• 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 of manufacturing a support panel of at least one cartridge of abradable material for a turbomachine casing, said panel comprising at least one block of honeycomb material covered with a rigid skin, characterized in that it comprises: - a machining step (ET5 ') of an outer face of a block of a material, in particular honeycomb, according to a three-dimensional profile configured to match that of an inner face of the housing, then - a bonding step (ET6 ') of the block of material machined in the rigid skin.
    公开号:FR3051828A1
    申请号:FR1654605
    申请日:2016-05-24
    公开日:2017-12-01
    发明作者:Marc-Emmanuel Jean Francois Techer；Hubert Jean Marie Fabre；Pauline Nathalie Six
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    The invention relates in particular to a method of manufacturing an abradable material support panel for a turbomachine casing.
    The aeronautical turbomachines are mainly constituted by at least one compressor, in which the air sucked into the air inlet of the turbomachine is compressed towards a combustion chamber in which the injected fuel is burned, then transmitted to at least one turbine wherein the flue gases are expanded to drive the integral compressor in rotation of the turbine, and finally discharged by an ejection device. The compressors and the aeronautical turbines consist of fins, or blades, which are rotated inside a casing which seals the air stream with the outside of the engine.
    For example, the casing consists of a succession of rings with which the vanes provide a running clearance. This clearance must be sufficient so that friction does not slow down the rotation of the moving parts but it must be controlled to prevent a large amount of gas is diverted from the active surfaces of the blades. In order to ensure as high a return as possible, it is important to master this game.
    Indeed, it is known that the clearance between the ends of the blades and the casing forming the inner wall of the air flow stream degrades the efficiency of the engine of the turbomachine. In the case of a compressor crankcase in particular, this game can significantly modify and degrade the operation of the compressor until the appearance of a phenomenon of "pumping", which results from the stall of the airflow from the surface blades. The control of the air circulation at the end of the blades is thus a major challenge to obtain both a good aerodynamic efficiency of the compressor or the turbine and, in the particular case of a compressor, to have a sufficient margin against the pumping phenomenon.
    In a known manner, in order to control this clearance, the casing carries an annular coating of abradable material. This coating extends around and at short radial distance from the blades, which can, in operation, rub against the abradable material and wear it by friction. This makes it possible to optimize the radial clearances between the blades and the casing which surrounds them and thus to limit the gas leaks at the vertices or radially external ends of the vanes.
    The casing can be made in the form of a one-piece ring, or a succession of ring sectors, and the same is true of the abradable material which can be produced in the form of an annular cartridge or of a succession of angular sectors of cartridges.
    The abradable material is not fixed directly to the housing. Indeed, the housing receives a support panel consisting of a block of honeycomb material covered by a rigid skin, which provides support for the cartridge or cartridges of abradable material.
    STATE OF THE PRIOR ART
    According to the state of the prior art, the abradable coating housing is made in three successive main steps of manufacturing the support panel, machining the support panel, and gluing the support panel on the housing.
    During a first step of manufacturing the support panel, covering a block of honeycomb material with a skin preform impregnated composite material, for example a preform made of carbon fibers impregnated with an epoxy resin. The preform has a wall and edges defining edges, and for this purpose, during the covering of the block of honeycomb material by the preform, an intumescent material is interposed between the edges of the block and the songs of the preform . Then, the assembly, shaped substantially in the form of a half-sandwich, is subjected to simple cooking during a second step so as to form a raw support panel.
    The internal surface of the housing does not necessarily correspond to its theoretical profile. In particular, in the case of a housing made of composite material, it was found that the inner face of the housing after manufacture did not necessarily have a perfectly circular section but could have an oval section. In addition, the inner face of the housing may have possible surface defects.
    It is therefore necessary to perform a machining of the outer face of the support panel so that it marries the inner face of the housing to minimize the deformations that the support panel could suffer, because these deformations would have the consequence of change the position required for the cartridge of abradable material that the support panel is to receive.
    To do this, during a third step, the inner face of the housing is measured so as to deduce a three-dimensional profile that the outer face of the support panel must match. Then, during a fourth step, the support panel is placed in a suitable tool for constraining it to a position similar to that which must occupy once mounted in the housing.
