MACHINING DEVICE AND METHOD FOR REPAIRING AN ANNULAL PART

Abstract

The invention relates to a machining device (10) for an annular part (100; 110), particularly a turbomachine, characterized in that the machining device comprises: a clamping system (50) for removably attaching the machining device to the part; a machining tool (20) for machining at least one area of ​​the part; a transport carriage (30) for the machining tool; and a shaped rail (40) for guiding the transport carriage in translation along the area of ​​the part to be machined. Figure 3

Description

Title of the invention: MACHINING DEVICE AND METHOD FOR REPAIRING AN ANNULAR PART Technical field

[0001] The technical field of the invention is that of the repair of aircraft turbomachine parts.

[0002] The present invention relates to a device for machining an annular part, in particular a turbomachine, and a method for repairing such a part. Prior art

[0003] Turbomachines comprise various parts which, after use, may have damaged or worn areas due to friction or erosion caused by the ingestion of particles which are carried by one or more air flows passing through the turbomachine or during impacts of foreign bodies. These defective, damaged or worn parts have their profiles modified, thus degrading the performance of the part and that of the turbomachine. In the worst case, these parts may break, which can cause significant damage to the turbomachine.

[0004] Frequently, in the context of the repair of aircraft turbomachine parts, problems arise regarding the accessibility of these parts. These problems exist, for example, for the annular flange between the engine and the reverser of a turbomachine, for which no repair solution is known to date. In the event of excessive wear, this annular flange is completely replaced, requiring disassembly of the turbomachine in order to disassemble and replace the defective annular flange.

[0005] An aircraft is powered by several propulsion units each suspended from a fixed structure of the aircraft, for example under a wing or on the fuselage of the aircraft, by means of a suspension pylon. [Fig. 1] illustrates such a propulsion unit 1 comprising in a known manner on the one hand a turbojet engine 2 equipped with a fan and an engine, and on the other hand a nacelle 3 surrounding the turbojet engine and housing a thrust reverser.

[0006] The nacelle 3 generally has a tubular structure comprising an upstream section, or an air inlet 4 upstream of the turbojet engine 2, a middle section 5 intended to surround the fan of the turbojet engine, a downstream section 6 housing the thrust reverser and intended to surround a combustion chamber and the turbines of the turbojet engine, carrying the thrust reverser means, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbojet engine 2.

[0007] The downstream section 6 generally has an external structure comprising an external cover 7, which defines, with a concentric internal structure (not visible in [Fig.l]), called "Inner Fixed Structure" in English (IFS), the annular vein used to channel the flow of cold air. The internal structure defines an internal part of the annular vein, and generally comprises two half-shells connected together "at six o'clock" by means of a locking device.

[0008] The thrust reversal means make it possible, when an aircraft is landing, to improve its braking capacity by redirecting a majority fraction of the thrust generated by the turbojet engine forward.

[0009] The external fixed structure of a thrust reverser comprises, in a known manner, in particular a peripheral front frame intended to be mounted on a fan casing of the corresponding turbojet engine, a peripheral rear frame, and a plurality of flow deflection grilles fixed between the front and rear frames and extending substantially parallel to the longitudinal geometric axis of the thrust reverser. The front and rear frames are arranged transversely relative to the longitudinal geometric axis of the thrust reverser.

[0010] The front frame is connected to the fan casing by fixing means generally of the knife / groove type comprising a substantially annular flange also called an annular flange, made in one or more parts integral with the front frame and cooperating with a J- or V-shaped groove. The fixing assembly, as well as the annular flange which has a J-shaped (or V-shaped) section, are commonly referred to as the J-Ring.

[0011] Numerous cases of wear of annular flanges of this type have been observed due to a friction phenomenon between the annular flanges and the corresponding grooves of the fixing means. Excessive wear in this area leads to interface problems such as play, vibrations, etc.

[0012] Replacing this annular flange, generally made of aluminum, is a complex and lengthy operation, and therefore expensive. Indeed, this operation requires the dismantling of the nacelle and numerous elements on it, as well as its transport to a repair site.

