BE1022808B1 - ABRADABLE JOINT OF AXIAL TURBOMACHINE COMPRESSOR HOUSING - Google Patents

Abstract

The invention relates to a method of making a seal, made of an abradable material for a low pressure compressor casing of an axial turbomachine. The method comprises the following steps: (a) providing or making (104) a sacrificial substrate; (b) projection (105) of a layer of abradable material on the sacrificial substrate, so that the layer has two opposite faces depending on its thickness, the first of the two faces being against the substrate; (c) fixing the substrate-abradable assembly (109; 110) on a casing of the turbomachine by placing the second of the two faces of the abradable layer against the casing; (d) removing (112) the sacrificial substrate so as to uncover the first side of the abradable layer. The invention also relates to a seal comprising the stacking of a layer of abradable material between a layer of fixing adhesive and a sacrificial substrate intended to be machined.

Description

Description

ABRADABLE JOINT OF AXIAL TURBOMACHINE COMPRESSOR HOUSING

Technical Field The invention addresses the field of abradable joints for axial turbomachine. More specifically, the invention relates to a method of applying an abradable seal on an axial turbomachine compressor shell. The invention also deals with an axial turbomachine.

Prior art

An abradable material is known for providing dynamic sealing in a turbomachine, in particular in a compressor of the axial turbomachine. Such a material is applied in a layer on an outer casing and is able to crumble in case of contact with the ends of the rotor blades without damaging them. The mechanical integrity is preserved despite rotation speeds above 4000 rpm, and a relative speed close to the speed of sound. Such a material is also used for sealing under inner shells, or on a drive shaft bearing.

In this way, it is possible to design a compressor while reducing the operating clearance between the ends of the rotor blades and the inner surface of the housing. The optimization can also take into account the expansion, the centrifugal force; and some operational hazards such as ingestions and pumping phenomena. An abradable material forming a casing coating generally comprises aluminum, silica, polyester.

This type of material is commonly applied by plasma spraying, whose temperature can reach 3000 ° C. In the context of a composite substrate, in particular an organic matrix composite outer casing, this temperature can create degradations. The organic matrix and / or the fibers may deteriorate. To preserve the composite material, it is known to use a metal strip as an interlayer between the composite housing and the hot-cast abradable material.

EP2418387 A1 discloses a low pressure axial turbine compressor with abradable joints. The seals have an Al-Si-Polyester composition, and are projected by plasma onto the inner surface of the compressor housing. The structuring wall of the compressor is made of a composite material with carbon fibers and an epoxy resin. A steel strip is glued inside the composite casing prior to the plasma projection of the abradable material, the strip then offers a receiving surface of the abradable. Surely, such a seal provides a dynamic seal between the housing and an annular row of rotor blades that surrounds. However, the overall cost of such a seal remains high. In addition, the establishment of the strip faces its stiffness to accommodate the variations of curvature of the housing. Summary of the invention

TECHNICAL PROBLEM The invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to reduce the cost of producing an abradable seal for a turbomachine casing. The invention also aims to simplify the integration of an abradable seal in a turbomachine.

TECHNICAL SOLUTION The subject of the invention is a method of producing a sealing device, in particular an abradable seal, of a turbomachine casing; for example an axial turbomachine compressor casing; remarkable in that the method comprises the following steps: (a) providing or producing a sacrificial substrate; (b) projecting a layer of abradable material on the sacrificial substrate, so that the layer has two opposite faces according to its thickness, the first of the two faces being against the housing; (c) fixing the substrate-abradable assembly on a casing of the turbomachine by placing the second of the two faces of the abradable layer towards the substrate; and then (d) removing the sacrificial substrate so as to discover the first side of the abradable layer.

By "towards the housing" one can hear radially opposite the housing.

According to an advantageous embodiment of the invention, during step (a) supply or production, the sacrificial substrate is circular, and at the end of step (b) projection, the method comprises a step of cutting the substrate-abradable assembly in angular segments, preferably the cut is a wire cut.

According to an advantageous embodiment of the invention, during step (b) projection, the sacrificial substrate is held on a support, for example a mandrel having a surface conforming to the substrate.

According to an advantageous embodiment of the invention, during step (c) fixation, the method comprises a phase of placing the substrate-abradable assembly in an injection mold, then an injection step of a resin in the mold so as to form the housing by linking the substrate-abradable assembly.