    During a fifth step, then the outer face of the support panel is machined to a three-dimensional profile corresponding to that of the inner face of the casing. These steps constitute the manufacturing steps of the support panel, and constitute as such a first phase of manufacture of the abradable coating housing. Then, during a second phase of manufacture of the abradable coating housing, the support panel is glued to the housing and the abradable material on the support panel.
    This design has the disadvantage of requiring a measurement operation of the inner face of the housing with very high tolerances because the slightest defect in shape of the inner face of the housing panel has consequences on the positioning of the support panel after fixing. .
    Moreover, the machining operation is moreover very restrictive by the tools that are implemented for its implementation. Indeed, once baked, the support panel is considerably stiffened, this rigidity being provided mainly by the skin of composite material. Straining the support panel in the tool to constrain it to the position it must occupy once mounted in the housing involves a tool capable of imparting the appropriate deformations while ensuring a high support of the support panel. This tooling is therefore complex and expensive.
    Moreover, in order to obtain satisfactory adhesion of the composite material skin to the block of honeycomb material, it is necessary to carry out the cooking of the half-sandwich assembly in an autoclave enclosure. Consequently, the mass production of such cartridge holders of abradable material involves a rigorous management of the autoclave speaker usage times, which complicates the production of these panels.
    Finally, the insertion of an intumescent material between the edges of the block of honeycomb material and the edges of the skin of composite material presents risks of deformation of the support panel. Indeed, the expansion of the intumescent has a direct impact on the quality of the songs. The support panels produced according to the current state of the art include craters, porosities, and delaminations at the edges, which almost always requires editing the edges to obtain the final support panel.
    To overcome these disadvantages it is desirable to allow the manufacture of the support panel using conventional cooking means and allow the machining of the block of honeycomb material with reduced tooling and lower tolerances.
    SUMMARY OF THE INVENTION The object of the invention is therefore to simplify the operations for preparing the raw support panel and its machining in order to adapt it to the internal surface of the housing.
    For this purpose, the invention proposes a method of manufacturing at least one support panel of a cartridge of abradable material for a turbomachine casing, said panel comprising at least one block of material, especially honeycomb material, and a rigid skin covering said block with the exception of a free outer face configured to be fixed to an internal face of the casing, characterized in that it comprises: a step of machining the outer face of the block of material in a three-dimensional profile configured to match that of the inner face of the housing, and - a step of fixing the machined block to the rigid skin.
    This new organization of the steps of the method of manufacturing the support member makes it possible, because of the step of machining the material prior to insertion into the rigid skin, to simplify this machining step because it can be achieved without the obligation to have specific tools necessary to constrain the support element according to the shape it will occupy in the housing. Moreover, the fixing of the block of material in the rigid skin makes it possible to avoid the use of an intumescent material and consequently eliminates the defects that it was likely, in the prior state of the art, to cause level of these songs.
    According to other characteristics of the manufacturing method of the support element: during the machining step, the external face of the block is machined to a predetermined thickness and, prior to the fixing step, a choice is made a rigid skin having a wall and edges defining edges of determined height less than the determined thickness of the block, - during the fixing step, the skin wall is bonded composite material on an inner face of the block and the edges on the edges of said block, the method comprises a prior step of manufacturing the skin by baking an impregnated composite material, the method comprises a prior step of measuring the dimensions of an internal face of the casing to determine the three-dimensional profile of said inner face. The invention also proposes a support panel for at least one cartridge of abradable material for a turbomachine, said panel comprising at least one block of a material, in particular a honeycomb material, which has an external face configured to be glued. an inner face of a turbomachine casing and which is covered with a rigid skin, said rigid skin having a wall covering an inner face of the block and flanges defining edges facing side edges of said block, characterized in that the outer face of the block is machined and in that the rigid skin is fixed to the block by means of a glue film, said glue film being inserted between the wall of the skin and the inner face of the block and between the chants of the skin and the lateral edges of said block.
    According to other features of the panel: - a free end of the edges is arranged set back from the outer face of the block, - the skin is a baked impregnated composite material. The invention also proposes a method of manufacturing a casing with an abradable turbomachine coating, comprising a turbomachine casing coated with a support panel of the type previously described, receiving a cartridge of abradable material, characterized in that it comprises successively a first phase during which the steps of the method of manufacturing a support panel as described above are carried out in order to obtain at least one support panel, a second phase during which said support panel is glued on the inner face of the housing, and a phase during which a cartridge of abradable material is glued to said support panel.