[0013] Thus, it would be beneficial to find an alternative to replacing this part allowing it to be repaired under the wing, that is to say, when the part is still installed on the turbomachine, and also allowing the aircraft to be released quickly.

[0014] A dynamic spray repair method (in English “cold spray”), called recharging, can be implemented with a nozzle for spraying by direct jet of metal powder at very high speed to fill damage to the surface of worn parts.

[0015] However, such a repair method creates a deformed surface once the resurfacing is carried out.

[0016] [Fig.2] illustrates a sectional view of the geometry of an annular flange of the type "J-ring" 110 as well as a zone Z, to be repaired, of this annular flange 110. It can be observed that the space is restricted to insert a machining tool. Thus, today there is no machining device that can be inserted into this architecture without interfering with other components surrounding the annular flange 110. In other words, the geometry of the annular flange of the "J-Ring" type 110 makes it impossible to use a conventional machining device, especially when the annular flange remains installed on the aircraft.

[0017] The objective of the present invention is thus to propose a device for machining an annular part such as a J-ring type annular flange making it possible to find the original profile of the part and to control it while overcoming at least some of these drawbacks. Summary of the invention

[0018] To this end, the invention relates to a device for machining an annular part, in particular a turbomachine, characterized in that the machining device comprises: - a fixing system for fixing the machining device to the part in a removable manner; - a machining tool for machining at least one area to be machined of the part;

[0019] - a carriage for transporting the machining tool; and

[0020] - a rail shaped to guide the transport trolley in translation along the zone to machine the part.

[0021] The invention thus offers a solution to the problems mentioned above, making it possible to overcome the aforementioned accessibility and space requirements problems in order to repair a “J-Ring” type turbomachine part under the wing, or any other type of part whose geometry does not allow the use of a conventional machining device.

[0022] Thanks to the invention, it is possible to position the machining device according to the invention, so that the machining tool easily accesses the surface to be repaired of the part despite the geometry of the part and the restricted accessibility to this area to be repaired. The machining device according to the invention thus makes it possible to repair the annular part, such as an annular flange of a turbomachine, by restoring the original profile and characteristics of the part, while the part remains installed on the turbomachine, itself remaining under the wing of the aircraft. It is therefore no longer necessary to dismantle the turbomachine from the aircraft, allowing a faster release of the device than currently. The machining device according to the invention also makes it possible to repair the annular flange on equipment removed from the turbomachine, in a workshop for example.

[0023] Such a machining device according to the invention has the advantage of being easily transportable to the site of the aircraft equipped with such an annular part to be repaired. There is therefore no longer any need to dismantle and transport the nacelle to a repair workshop. The machining device is therefore quickly usable. In the case of a workshop repair, it thus avoids transporting the equipment and thus allows the operation in any workshop if necessary. It also has the advantage of being fixed directly to the part to be retouched so that it regains its original surface profile and in a simple manner.

[0024] The machining device according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another in any technically possible combination: - the machining device further comprises a system for moving the transport carriage on the rail along the area of ​​the part to be machined; - the movement system comprises a drive element for moving the transport carriage on the rail, preferably a rack-type drive element; - the system for moving the transport trolley on the rail includes a manual or electric advance system; - the transport carriage comprises a tray extending parallel to the rail and at least three rollers arranged on the tray, at least two of the rollers are configured to cooperate with a first guide track of the rail and at least one of the rollers is configured to cooperate with a second guide track of the rail, the two guide tracks are each arranged on a circumferential inner edge of the rail and a circumferential outer edge of the rail; - the machining device comprises a geometric control tool for the area to be machined of the part and in which the transport carriage is configured to support the geometric control tool; - the fixing system configured to fix the machining device to the part comprises at least one fixing flange to the part, preferably two fixing flanges to the part each arranged at one end of the rail, to hold the rail in position relative to the part; - the fixing system comprises at least one additional fixing element, preferably two additional fixing elements each arranged at one end of the rail, the additional fixing element(s) are configured to fix the rail to a frame supporting the part; - the transport carriage includes a system for positioning the machining tool relative to an area of ​​the part to be machined.