According to an advantageous embodiment of the invention, during step (c) fixation, the method comprises a phase of placing a fibrous preform in the mold, coming against the substrate-abradable assembly so as to cover, the fibrous preform forming a reinforcement of the housing, and the injection being an RTM injection.

According to an advantageous embodiment of the invention, during step (c) fixation, the substrate-abradable assembly is fixed on the housing by gluing with a layer of glue cooperating with the abradable layer.

According to an advantageous embodiment of the invention, at the end of step (b), the substrate-abradable assembly is maintained for at least 30 minutes at a temperature above 100 ° C., preferably maintained for at least one hour. hour at a temperature greater than or equal to 150 ° C.

According to an advantageous embodiment of the invention, during step (d) deletion, the substrate is removed by machining, in particular by turning; optionally during step (d) deletion, a film of the abradable layer is removed, in particular by machining. The invention also relates to a sealing device, in particular an abradable seal precursor, for a turbomachine, optionally an axial turbomachine compressor, the device comprising: a substrate having two opposite faces according to its thickness; a layer of abradable material covering one of the faces of the substrate, the layer being adapted to cooperate by abrasion with an annular row of rotor blades of the turbomachine; remarkable in that it further comprises a layer of adhesive applied to the abradable layer so that the abradable layer is between the adhesive layer and the substrate.

According to an advantageous embodiment of the invention, the substrate is a ribbon.

According to an advantageous embodiment of the invention, the substrate and the abradable layer are circular or form a circular arc.

According to an advantageous embodiment of the invention, the substrate and the abradable layer form a coiled coil.

According to an advantageous embodiment of the invention, the ribbon is metallic, such as aluminum.

According to an advantageous embodiment of the invention, the thickness of the substrate is between 0.05 mm and 5.00 mm; preferably between 0.50 mm and 3.00 mm, more preferably between 1.50 mm and 2.00 mm.

According to an advantageous embodiment of the invention, the glue is a glue film, optionally epoxy.

According to an advantageous embodiment of the invention, the abradable layer comprises aluminum and polyester

According to an advantageous embodiment of the invention, the abradable layer comprises silicon, or nickel, or iron, or copper, or nicral.

According to an advantageous embodiment of the invention, the abradable layer is a main abradable layer, the device further comprising an underlayer between the main abradable layer and the substrate, optionally the underlayer is essentially metallic.

According to an advantageous embodiment of the invention, the abradable underlayer comprises between 95% and 80% by weight of nickel and between 5% and 20% by weight of aluminum. According to an advantageous embodiment of the invention, the device comprises a protective film against the adhesive layer and / or a sealed package.

According to an advantageous embodiment of the invention, the adhesive layer has a weight per unit area of between 100 and 900 g / m 2, preferably between 300 and 500 g / m 2.

According to an advantageous embodiment of the invention, the density of the sub-layer is greater than the density of the abradable main layer, preferably greater than at least 10%; more preferably greater than 50%; possibly greater by at least 100%.

According to an advantageous embodiment of the invention, the adhesive layer is intended to be fixed to the stator of the turbomachine, for example to its housing; or its rotor. The invention also relates to a turbomachine comprising a housing with a sealing device, characterized in that the sealing device is produced according to the invention; and / or the sealing device is in accordance with the invention, optionally the housing is a composite organic matrix housing and is formed of two half-shells.

In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention.

Advantages The invention makes it possible to improve the cohesion between an abradable layer and its stator. It makes it possible to dispense with the presence of a strip between the casing and the abradable layer, which lighten the turbomachine in addition to reducing costs. Indeed, the cost of the substrate is lower than that of a corresponding strip because the substrate is not in the final turbomachine. The number of components decreases, as does the number of interfaces between the different materials. The invention provides a simple seal to implement; which can be simply glued into the turbomachine or integrated during the molding process. The invention makes it possible to simultaneously produce several abradable joints on the same housing or support.

Brief description of the drawings

FIG. 1 represents an axial turbomachine according to the invention.

Figure 2 outlines a turbomachine compressor according to the invention.

FIG. 3 represents a diagram of the process for producing a sealing device for a turbomachine casing.

FIG. 4 illustrates the step of supplying or manufacturing the substrate of the method according to the invention.

FIG. 5 illustrates the plasma projection step of the method according to the invention.

FIG. 6 illustrates a step of machining the abradable of the method according to the invention.

FIG. 7 illustrates the cutting step of the method according to the invention.