    According to another characteristic of the manufacturing process of the abradable-coating casing, the second phase of said process occurs simultaneously with the bonding step of the manufacturing process of the support panel. Finally, the invention relates to a turbomachine comprising at least one abradable coating casing obtained by the method described above. The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which: Figure 1 is a schematic sectional view of a casing with an abradable turbomachine coating according to a prior art; - Figures 2A and 2B are schematic views showing part of the steps of a method of manufacturing a support panel according to a prior art; FIG. 3 is a schematic view showing a final phase of a process for manufacturing the abradable coating of FIG. 1; FIG. 4 is a flowchart showing the phases of a manufacturing process of the abradable coating casing of FIG. 1; - Figure 5 is a schematic sectional view of an abradable coating housing according to the invention; FIGS. 6A and 6B are schematic views showing part of the steps of a method of manufacturing a support panel according to the invention; FIG. 7 is a schematic view showing a final phase of a manufacturing process of the abradable coating casing of FIG. 5. FIG. 8 is a flow chart showing the phases of a manufacturing process of the abradable coating casing of FIG. Figure 5.
    In the following description, like reference numerals designate like parts or having similar functions.
    In the remainder of the present description, the "internal" and "external" orientations are defined by reference to an axis of rotation of the rotors of a turbomachine, the "external" orientations being turned away from said axis, and the orientations "Internal" being turned towards said axis.
    FIGS. 1 and 5 show an abradable housing 10 for a turbomachine.
    In known manner, such an abradable coating housing 10 comprises a housing 12 bare which is coated with a support panel 14 which is itself coated with a cartridge 16 of abradable material.
    The support panel 14 comprises at least one block 18 of honeycomb material, generally known by the name "Nida", and a rigid skin 20 which covers the block 18 and which is intended to receive the cartridge 16 of material abradable.
    Thus, the support panel 14 is in the form of a half-sandwich which is fixed to an inner face 13 of the casing 12 via an adhesive film 22.
    The cartridge of abradable material 16 is fixed to the support member 14 by gluing, and in particular by baking the abradable material. The firing of the abradable material ensures its cohesion with the support panel 14.
    Figure 1 illustrates more particularly an abradable coating housing 10 made in accordance with a prior art. This abradable coating housing 10 comprises in particular a support panel 14 which is produced according to a method which has been represented in FIGS. 2A and 2B in correspondence of the steps of FIG. 4.
    According to this method, during a first step ET1 which has been shown in FIG. 2A, a block 18 of honeycomb material is inserted in a skin preform 26 made of impregnated composite material, for example a preform 26. made of carbon fiber woven and impregnated with an epoxy resin. The preform 26 has a wall 28 and flanges defining edges 30. Upon insertion of the block 18 of honeycomb material into the preform, an intumescent material 32 is interposed between edges 34 of the block 18 of the material. honeycomb and the edges 30 of the preform 26. The assembly, shaped substantially in the form of a half-sandwich, is subjected to a simple firing during a second step ET2 of so as to form a panel of raw support. At the end of this step ET2, the skin preform 26 made of composite material has become a rigid skin 20 as shown in FIG. 2B. The block 18 of honeycomb material, the intumescent material 32, and the skin 20 are adhered to each other following the baking of the composite material.
    Moreover, the inner surface 13 of the casing 12 previously shown in FIG. 1 does not necessarily correspond to its theoretical profile. In particular, in the case of a housing 12 of revolution made of composite material, it was found that the inner face 13 of the housing 12 after manufacture may not have a perfectly circular section but rather an ovalized section unsuitable for receiving a wheel of compressor or turbomachine turbine (not shown). In addition, the inner face 13 of the housing 12 may have any surface defects.
    Insofar as the skin 20 is rigid and where its general shape must not be changed because it must have a minimum thickness to support the cartridge of abradable material 16, it is therefore necessary to perform a machining of a face external 36 of the support panel 14 so that it matches the inner face 13 of the housing 12 to minimize the deformations that the support panel 14 could suffer from its theoretical profile. Indeed, such deformations would have the effect of changing the position required for the support panel 14, and therefore for the cartridge of abradable material 16 that the support panel 14 must receive.