[0025] The invention also relates to a method for repairing an annular flange of a turbomachine, the annular flange having a damaged area, the method of re- preparation including the following steps: - a step of recharging material in the damaged area of ​​the annular flange to form a recharged area of ​​the annular flange; - a step of machining the resurfaced area of ​​the annular flange to obtain a repaired area of ​​the annular flange, this step being implemented by a machining device according to the invention and as described previously.

[0026] The machining method according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another in any technically possible combination: - the annular flange is installed on a turbomachine during the implementation of the repair process; - the method comprises a step of positioning the machining device opposite the resurfaced area of ​​the annular flange and a step of fixing the rail at least to the annular flange; - the method comprises a step of moving the transport carriage of the machining tool opposite the reloaded area of ​​the annular flange; - the method comprises a step of positioning the machining tool so as to machine the resurfaced area of ​​the annular flange to obtain a repaired area of ​​the annular flange. Brief description of the drawings

[0027] The present invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the description of a non-limiting example which follows, with reference to the appended drawings in which: - [Fig.l], already described, is a three-dimensional schematic view of a propulsion unit comprising an annular part which may require repair; - [Fig.2], already described, is a side view of an annular flange having a damaged area requiring repair; - [Fig.3] schematically represents a machining device according to an exemplary embodiment of the invention; - [Fig.4] represents a perspective view of the machining device of [Fig.3] in operational position; - [Fig.5] illustrates a profile and sectional view of the machining device of [Fig.3] in operational position; - [Fig.6] is an enlarged view of [Fig.5] at the level of the machining tool; - [Fig.7] is a view of the cutting tool of the machining device of [Fig.3] in the functional position for repairing a “J-Ring” type annular flange; - [Fig.8] illustrates the end of a “J-Ring” type annular flange in its initial state before wear; - [Fig.9] illustrates the end of the “J-Ring” type annular flange of [Fig.8] showing a worn area; - [Fig. 10] illustrates the result of a reloading step of the worn area of ​​the end of the “J-Ring” type annular flange of [Fig.9]; and - [Fig. 11] illustrates the result of a machining step implemented by the machining device according to the invention of the reloaded zone of the end of the annular flange of the “J-Ring” type of [Fig. 10].

[0028] Elements having the same functions in different implementations have the same references in the figures.

[0029] In the description and in the claims, the terms "upstream" and "downstream" are defined in relation to the circulation of the air flow inside the propulsion unit formed by the nacelle and the turbojet, that is to say from left to right with reference to [Fig.l]. Similarly, the expressions "internal" or "interior" and "external" or "exterior" will be used without limitation in reference to the radial distance from the longitudinal axis of the nacelle, the expression "internal" defining a zone radially closer to the longitudinal axis of the nacelle, as opposed to the expression "external". Furthermore, in the description and the claims, to clarify the description and the claims, the terminology axial, radial and transverse will be adopted without limitation in reference to the trihedron A, R, T indicated in the figures. Description of the embodiments

[0030] Reference is made to [Fig. 3] which illustrates a machining device according to an embodiment of the invention as well as to figures 4 to 7 representing views of the device of [Fig. 3] in functional position, that is to say arranged so as to be able to machine an annular part 100, in particular of a turbomachine.

[0031] Indeed, as indicated previously, such a turbomachine comprises annular parts which may require repair of damaged areas which are difficult to access.

[0032] In particular, a thrust reverser comprises means for fixing the front frame to the turbomachine comprising an annular flange of the J-ring type, due to its J or V shape.

[0033] Thus, in the example illustrated in Figures 4 to 7, the annular part 100 is an annular flange 110 of the J-Ring type of the thrust reverser.

[0034] Such an annular flange 110 is also illustrated in [Fig.8] and has at one end 112 folded or curved in a J or V shape, a surface subject to wear during use. Thus, the surface may have a damaged area as shown in [Fig.9].

[0035] The machining device according to the invention is suitable for repairing parts made of an alloy of aluminum, titanium or other metallic materials.