FIG. 8 illustrates the step of implementing an adhesive layer of the process according to the invention.

FIG. 9 illustrates a first phase of the step of fixing the seal of the method according to the invention.

Figure 10 illustrates a second phase of the step of fixing the seal of the method according to the invention.

Figure 11 illustrates an intermediate state of the process where the seal precursor is in a state attached to the housing.

Figure 12 illustrates the step of removing the substrate of the method according to the invention.

Description of the embodiments

In the following description, the terms inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine.

FIG. 1 is a simplified representation of an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8. Reducing means can increase the speed of rotation transmitted. compressors.

An inlet fan commonly referred to as a fan or fan 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet. The secondary flow can be accelerated to generate a thrust reaction. The primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical walls or ferrules which can be internal and external.

FIG. 2 is a sectional view of a compressor of an axial turbomachine such as that of FIG. 1. The compressor may be a low-pressure compressor 4. There may be seen a part of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, in this case three.

The low pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26. The rectifiers are associated with the fan 16 or a row of rotor vanes to straighten the flow of air, so as to convert the speed of the flow into static pressure. The stator vanes 26 extend essentially radially from an outer casing 28, and can be fixed thereto by means of fixing pins.

The compressor 4 has sealing devices. The housing comprises abradable sealing joints 30, arranged around the annular rows of rotor blades. The devices, via the abradable joints 30, provide dynamic sealing with the rotor rows since the clearance between the casing and the radial ends of the blades can be reduced to a minimum during operation of the turbomachine, for example in flight conditions. This reduction is authorized thanks to the use of abradable material, the ability to crumble in case of contact with the rotor blades 24 prevents damage. The seals 30 may be circular or annular. They have internal generally tubular or substantially frustoconical sealing surfaces. The length of at least one or each abradable seal 30 may be greater than 1 cm, preferably greater than 4 cm; the length being measured along the axis 14 of the turbomachine.

FIG. 3 represents a diagram of the process for producing a sealing device for a turbomachine, for example of one of the abradable joints represented in FIG. 3.

The method may comprise the following steps, possibly carried out in the following order: - supply or realization 104 of a sacrificial substrate; placing the substrate on a support such as a mandrel; projection 105 of an underlayer of abradable material on the substrate; - projection 105 of a main layer of abradable material on the sacrificial substrate by covering the abradable underlayer, the underlayer and the main layer form a complex layer of abradable, said abradable or abradable layer; the abradable layer having two opposite faces according to its thickness, the first of the two faces being towards the substrate; - Relaxation of the abradable by maintaining it at a temperature of 150 ° C for one hour, which eliminates internal stresses, this step is optional; machining 106 of the abradable face which is opposite the substrate, said second face; - cutting 107 of the precursor of the abradable seal - applying a layer of adhesive 108 on the second face of the abradable which has been previously machined; fixing the substrate-abradable-adhesive assembly on a casing of the turbomachine by placing the second of the two faces of the abradable against the casing; this step comprising a first phase 109 and a second phase 110; an intermediate state 111 is then observed in which the precursor of the seal is bonded to the casing; removing the sacrificial substrate 112, and possibly the underlayer, so as to discover the first face of the abradable and / or the main layer.

It should be noted that according to the invention, the stages of projection of an underlayer, expansion of the abradable, machining 106 of the abradable face, application of a glue film 108 are optional. These steps make it possible to modulate the quality of a seal according to the invention but they are not essential to achieve the result of the invention and / or to solve the technical problem posed by the invention.

FIG. 4 represents the step of supplying or producing a sacrificial substrate 32 of the process for producing the abradable gasket for a turbomachine.

The substrate 32 may be a ribbon, for example a sheet. The material used may be steel, or aluminum to facilitate the shaping, and the subsequent removal. The substrate 32 may have a tube shape, or cone base. It can be made from a band of arcuate material then closed like a ferrule; it can also be made from a deformed flat washer to become conical.

Following its implementation, the substrate 32 may be arranged on a support 34. The support 34 forms a tool for immobilizing the substrate 32, maintaining it in a given rounded shape. The support 34 is configured to withstand mechanical forces of projection and removal of material. It may have a conical receiving surface conforming to the inner annular face of the substrate 32.

Figure 5 shows the process abradable projection steps.

