3715638A1|2020-09-30|Hybrid rotor with external shell offset against the composite annular wall
    同族专利:
    公开号 | 公开日
    FR3046951B1|2018-01-12|
    US20170211420A1|2017-07-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2005012696A1|2003-07-29|2005-02-10|Pratt & Whitney Canada Corp.|Turbofan case and method of making|
    US20140165533A1|2012-12-18|2014-06-19|Pratt & Whitney Canada Corp.|Gas turbine engine mounting ring|
    WO2014143329A2|2012-12-29|2014-09-18|United Technologies Corporation|Frame junction cooling holes|
    FR3018114A1|2014-03-03|2015-09-04|Turbomeca|DEVICE FOR POSITIONING AN INSPECTION TOOL|WO2021229163A1|2020-05-15|2021-11-18|Safran Aircraft Engines|Turbomachine exhaust case|
    FR3051840B1|2016-05-31|2020-01-10|Safran Aircraft Engines|INTERMEDIATE CRANKCASE OF TURBOMACHINE, EQUIPPED WITH A SEALING PART WITH ARM / CRANK INTERFACE|
    US11162425B2|2019-06-11|2021-11-02|Rolls-Royce Corporation|Assembly fixture|
    法律状态:
    2017-01-03| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-28| PLSC| Publication of the preliminary search report|Effective date: 20170728 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650492|2016-01-21|
    FR1650492A|FR3046951B1|2016-01-21|2016-01-21|PROCESS FOR MANUFACTURING A PIECE OF A TURBOMACHINE AND PIECE PRODUCED THEREBY|FR1650492A| FR3046951B1|2016-01-21|2016-01-21|PROCESS FOR MANUFACTURING A PIECE OF A TURBOMACHINE AND PIECE PRODUCED THEREBY|
    US15/409,852| US20170211420A1|2016-01-21|2017-01-19|Method for manufacturing a turbine engine part and the thereby produced part|
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