[0036] [Fig. 3] schematically represents an example of a machining device 10 of an annular part according to the invention. The annular part has a symmetry of revolution around an axis of revolution.

[0037] Such a machining device 10 comprises: - a machining tool 20 for machining at least one area to be machined of the part; - a transport carriage 30 for the machining tool 20; and - a rail 40 shaped to guide the transport carriage 30 in translation along the area of ​​the part to be machined. The machining tool 20 is a tool such as a drill, pneumatic or electric router, milling cutter or abrasive disc chosen according to the area of ​​the part to be machined.

[0038] The machining device 10 comprises a fixing system 50 for fixing the machining device to the workpiece, in this case to the annular flange 10, in a removable manner.

[0039] Advantageously, the fixing system 50 comprises at least one flange 52 for fixing to the part 100 to hold the rail in position relative to the part in a so-called axial direction A parallel to the axis of revolution of the annular part. In the example illustrated in FIGS. 3 and 4, such a fixing flange 52 comprises a substantially flat plate extending in a plane substantially perpendicular to the rail 40 of the machining device. The plate is fixed on the one hand to the part to be machined and on the other hand to the rail 40 by fixing means such as, for example, screw / nut systems.

[0040] Preferably, the fixing system 50 comprises two flanges 52 for fixing to the part, each arranged at one end of the rail 40.

[0041] Advantageously, the fixing system 50 comprises at least one additional fixing element 54 for fixing the rail to a frame 120 supporting the part. In the case of the annular flange 110, the additional fixing element 54 makes it possible to fix the positioning system to the frame supporting the annular flange 110 and thus to guarantee its positioning in a so-called radial direction R perpendicular to the axis of revolution of the annular part. For this purpose, the additional fixing element 54, in the example illustrated in Figures 3 and 4, comprises two arms extending perpendicular to each other: - a first arm extending radially outwards from a first end fixed to the rail 40, and in particular to an outer edge 44 of the rail 40, and comprising a second end opposite the first end, and - a second arm, extending perpendicular to the first arm and comprising a first end linked to the second end of the first arm and a second end opposite the first end of the second arm and comprising means for fixing to the frame 120, for example a screw / nut type system. The second arm can advantageously be connected by a radial axis sliding connection to the first arm facilitating the fixing of the machining device to the frame 120 in particular by adapting the additional fixing element to the dimensions of the frame. For this purpose, the first arm can also be movable along the rail.

[0042] Preferably, the fixing system comprises two additional fixing elements 54 each arranged at one end of the rail 40 and as described previously.

[0043] For example, the fixing flange(s) 52 and the additional fixing element(s) 54 are fixed by clamping respectively on the annular part and on the frame.

[0044] The rail 40 has a circular shape or an arc of a circle with a radius substantially equal to that of the annular part so that it can be juxtaposed therewith. Thus, once the machining device is installed and fixed to the annular part, the geometric center of the arc of a circle forming the rail 40 belongs to the axis of revolution of the annular part.

[0045] The rail 40 extends over an angular portion of angles between 60° and 180°. Preferably, the rail 40 extends over an angular sector of 60° making it possible to cover, for example, half of the annular part by moving the rail only three times. Such a dimension of the rail advantageously makes it easy to transport so that it can be used at the location where the equipment is positioned, anywhere in the world.

[0046] The rail 40 extends between a first end 41 and a second end 42 opposite the first end 4L.

[0047] According to the embodiment illustrated in Figures 3 to 7, the rail 40 extends radially between a circumferential inner edge 43 and the circumferential outer edge 44. The inner 43 and outer 44 edges of the rail define a main plane perpendicular to the axis of revolution of the annular part when the machining device is installed and fixed to the annular part. A main axis of the rail is defined, an axis perpendicular to the main plane of the rail and passing through its geometric center. Thus, when the machining device is installed and fixed to the annular part, the main axis of the rail and the axis of revolution of the annular part to be machined are the same.

[0048] The transport carriage 30 comprises a tray 32 or support configured to support the machining tool 20.