At least one abradable layer 36 is projected onto the substrate 32 by means of a torch 38. The substrate 32 thus forms a structure that provides a surface receiving the abradable projected. The or each projection may be a plasma projection, this method of applying an abradable material being well known to those skilled in the art.

First, an underlayer may be projected onto the substrate. This underlayer may comprise nickel and aluminum, for example between 95% and 80% by weight of nickel, and between 5% and 20% by weight of aluminum. This underlayer may make it possible to improve the adhesion of another layer of abradable material, for example when the substrate 32 is metallic. The presence of the underlayer is optional because the grip of a main abradable layer may suffice.

Then, a main layer of abradable can be projected towards the substrate 32; either directly on it or on the underlayer if it is present. The main layer of abradable material may comprise aluminum, silicon, and polyester. Nickel or iron or copper or nickel can replace silicon. Its composition can be adapted to improve the strength of the seal and the seal.

The underlayer may have a thickness less than that of the main layer. The underlayer may have a thickness of between 0.05 mm and 0.50 mm; optionally equal to 0.10 mm. The thickness of the main layer may be between 0.50 mm and 5.00 mm; preferably between 1.00 mm and 3.00 mm.

FIG. 6 represents the step of machining the second face of the abradable layer 36, which face is opposite to the substrate 32. The precursor 40 of the seal being shown in section. The underlayer and the main layer are represented in one and the same layer of abradable material 36.

The substrate 32 may be a ribbon with two opposite faces according to its thickness, including an inner face 42 and an outer face 44. The abradable 36 may also have two opposite faces according to its thickness, including an inner face 46 or first face 46 which remains free, and an outer face 48 or second face 48 in contact with the substrate 32 by covering it.

Following the projection of the abradable, the free surface 48 of the latter may have asperities and possibly a variable thickness. The length of the abradable track, along the axis of revolution of the joint, can also vary. To correct the length of the abradable track and to improve the surface condition, the abradable layer 46 is machined to a predetermined envelope 50. The abradable 36 can be machined by turning or milling. This removal of material can be done directly on the support. The machining of the abradable can be adapted to fit a housing with an internal ogive surface.

FIG. 7 represents the step of cutting the substrate-abradable assembly of the process for producing the abradable gasket for a turbomachine.

The seal can be formed as angular segments 52 or angular sectors 52. Therefore, following the step of expansion of the substrate-abradable assembly, a cutting step can be performed. The precursor of the seal 40 can be cut into angular sectors 52, for example into six sectors 52. A wire cut can be made to reduce the thickness of the cutting lines 54, to limit heating and to limit the mechanical effects of cutting .

FIG. 8 represents the step of applying the glue layer of the process. The precursor of the seal being shown in section.

In order to fix it, a layer of adhesive 56 is applied to the abradable, in this case to the main layer 58. The adhesive layer 56 is placed opposite the substrate 32 with respect to the abradable element 36. The adhesive used may be an epoxy glue film, for example with a surface density of 380 grams per square meter. Such a glue film is known to those skilled in the art, the REDUX® 322/380 gsm product may be suitable.

Such an abradable seal precursor 40 can be marketed. It may be marketed comprising a sacrificial substrate 32, an abradal layer 36, a layer of adhesive 56, the abradable possibly comprising several stacked layers (58; 60).

In addition, the seal may receive a protective film 62 on the adhesive 56 so as to protect it. Moreover, the precursor of the abradable seal 40, possibly in the form of an angular segment, may comprise a sealed package which completely envelopes it.

FIG. 9 represents a first phase of the step of fixing the precursor of the gasket to the casing of the process for producing the abradable gasket for a turbomachine.

The fixing of the precursor of the seal 40 on the housing can be carried out in different ways. The precursor of the seal 40 can be directly attached to the inner surface of a casing of a turbomachine, by placing the substrate 32 inwards. Fixing can be done thanks to the adhesive layer 56.

Or again, fixing the precursor of the seal 40 to the housing can be carried out simultaneously with the production of the housing, for example when the housing is made of composite material. For this purpose, a mold 64 for producing the housing is adapted. This has a groove in which is placed the precursor of the seal 40. The adhesive layer 56 is flush with the outer surface 66 of the mold 64, and the protective film of the glue 56 has been removed.

FIG. 10 represents a second phase of the step of fixing the precursor of the seal 40 to the casing of the process.