    To do this, as illustrated in FIG. 4, during a third step ET3 (not shown), the inner face 13 of the casing 12 is measured so as to deduce therefrom a three-dimensional profile that the external face 36 of the panel support 14 must marry. Then, during a fourth step ET4, the support panel 14 is placed in an appropriate tool (not visible) which makes it possible to constrain the panel 14 in a position similar to that which it must occupy once mounted in the housing. 12.
    For example, this constraint may consist, when the panel 14 has an annular shape, in a radial stress exerted along the entire periphery of the outer face 36 of the panel 14 or, when the panel 14 has an angular sector shape as shown in FIGS. 2A and 2B, in a stress exerted radially on the periphery of the outer face 36 and tangentially on the edges 30 of the panel 14, since the panel 14 is intended to be arranged between two panels 14 of the same type which consequently exert on him tangential efforts at the level of these two songs 30.
    It will be understood that other constraints may be exerted to constrain the panel 14 to its position mounted in the housing 12, without limitation of the invention.
    Then, during a fifth ETS step which has been shown in FIG. 2B, the outer face 36 of the support panel 14 is then machined according to a three-dimensional profile corresponding to that of the inner face 13 of the casing 12, for example to using a strawberry two sizes 37.
    The first to fifth steps ET1 to ETS of the method of manufacturing the support panel 14, comprising in particular the steps ET1 and ETS which have been represented in FIGS. 2A and 2B, constitute a first phase PI of the manufacturing process of the abradable coating. . Then, during a second phase P2 shown in FIG. 4 and illustrated in FIG. 3, the support panel 14 is glued to the inner face 13 of the casing and finally during a phase P3, the bonding is carried out of the cartridge 16 of abradable material on the support panel 14
    These methods have several disadvantages.
    In the first place, during step ET3, they impose an operation of measuring the internal face 13 of the housing 12 with very high tolerances, since, as the support panel 14 is made rigid at the end of the ET2 cooking step of the skin 20, the slightest defect in shape of the inner face 13 of the housing panel 12 causes a positioning defect of the support panel 14 after its attachment to the housing 12.
    In particular, as illustrated in Figure 1, the outer ends 38 of the edges 30 being directly in contact with the inner face 13 of the housing 12, any defect of the inner face 13 causes a defect of positioning of the wall 28 of the panel. support 14, and therefore the cartridge 16 of abradable material.
    Secondly, the machining operation of the ETS step is moreover very restrictive to implement by the nature of the tools it involves. As we have seen, once baked, the support panel 14 is considerably stiffened by the skin 20 of composite material. The stressing of the support panel 14 in the tooling in order to constrain it to the position it must occupy once mounted in the casing involves a tooling capable of conferring the appropriate deformations of the panel 14 while ensuring a maintenance for it does not escape from said high tooling of the support panel.
    Third, the second cooking step is also problematic. Indeed, as the connection of the block 18 to the skin 20 is achieved by the baking of the support panel 14 in its entirety, it is necessary to carry out the cooking of this half-sandwich assembly in an autoclave chamber. Therefore, the mass production of such supports 14 of cartridges of abradable material involves a rigorous management of the use and occupation times autoclave enclosures which complicates the management of workflows.
    Finally, the insertion of the intumescent material 32 between the edges of the block of honeycomb material and the songs of the skin of composite material increases the risk of deformation of the support panel 14. Indeed, the expansion of the intumescent can produce craters, porosities and delaminations at the edges 30, which almost always requires retouching of the edges 30 to obtain the final support panel 14.
    This disadvantage is remedied by proposing a method of manufacturing the support panel 14 and a method of manufacturing the abradable coating housing 10 which advantageously allow the manufacture of the support panel 14 by using conventional cooking means and allowing the machining of the Block 18 of honeycomb material with reduced tooling and lower tolerances.
    According to the invention, as illustrated in FIGS. 6A, 6B and 7, the method comprises successively at least one step ET5 'of machining the outer face 36 of the block 18 of honeycomb material according to a profile of three dimensions configured to match that of an internal face of the housing, then a step ET6 'of bonding the block 18 machined to the rigid skin 20.
    The implementation of this method may involve the provision of a rigid skin that may already be formed, and for example be part of a skin stock 20 available to the operator in charge of manufacturing, or alternatively , a skin that is formed at the time of implementation of the method. We will now describe a preferred embodiment of the method, it being understood that this embodiment is, in its organization, not limiting of the invention, as long as the method comprises at least the machining step of the invention. the outer face 36 of the block 18 and the step of bonding the block 18 machined to the rigid skin 20.