[0049] Advantageously, the transport carriage 30 comprises a positioning system 33 supported by the tray 32. The positioning system 33 is configured to po position with great precision in three directions perpendicular to each other the machining tool 20 relative to the area to be machined of the part. The positioning system 33 comprises adjustment means, such as micrometric screws, and means for locking the machining tool 20 in position relative to the area to be machined.

[0050] In the illustrated embodiment, when the transport carriage is arranged on the rail 40, the plate 32 extends in a plane parallel to the main plane of the rail, that is to say in a plane transverse to the main axis of the rail.

[0051] The plate 32 and the machining tool 20 are arranged on either side of the rail, in particular the main plane of the rail when the transport carriage is arranged on the rail 40 so that the machining tool 20 has access to the surface to be machined of the annular part when the machining device is installed and fixed to the annular part.

[0052] The transport carriage 30 is movable on the rail 40. Thus, the machining device 10 advantageously comprises a system 60 for moving the transport carriage 30 on the rail 40 along the area of ​​the part to be machined.

[0053] Advantageously, the movement system 60 comprises a drive element 62 for moving the transport carriage 30 on the rail 40.

[0054] In the exemplary embodiment of the machining device 10 illustrated in FIGS. 3 to 7, the drive element 62 is for example a rack-type drive element.

[0055] Thus, in the illustrated example, the drive element 62 comprises a toothed bar arranged on the rail 40 and a toothed wheel 66 arranged on the plate 32 of the transport carriage 30 and configured to cooperate with the toothed bar of the rail by meshing with the teeth of the toothed bar. The toothed wheel 66 extends parallel to the plate 30.

[0056] Preferably, the movement system 60, in particular the toothed wheel of the drive element, and the machining tool 20 are arranged on either side of the rail 40. More precisely, the machining tool 20 is arranged so as to be closer to the main axis of the rail than the movement system in order to minimize the size of the machining device and guarantee the machining tool access to the area to be machined and in order to balance the masses of the different elements of the machining device and thus guarantee optimum movement.

[0057] The system 60 for moving the transport carriage on the rail comprises a system for advancing on the rail 40. In the example illustrated, the advance system is manual and comprises a crank 68 configured to rotate the toothed wheel 66 of the drive element.

[0058] Alternatively, the feed system may be electric and comprise an electric motor configured to rotate the toothed wheel 66 of the element training.

[0059] Advantageously, the transport carriage 30 comprises at least three rollers arranged on the plate 32. The rollers, of general reference 34, are each movable in rotation about an axis of rotation perpendicular to the plate 32. At least two of the rollers are configured to cooperate with a guide track 45 of the rail and at least one of the rollers is configured to cooperate with another guide track 46 of the rail. The two guide tracks 45, 46 are each arranged on the inner edge 43 and the outer edge 44 of the rail.

[0060] In the example illustrated in the figures, four rollers denoted 34A, 34B, 34C, 34D are supported by the plate of the transport carriage. The rollers 34A and 34B are arranged radially outwardly relative to the rail 40 while the rollers 34C and 34D are arranged radially inwardly relative to the rail 40. In other words, the rail 40 is arranged between the pair of radially outward rollers 34A, 34B and the pair of radially inward rollers.

[0061] [Fig. 5] represents a profile and sectional view of the machining device in functional position in the sectional plane passing through the axes of rotation of the rollers 34B and 34D.

[0062] In the illustrated example, each roller has a groove 35 adapted to receive one of the guide tracks 45, 46 of the rail as is more visible in the sectional view illustrated in [Fig.4]. In the illustrated example, the groove has a V-shaped section and the guide tracks 45, 46 have a complementary shape, here a triangle. However, other shapes for the groove and consequently for the complementary shape of the guide track.

[0063] Similarly, as a variant, each guide track may comprise a groove and each roller may have at its circumferential end a protuberance of a shape complementary to that of the groove.

[0064] Advantageously, the machining device 10 may comprise a geometric control tool (not shown) configured to control the geometric profile of the surface to be machined / machined of the area to be machined of the part. In this case, the transport carriage 30 is configured to support said geometric control tool.

