Deformation-preventing clamping tool for machining aero-engine cover plate

Abstract

The utility model relates to a deformation prevention fixture for aero-engine cover plate processing, which comprises a base provided with a placing groove, an aero-engine cover plate to be processed can be placed in the placing groove, a concave-convex part is arranged in the placing groove, the aero-engine cover plate to be processed is connected with the bottom surface of the placing groove through adhesive, and the aero-engine cover plate to be processed can be placed in the placing groove. Compared with the prior art, the aero-engine cover plate machining base has the advantages that when an aero-engine cover plate is machined, the cover plate is placed in the containing groove in the base, the concave-convex part is arranged in the containing groove at the moment, and the concave-convex part is matched with a concave-convex structure on the aero-engine cover plate; according to the aero-engine cover plate, the concave-convex structure on the aero-engine cover plate is internally supported through the concave-convex part, other positions on the aero-engine cover plate are attached to the bottom face of the containing groove at the moment, the aero-engine cover plate and the base are bonded through AB glue serving as an adhesive, and at the moment, the aero-engine cover plate is stable and not prone to deformation in the machining process.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aero-engine parts tooling equipment, specifically relates to a prevent deformation clamping fixture for aero-engine cover plate processing. BACKGROUND

[0002] The aero-engine is a kind of highly complex and precision thermodynamic machinery, which is combined by several precision components and systems, in order to protect the precision components, so the protective shell needs to be installed when finally assembling, i.e. the front and rear cover plates of the engine, and in order to make the cover plate fully protect the precision components of the engine and simultaneously form the shell, the cover plate also needs to be processed accordingly.

[0003] The prior art discloses a kind of aero-engine cover plate processing clamps, and the authorized announcement number is CN211889897U, which is mainly used for processing the cover plate of automobile engine, specifically including support base, first side fixed platform, second side fixed platform, lifting motor, support rod, support platform, first rotating disc, second rotating disc, clamp, rotating motor, connecting shaft, telescopic motor and fastening knob etc., in working process, first aero-engine cover plate is placed on support platform, the longitudinal position of aero-engine cover plate is adjusted by lifting motor, then the position of first rotating disc is adjusted by telescopic motor, both ends of aero-engine cover plate are fixed by clamp, then telescopic motor is opened again, to ensure that two rotating disc supports are firm and firm, after being firm, aero-engine cover plate is adjusted in position by rotating motor.

[0004] But in the above technical scheme, when the position of aero-engine cover plate is fastened, a part of aero-engine cover plate is still in the state of not being supported, due to the influence of thickness, material and shape of aero-engine cover plate, after fastening and processing aero-engine cover plate by using the above clamp, it is easy to cause large deformation of aero-engine cover plate, causing problems such as part size and technical requirement out of tolerance. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing a clamping fixture that can improve the stability of aero-engine cover plate processing, so that aero-engine cover plate is fully supported during processing and deformation is reduced.

[0006] In order to achieve the above object, the utility model discloses the technical scheme that a kind of anti-deformation clamping fixture for aero-engine cover plate processing is used, including the base being provided with placing groove, the aero-engine cover plate to be processed can be placed in placing groove, the contour shape of placing groove is compatible with the contour shape of the aero-engine cover plate to be processed, recessed and protruding part is provided in placing groove, recessed and protruding part is supported inside to the recessed and protruding structure of the aero-engine cover plate to be processed, the bottom surface between the aero-engine cover plate to be processed and placing groove is connected by adhesive, cutting assembly is provided in placing groove, and cutting assembly can cut adhesive.

[0007] As a further improvement of the utility model, the cutting assembly is connected with a driving member, the driving member is located in the central passage, and the central passage is provided on the base and penetrates the base horizontally.

[0008] As a preferred scheme of the utility model, the cutting assembly includes a rotating rod, a cap is provided on the rotating rod, and a cutting piece is provided on the cap. The rotating rod drives the cutting piece to move when rotating. The adhesive is located on the moving track of the cutting piece.

[0009] As a further improvement of the utility model, the lower end of the rotating rod is provided with a driving gear, the driving gear is engaged with the driving member, and the driving member moves in the central passage to rotate the rotating rod.

[0010] As a further improvement of the utility model, the cutting assembly includes a sliding block, the sliding block is connected with the driving member, and the cutting piece is connected on the sliding block. The driving member can drive the sliding block to translate in the placing groove.

[0011] As a further improvement of the utility model, an inner support groove is provided in the placing groove, and an inner support strip is installed in the inner support groove. When the aero-engine cover plate to be processed is placed in the placing groove, the upper surface of the inner support strip is in contact with the position close to the edge of the aero-engine cover plate.

[0012] As a further improvement of the utility model, an extension plate is provided on the inner support strip, and there is a gap between the upper surface of the extension plate and the aero-engine cover plate to be processed. The adhesive is applied on the extension plate.

[0013] As a further improvement of the utility model, a compression return spring is connected between the inner support strip and the bottom surface of the inner support groove, and the inner support strip and the extension plate can both enter the inner support groove.

[0014] Compared with the prior art, the aero-engine cover plate is placed in the placing groove on the base during machining, at this time, the concave-convex part is arranged in the placing groove, the concave-convex part is matched with the concave-convex structure on the aero-engine cover plate, the concave-convex structure on the aero-engine cover plate is supported by the concave-convex part, and at this time, the aero-engine cover plate is adhered to the base by AB glue as an adhesive, so that the aero-engine cover plate is relatively stable and will not be easily deformed during the machining process.