A fiber preform 68 may be placed against the outer surface of the mold 66. The preform covers the precursor of the seal 40, and in particular the adhesive layer 56 with which it is in contact. It may comprise a fibrous mat; for example woven in three dimensions. Or again, the fiber preform 68 may comprise a stack of fibrous folds, for example woven. The preform 68 may be pre-impregnated. Glass, graphite, carbon fibers can be used. Other useful inserts may be placed, for example, attached fastening flanges or any other useful element.

Following the introduction of the preform 65, the mold can be closed. This can be achieved by using a membrane, or a counter mold pressed against the preform 68 by compacting it. Then, a resin 70 is injected into the molding cavity by impregnating the fiber preform 68. This molding can be of the RTM type for "Resin Transfer Molding". An epoxy resin may be suitable in this context. The injection is carried out hot; that is to say at a temperature above 50 ° C, preferably above 100 ° C.

The temperature promotes the connection between the abradable layer 36 and the preform 68 through the adhesive layer 56 which may optionally be mixed with the injected resin, at least partially.

According to an alternative of the invention, the composite casing can be made by injecting a filled resin containing fibers. The fibers may have a length of less than 10 mm, preferably less than 5 mm, more preferably less than 2 mm. The length can be an average length.

FIG. 11 represents a final state of the step of fixing the precursor of the seal to the casing. At the end of the injection, the resin and the adhesive polymerize so that the housing-abradable-substrate assembly forms a solid, a block of material. This block is then removed from the mold. It may have a stack with the housing wall 28, a glue layer 56, the abradable main layer 58, the underlayer 60, the substrate 32. Other layers, for example interleaved, may be added to reduce the cost of the seal; to improve the mechanical strength, the seal, the friable character of the seal.

The housing 28 may be circular. It can also be formed of half-shells which are molded separately and then brought against each other. In the case of half-shells, three of the six angular joint segments may be associated with each half-shell. It is also possible to create a quarter housing, which has four, six, eight or more angular crank sectors. The cutting of the seal segments can be adapted accordingly.

FIG. 12 represents the step of removing the substrate 32 from the seal 30.

The substrate 32 may have an unsuitable friable or abradable character, that is to say which could degrade the rotor blades 24 of the turbomachine in case of contact. To unveil, release the abradable, the substrate 32 (dashed line) is removed or deleted. Similarly, the underlayer 60 (drawn in dashed line) may have an unsuitable friable or abradable character. To unveil, release the main layer of abradable 58, the underlayer 60 is removed or removed. A thin film of the main layer 58 can also be removed together with the adjoining layer. The substrate then acquires a temporary support role making it possible to receive and maintain the main abradable layer 58 from the abradable projection step until the end of the attachment to the casing 28. The suppression can take place perform by machining; for example by turning to improve the circularity. Milling can be used. It is also possible to use a chemical or thermal process. The skilled person is rightly encouraged to consider other solutions to remove the substrate 32 and / or the underlayer 60. At the end of the removal step, the main layer of abradable 58 bonded to the housing can present a composition, a homogeneous structure axially and radially. It is essentially connected to the housing 28 via the adhesive layer 56. Its inner surface can cooperate with outer ends of rotor blades 24 to provide a dynamic seal.

Subsequently, the housing wall 28 can receive stator vanes which are fixed using their attachment platforms. These platforms can come into contact, abutting against the abradable layer. This cooperation can make it possible to position and lock in rotation the stator vanes. Dimension chains may be accurate since the upstream and downstream edges of the abradable have been machined; in addition to being precisely positioned through the throat of the mold. The deletion can also take place after the integration of the stator vanes, or during. The invention has just been presented in relation to an abradable seal 30 of outer casing 28. However, such a seal 30 may be adapted for an inner shell; for example by modifying the segmentation, the cutting of the joint segments. It is also possible to make an abradable seal cooperating with annular ribs, wipers; for example to form a labyrinth seal. The seal 30, in particular its abrabable portion can be placed on the stator or the rotor of the turbomachine.