[0065] The geometric control tool is for example a mechanical or electronic micrometer with possibly a system for recording the position of the area to be machined and the profile of the surface before and after machining.

[0066] A method for repairing an annular flange of a turbomachine, for example of the “J-Ring” type, is now described. The annular flange 110 has at one end 112 folded or curved in the shape of a J or V, a surface S subject to wear during its use. The annular flange before use is illustrated in [Fig.8] and has an initial surface profile noted 'Si'.

[0067] After use, the annular flange has worn / damaged areas as shown in [Fig.9] with a loss of material compared to the original profile. Such a damaged area Z has a surface profile noted 'Su' and must be repaired.

[0068] The repair method comprises a step of recharging material in the damaged area of ​​the annular flange to form a Zr recharged area of ​​the adapter ring with a gain in material compared to the damaged area of ​​[Fig.9].

[0069] During this reloading step, the damaged area Z is coated with metal powder by a dynamic projection device adapted to carry out the reloading of the area.

[0070] Advantageously, this step can be carried out without removing the annular flange, i.e. while the annular flange is installed on the turbomachine using a gas dynamic projection device as described in patent application FR 2 209 900. There is therefore no disassembly to be carried out, allowing a considerable saving of time.

[0071] [Fig. 10] illustrates the result of this step. The damaged area with a surface profile 'Su' ([Fig.9]) was reloaded to form a reloaded Zr area with a surface profile denoted 'Sr'.

[0072] In order to recover the initial surface profile 'Si', the resurfaced area is machined during a machining step implemented by a machining device according to the invention and as described previously. For this purpose, the machining device is fixed to the part opposite the area to be machined by means of the fixing means 50 of the device and the machining tool 20 is moved on the rail by translation in order to place it opposite the area in order to machine it.

[0073] The result of this step is shown schematically in [Fig.l 1]. The reloaded Zr zone with a surface profile 'Sr' ([Fig. 10]) was machined to return to the original profile 'Si' of [Fig.8]'.

[0074] Advantageously, this step can also be carried out without removing the annular flange, i.e. while the annular flange is installed on the turbomachine. There is therefore no disassembly to be carried out, allowing a considerable saving of time.

[0075] The position of the transport carriage 30 and / or that of the machining tool 20 are modified as many times as necessary in order to repair all the damaged areas of the annular flange accessible by the tool in this position of the machining device relative to the annular flange.

[0076] The machining device is then moved again and fixed opposite another portion of the annular flange comprising resurfaced areas to be machined in order to cover this other portion of the annular flange accessible by the machining tool.

[0077] In particular, the machining device is positioned and the rail of the machining device is fixed from the rail at least to the annular flange and preferably also to the frame supporting the annular flange.

[0078] In the case where the machining device comprises at least one fixing flange 52 to the part 100, preferably two, to hold the rail in position relative to the part in the axial direction A parallel to the axis of revolution of the annular part, the machining step advantageously comprises a step of positioning the machining device opposite the resurfaced zone of the annular flange followed by a step of fixing the rail to the flange. In particular, the rail 40 is fixed to the annular flange 110 via at least one plate. The plate or plates are fixed on the one hand to the part to be machined 110 and on the other hand to at least one of the ends of the rail 40, preferably to each end of the rail 40, by fixing means such as screw / nut systems.

[0079] Furthermore, in the case where the machining device also comprises at least one additional fixing element 54 for fixing the rail 40 to a frame 120 supporting the part, the machining step also advantageously comprises a step of fixing the rail 40 to such a frame 120 in order to guarantee its positioning in the radial direction R perpendicular to the axis of revolution of the annular part.