    As illustrated in FIG. 8, the method of manufacturing the support panel 14 according to the invention preferably comprises a first step ET 1 ', during which the skin 20 made of composite material is produced by firing a composite material impregnated, for example a carbon fiber fabric impregnated with epoxy resin. A skin 20, preferably rigid, having a wall 28 and edges 30, as shown in FIG. 6A, is then obtained. The skin 20 is configured to leave free on the block 18 an outer face 36 configured to be fixed to an inner face 13 of the housing 12 as shown in Figure 5.
    Then, or in parallel, because these operations can be carried out simultaneously, the method comprises a step ET2 'of cutting the block 18 of honeycomb material in dimensions adapted to those of the wall 28 of the skin 20 , the purpose of this operation being obviously to ensure that the block 18 can be covered by the skin 20.
    Then or in parallel, because these operations can be carried out simultaneously, the method preferably comprises a third step ET3 'measuring the inner face 13 of the housing 12 to determine the three-dimensional profile of said inner face 13. This third step ET3' The method is not limiting of the invention but it allows to characterize very accurately the profile of the inner face 13 to accurately measure all defects.
    Then, during a fourth step ET4 ', the block 18 is placed on a tool (not visible) able to give it a position corresponding to the final position it is intended to occupy in the panel 14 mounted in the housing 12.
    Advantageously, since the block 18 is not stiffened by the rigid skin 20, the tool used does not require to prestress the block 18 to obtain the final position it is intended to occupy in the panel 14 mounted in the housing 12 This configuration makes it possible to use a simpler tooling.
    Then, at least one machining step ET5 'of the external face 36 of the block 18 made of honeycomb material is carried out according to a three-dimensional profile configured to match that of the inner face 13 of the casing 12, as shown in FIG. Figure 6B.
    Compared with the method as described above with reference to the state of the art, this method advantageously makes it possible to machine a block 18 of honeycomb material which is more flexible than previously, since it is not stiffened by the rigid skin 20. As a result, the machining may advantageously be carried out as previously with a two-size milling cutter 37, but it is not necessary to have tools that make it possible to constrain and maintain the block precisely. 18 of honeycomb material, because it is not stiffened by the skin 20 and is therefore more flexible.
    Then, as illustrated in FIG. 7, during a step ET6 'of bonding, the block of honeycomb material 18 previously machined to the skin 20 is fixed by means of a film of glue 40 .
    Preferably, an external face 27 of the wall 28 of the composite material skin 20 is adhered via the adhesive film 40 to an internal face 42 of the honeycomb material block 18 and the edges 30 to the edges 34 of said block 18 of honeycomb material.
    Advantageously, in the preferred embodiment of the manufacturing method of the support element 14, the block 18 of honeycomb material is machined during the step ET5 'according to a thickness E1, represented in FIG. 6B .
    During the first step ET 1 ', a rigid skin 20 is made or selected having edges defining edges 30 of determined height H, as shown in FIG. 6A. The height H of the edges 30 is intended to be less than the height E1 of the block 18.
    This configuration is particularly advantageous. Indeed, the support panel 14 obtained has edges 30 whose free end is therefore capable of being arranged in withdrawal from the plane of the outer face 36 of the block 18.
    This configuration ensures that, when the block 18 of honeycomb material is assembled with the rigid skin 20, the outer ends 38 of the edges 30 do not touch the inner face 13 of the housing 12, as represented by the reference detail and the associated arrow shown in Figure 7. Thus, any residual fault of the inner face 13 of the housing 12 is not transmitted by the rigid skin 20 to its wall 28, and does not affect the positioning from its wall 28.
    In addition, this configuration allows the use of a standard composite skin 20 whose edges 30 require no machining. A simple choice of the composite skin in a stock of can composite of different heights makes it possible to find the one whose height H can be adapted to the block 18 without the height of its edges 30 exceeding the height E1 of the block 18.
    The first to fifth steps ET1 'to ET6' of the method of manufacturing the support panel 14 according to the invention, comprising in particular the steps ET1 'and ET5' which have been represented in FIGS. 6A and 6B, constitute a first phase PI ' Finally, during a second phase P2 'of the manufacturing process of the abradable coating casing 10 which has been shown in FIG. 8 and illustrated in FIG. 7, the adhesive is bonded to the abradable coating case 10. support panel 14 on the internal face 13 of the casing and in a third phase P3 'the cartridge 16 of abradable material is bonded to the support panel 14.