Claims (21)

claims 1. A method of producing a sealing device, in particular an abradable seal (30), turbomachine casing (28) (2); for example, axial turbomachine compressor casing (28) (28), characterized in that the method comprises the following steps: (a) supplying or producing (104) a sacrificial substrate (32); (b) projecting (105) a layer of abradable material (36; 58; 60) on the sacrificial substrate (32) so that the layer (36) has two opposing faces (46; thickness, the first (46) of the two faces being against the substrate (32); (c) securing (109; 110) the substrate-abradable assembly to a casing (28) of the turbomachine (2) by placing the second (48) of the two faces of the abradable layer (36) towards the casing (28); and then (d) removing (112) the sacrificial substrate so as to discover the first face (48) of the abradable layer. 2. Method according to claim 1, characterized in that during step (a) supply or embodiment (104), the sacrificial substrate (32) is circular, and at the end of step (b) projection ( 105), the method comprises a step of cutting (107) the substrate-abradable assembly into angular segments (52), preferably the cut is a wire cut. 3. Method according to one of claims 1 to 2, characterized in that during step (b) projection (105), the sacrificial substrate (32) is held on a support (34), for example a mandrel having a surface conforming to the substrate (32). 4. Method according to one of claims 1 to 3, characterized in that during the step (c) fixing (109; 110), the method comprises a phase (109) of setting up the substrate-substrate assembly. abradable in an injection mold (64), then a step of injecting a resin (70) in the mold (64) so as to form the housing (28) by linking the substrate-abradable assembly. 5. Method according to claim 4, characterized in that during the step (c) fixation (109; 110), the method comprises a phase of placing a fibrous preform (68) in the mold (64) , against the substrate-abradable assembly so as to cover it, the fiber preform (68) forming a reinforcement of the housing (28), and the injection being an RTM injection. 6. Method according to one of claims 1 to 5, characterized in that during step (c) fixing (109; 110), the substrate-abradable assembly is fixed on the housing (28) by gluing with an adhesive layer (56) cooperating with the abradable layer (36). 7. Method according to one of claims 1 to 6, characterized in that at the end of step (b) projection (105), the substrate-abradable assembly is maintained for at least 30 minutes at a temperature greater than 100 ° C, preferably maintained for at least one hour at a temperature greater than or equal to 150 ° C. 8. Method according to one of claims 1 to 7, characterized in that during step (d) deletion (112), the substrate (32) is removed by machining, in particular by turning; optionally during step (d) deletion (112), a film of the abradable layer (36) is removed, in particular by machining. 9. Sealing device, in particular an abradable seal precursor (40), for a turbomachine (2), optionally a compressor (4; 6) for an axial turbomachine (2), the device comprising: - a substrate (32) having two opposite faces (42; 44) according to its thickness; a layer of abradable material covering one of the faces of the substrate, the layer being able to cooperate by abrasion with an annular row of rotor blades of the turbomachine. ; characterized in that it further comprises an adhesive layer (56) applied to the abradable layer (36) so that the abradable layer (36) is between the adhesive layer (56) and the substrate ( 32). 10. Device according to claim 9, characterized in that the substrate (32) is a ribbon. 11. Device according to claim 10, characterized in that the ribbon is metal such aluminum. 12. Device according to one of claims 9 to 11, characterized in that the substrate (32) and the abradable layer (36) are circular or form a circular arc. 13. Device according to one of claims 9 to 11, characterized in that the substrate (32) and the abradable layer (36) form a coiled coil. 14. Device according to one of claims 9 to 13, characterized in that the thickness of the substrate (32) is between 0.05 mm and 5.00 mm; preferably between 0.50 mm and 3.00 mm, more preferably between 1.50 mm and 2.00 mm. 15. Device according to one of claims 9 to 14, characterized in that the adhesive (56) is a glue film, optionally epoxy. 16. Device according to one of claims 9 to 15, characterized in that the abradable layer (36) comprises aluminum and polyester 17. Device according to one of claims 9 to 16, characterized in that the abradable layer (36) comprises silicon, or nickel, or iron, or copper, or nicral. 18. Device according to one of claims 9 to 17, characterized in that the abradable layer (36) is a main abradable layer (58), the device further comprising an underlayer (60) between the abradable layer main (58) and the substrate (32), optionally the underlayer (60) is essentially metallic. 19. Device according to claim 18, characterized in that the abradable sub-layer (60) comprises between 95% and 80% by weight of nickel, and between 5% and 20% by weight of aluminum. 20. Device according to one of claims 9 to 19, characterized in that it comprises a protective film (62) against the adhesive layer (56) and / or a sealed package. 21. Turbomachine (2) comprising a housing (28) with a sealing device, characterized in that the sealing device is produced according to one of claims 1 to 8; and / or the sealing device is according to one of claims 9 to 20, optionally the housing (28) is an organic matrix composite housing and is formed of two half-shells.