[0080] According to the embodiment of the machining device in which the latter comprises a system 60 for moving the transport carriage on the rail, the machining step comprises, after the step of fixing the machining device to the part to be machined and where appropriate also to the frame supporting the part, a step of moving the transport carriage 30 of the machining tool 20 by the moving system in order to position it opposite the reloaded zone of the annular flange 110. Its position is then advantageously locked on the rail by a means of locking the transport carriage. Advantageously, the transport carriage is driven in its movement by the drive element 62 of the movement system 60, for example by a rack / toothed wheel type system. In the case where the movement system 60 further advantageously comprises a system for advancing on the rail 40, the transport carriage 30 can be easily moved along the rail manually via the crank 68 linked to the toothed wheel or electrically using a motor to maneuver said toothed wheel 66.

[0081] Furthermore, the machining tool 20 can be advantageously positioned precisely so as to machine the resurfaced area of ​​the annular flange to obtain a repaired area of ​​the annular flange using the geometric control tool for the area to be machined described above in the case where the transport carriage 30 is equipped with it. Its position is preferably locked before starting the machining of the area using a system for locking the position of the machining tool of the geometric control tool.

[0082] It should be noted that the examples illustrated in the figures are in no way limiting, the repair method previously described for an annular flange can be adapted to any other component whose shape and arrangement in a turbomachine does not allow machining under the wing, that is to say when the part remains installed on the turbomachine.

[0083] The machining device is suitable for machining any type of annular parts made of aluminum alloy, titanium or other metallic materials.

[0084] Such a machining device according to the invention has the advantage of being easily transportable to the site of the equipment of such an annular part to be repaired. There is therefore no longer any need to dismantle and transport the nacelle to a repair workshop. The machining device is thus quickly usable. It also has the advantage of being fixed directly to the part to be retouched so that it regains its original surface profile and in a simple manner.

Claims

Claims

1. Machining device (10) for an annular part (100; 110), in particular a turbomachine, characterized in that the machining device comprises: - a fixing system (50) for fixing the machining device to the part in a removable manner; - a machining tool (20) for machining at least one area to be machined of the part; - a transport carriage (30) for the machining tool; and - a rail (40) shaped to guide the transport carriage in translation along the area to be machined of the part, the rail being flat and having the shape of an arc of a circle.

2. Machining device according to claim 1, further comprising a system (60) for moving the transport carriage (30) on the rail (40) along the area to be machined of the part.

3. Machining device according to claim 2, wherein the displacement system (60) comprises a drive element (62) for moving the transport carriage (30) on the rail (40), preferably a rack-type drive element.

4. Machining device according to claim 2 or 3, in which the movement system (60) of the transport carriage on the rail comprises a manual or electric advance system.

5. Machining device according to one of claims 1 to 4, wherein the transport carriage (30) comprises a plate (32) extending parallel to the rail (40) and at least three rollers (34a, 34b, 34c, 34d) arranged on the plate, at least two of the rollers are configured to cooperate with a first guide track (45) of the rail and at least one of the rollers is configured to cooperate with a second guide track (46) of the rail, the two guide tracks are each arranged on a circumferential inner edge (43) of the rail and a circumferential outer edge (44) of the rail.

6. Machining device according to one of the preceding claims, comprising a geometric control tool for the area to be machined of the part and in which the transport carriage (30) is configured to support the geometric control tool.

7. Machining device according to one of the preceding claims, wherein the fixing system (50) configured to fix the device machining the part comprises at least one flange (52) for fixing to the part, preferably two flanges for fixing to the part each arranged at one end of the rail (40), to hold the rail in position relative to the part.

8. Machining device according to the preceding claim, in which the fixing system (50) comprises at least one additional fixing element (54), preferably two additional fixing elements (54) each arranged at one end of the rail (40), the additional fixing element(s) are configured to fix the rail to a frame supporting the part.

9. Machining device according to one of the preceding claims, in which the transport carriage (30) comprises a system (33) for positioning the machining tool (20) relative to an area of the part to be machined.

10. Method for repairing an annular flange of a turbomachine, the annular flange having a damaged area, the repair method comprising the following steps: - a step of recharging material in the damaged area of the annular flange to form a recharged area of the annular flange; - a step of machining the recharged area of the annular flange to obtain a repaired area of the annular flange, this step being implemented by a machining device according to one of the preceding claims.

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