    Advantageously, as illustrated by the variant of the dashed line method of FIG. 8, the sixth step ET6 'of manufacturing the support panel 14 may coincide with the second phase P2' of the process for manufacturing the abradable coating casing 10, in the extent that the bonding of the block 18 in the skin 20 can be performed in a single operation at the same time as that of the outer face 36 of the block 18 on the inner face 13 of the housing 12. The grouping of the operations of coliage thus allows to avoid adding an additional step to the process, which retains the same number of steps as the processes according to the state of the art, while avoiding its disadvantages and without requiring independent cooking for fixing the skin 20 to block 18 and for fixing the block 20 to the casing 12. The invention is particularly applicable to a support panel 14 for equipping an abradable panel 10 of a turbomachine, whether it is an abradable panel 10 for a compressor or turbine stream of said turbomachine.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. A method of manufacturing a support panel (14) of at least one cartridge (16) of abradable material for a turbomachine casing, said panel (14) comprising at least one block (18) of material and a skin rigid member (20) covering said block with the exception of a free outer face (36) configured to be fixed to an internal face (13) of the casing (12), characterized in that it comprises: a step of machining (ET5 ') of the outer face (36) of the block (18) of material in a three-dimensional profile configured to match that of the inner face (13) of the housing (12), then - a gluing step (ET6 ') of the block (18) machined with the rigid skin (20).
    [2" id="c-fr-0002]
    2. Method according to the preceding claim, characterized in that during the machining step (ET5 '), the outer face of the block (18) is machined to a thickness (E2) determined, and in that prior to the bonding step (ET6 '), a rigid skin (20) having a wall (28) and edges defining edges (30) of determined height (H) lower than said determined thickness (E2) are chosen of the block (18).
    [3" id="c-fr-0003]
    3. Method according to the preceding claim, characterized in that, during the bonding step (ET6 '), the wall (28) of the skin (20) is bonded to an inner face (42) of the block (18). ) and the edges (30) on the edges (34) of said block (18).
    [4" id="c-fr-0004]
    4. Method according to one of the preceding claims, characterized in that it comprises a prior step (ET1 ') of manufacture of the skin (20) by baking an impregnated composite material.
    [5" id="c-fr-0005]
    5. Method according to one of the preceding claims, characterized in that it comprises a step (ET3 ') prior to measurement of dimensions of an inner face (13) of the housing (12) to determine the profile in three dimensions of said inner face.
    [6" id="c-fr-0006]
    6. Panel (14) for supporting at least one cartridge (16) of abradable material (16) for a turbomachine, said panel (14) comprising at least one block (18) of material which has an outer face (36) configured to be bonded to an inner face (13) of a turbomachine casing and which is covered with a rigid skin (20), said rigid skin having a wall (28) covering an inner face (42) of the block (18). ) and flanges defining edges (30) facing lateral edges (34) of said block (18), characterized in that the outer face (36) of the block (18) is machined and in that the rigid skin (20) ) is fixed to the block (18) by means of an adhesive film (24), said glue film (24) being interposed between the wall (28) of the skin (20) and the inner face (42) of the block (18) and between the edges of the skin (30) and the lateral edges (34) of said block (18).
    [7" id="c-fr-0007]
    7. support panel (14) according to the preceding claim, characterized in that a free end (38) of the edges (30) is arranged recessed from the outer face (36) of the block (18).
    [8" id="c-fr-0008]
    8. Panel (14) support according to one of claims 6 or 7, characterized in that the skin (20) is made of baked impregnated composite material.
    [9" id="c-fr-0009]
    9. A method of manufacturing a casing with an abradable coating (10) of a turbomachine, comprising a casing (12) of a turbomachine coated with a support panel (14) according to claims 6 to 8 receiving a cartridge (16) of material abradable, characterized in that it comprises successively a first phase (PI ') during which it implements the steps (ET5', ET6 ') of the method of manufacturing a support panel according to one of the claims 1 to 5 to obtain at least one support panel (14), a second phase (P2 ') during which said support panel (14) is glued to the inner face (13) of the housing (12), and a third phase (P3 ') during which a cartridge (16) of abradable material is glued to said support panel (14).
    [10" id="c-fr-0010]
    10. A method of manufacturing an abradable coating housing (14) according to the preceding claim, characterized in that the second phase (P2 ') of said process occurs simultaneously with the bonding step (ET6') of the manufacturing process of the support panel (14).
    [11" id="c-fr-0011]
    11. Turbomachine comprising at least one support panel (14) according to one of claims 6 to 8 obtained by the method according to one of claims 1 to 5.
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    WO2021048473A1|2021-03-18|Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine
    FR3106363A1|2021-07-23|BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE TEST BENCH
    FR2998672A1|2014-05-30|ROTOR OF TURBOMACHINE OR TEST ENGINE
    同族专利:
    公开号 | 公开日
    US20200308975A1|2020-10-01|
    WO2017203135A1|2017-11-30|
    EP3464829B1|2020-07-15|
    EP3464829A1|2019-04-10|
    CN109312628B|2021-08-24|
    CN109312628A|2019-02-05|
    FR3051828B1|2018-05-11|
    US11002145B2|2021-05-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2922950A1|2007-10-31|2009-05-01|Snecma Sa|Abradable cartridge for assuring sealing between sectors of downstream guide vanes and rotor of e.g. compressor, of turbomachine, has support with window, where cartridge is extended on single part in three hundred and sixty degrees|
    US20140150262A1|2011-07-13|2014-06-05|Snecma|Method for manufacturing a turbine-engine fan casing having an acoustic coating|FR3106611A1|2020-01-29|2021-07-30|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE CASE AND ITS MANUFACTURING PROCESS|
    FR3106610A1|2020-01-29|2021-07-30|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE CASE AND ITS MANUFACTURING PROCESS|
    FR3106612A1|2020-01-29|2021-07-30|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE CASE AND ITS MANUFACTURING PROCESS|US4600619A|1984-12-31|1986-07-15|The Boeing Company|Continuously wound filament structure for use in noise attenuation element|
    US20090151162A1|2007-12-12|2009-06-18|Ming Xie|Methods for making composite containment casings having an integral fragment catcher|
    GB2459844B|2008-05-06|2011-01-19|Rolls Royce Plc|Fan section|
    GB0917123D0|2009-09-30|2009-11-11|Rolls Royce Plc|A method of securing a liner panel to a casing|
    FR2979385A1|2011-08-22|2013-03-01|Snecma|ACOUSTIC INSULATION PANEL FOR TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A PANEL|
    US20140086734A1|2012-09-21|2014-03-27|General Electric Company|Method and system for fabricating composite containment casings|
    FR2997726B1|2012-11-05|2018-03-02|Safran Aircraft Engines|TURBOMACHINE HOUSING|
    EP2902592B1|2014-01-31|2017-04-12|Rolls-Royce plc|Gas turbine engine|
    GB2524320B|2014-03-21|2016-05-04|Rolls Royce Plc|Gas turbine engine|
    US9932839B2|2014-06-04|2018-04-03|United Technologies Corporation|Cutting blade tips|
    GB201416764D0|2014-09-23|2014-11-05|Rolls Royce Plc|Gas turbine engine|
    法律状态:
    2017-04-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-01| PLSC| Search report ready|Effective date: 20171201 |
    2018-04-23| 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 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1654605|2016-05-24|
    FR1654605A|FR3051828B1|2016-05-24|2016-05-24|PROCESS FOR MANUFACTURING A TURBOMACHINE ABRADABLE COATING CASE|FR1654605A| FR3051828B1|2016-05-24|2016-05-24|PROCESS FOR MANUFACTURING A TURBOMACHINE ABRADABLE COATING CASE|
    PCT/FR2017/051203| WO2017203135A1|2016-05-24|2017-05-18|Method for manufacturing a turbine engine casing with abradable coating|
    CN201780035299.6A| CN109312628B|2016-05-24|2017-05-18|Method for manufacturing a turbine engine casing with an abradable coating|
    EP17729177.0A| EP3464829B1|2016-05-24|2017-05-18|Method for manufacturing a turbine engine casing with abradable coating|
    US16/303,561| US11002145B2|2016-05-24|2017-05-18|Method for manufacturing a turbine engine casing with abradable coating|
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