[0015] In addition, when the aero-engine cover plate needs to be taken down after machining is completed, the solidified adhesive can be cut by translation of the driving part in the center channel, and after the adhesive is cut, the aero-engine cover plate can be conveniently taken down, and the machining efficiency can be improved. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is an application state schematic view of the utility model;

[0017] Figure 2 It is a first peeling mechanism and base connection overhead structure schematic view of the utility model;

[0018] Figure 3 It is a first peeling mechanism and base connection side view schematic view of the utility model;

[0019] Figure 4 It is a first peeling mechanism and driving part connection schematic view of the utility model;

[0020] Figure 5 It is a second peeling mechanism and base connection overhead structure schematic view of the utility model;

[0021] Figure 6 It is a second peeling mechanism and base connection side view schematic view of the utility model;

[0022] Figure 7 It is a second peeling mechanism and driving part connection schematic view of the utility model;

[0023] Wherein, 1-base, 2-aero-engine cover plate, 3-placing groove, 4-concave-convex part, 5-center channel, 6-displacement channel, 7-driving part, 8-rotation rod, 9-tray, 10-cap, 11-slice, 12-sliding block, 13-inner support groove, 14-inner support strip, 15-compression return spring, 16-outer extension plate, 17-pressing plate, 18-horizontal supporting plate, 19-end position seat, 20-flat push screw rod, 21-intermediate piece. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be understood that the preferred embodiments described herein are only used to explain and illustrate the present application, and are not intended to limit the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application. In the embodiments, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed application, but only represents selected embodiments of the present application.

[0025] Referring to Figure 1 As shown in the drawings, a deformation-preventing clamping fixture for machining an aero-engine cover plate comprises a base 1 which can be installed on a machining platform, the base 1 is provided with a placing groove 3, the contour shape of the placing groove 3 is matched with the contour shape of the aero-engine cover plate 2 to be machined, the aero-engine cover plate 2 can be placed in the placing groove 3, at this time, the upper surface of the aero-engine cover plate 2 is exposed, that is, the depth of the placing groove 3 is smaller than the thickness of the aero-engine cover plate 2, then the position of the aero-engine cover plate 2 is locked, and the aero-engine cover plate 2 can be subjected to surface machining.

[0026] The concave-convex part 4 is arranged in the placing groove 3, the concave-convex part 4 is matched with the concave-convex structure on the aero-engine cover plate 2, and forms an internal support for the aero-engine cover plate 2, so that the aero-engine cover plate 2 is fully supported, and the deformation of the aero-engine cover plate 2 can be reduced when the surface of the aero-engine cover plate 2 is subjected to milling machining.

[0027] Referring to Figures 2 to 7 When the aero-engine cover plate 2 is positioned, the aero-engine cover plate 2 is connected with the base 1 through an adhesive, specifically, AB glue can be used as the adhesive, the adhesive is applied at a plurality of positions close to the edge in the placing groove 3 during the process of connecting the aero-engine cover plate 2 with the base 1, at this time, a plurality of adhesive areas are formed in the placing groove 3, then the aero-engine cover plate 2 is placed in the placing groove 3, and the connection between the aero-engine cover plate 2 and the base 1 is realized after the adhesive is solidified;

[0028] When the adhesive is applied, the adhesive can also form a linear track on the lower surface of the placement groove 3 or the aero-engine cover plate 2, and then the aero-engine cover plate 2 is placed in the placement groove 3, and the connection between the aero-engine cover plate 2 and the base 1 can also be formed after the adhesive is solidified, and at this time the connection strength between the two is higher, but correspondingly, the two are relatively troublesome to disassemble.

[0029] In order to facilitate the disassembly of the processed aero-engine cover plate 2, a horizontal center passage 5 is arranged on the above-mentioned base 1, and the center passage 5 is communicated with the placement groove 3 through a displacement passage 6, a slitting assembly is arranged in the displacement passage 6, and a driving member 7 is arranged in the center passage 5, the driving member 7 is connected with the slitting assembly, and when the driving member 7 moves in the center passage 5, the slitting assembly can be controlled to work, so that the adhesive in the bonding area is cut off, thereby facilitating the separation of the aero-engine cover plate 2 and the base 1;

[0030] The slitting assembly and the driving member 7 constitute a peeling mechanism, and the peeling mechanism has two implementation structures, and the specific structure is as follows:

[0031] The slitting assembly in the first peeling mechanism is a rotary slitting, that is, the slitting assembly at this time includes a rotating rod 8, the rotating rod 8 passes through the displacement passage, the displacement passage is a hole at this time, a tray 9 and a cap 10 are arranged on the rotating rod, the tray 9 is located in the center passage 5, and the cap 10 is located in the placement groove 3, so that the rotating rod 8 can be prevented from being separated from the displacement passage, a cutting piece 11 is fixed on the cap 10, the cutting piece 11 is arranged in an annular array around the central axis of the cap 10, when the rotating rod 8 rotates, the cutting piece 11 moves along the circumferential direction of the cap 10, and the cutting piece 11 cuts the adhesive in the bonding area in the movement process. When the rotating rod 8 is controlled to rotate, the driving member 7 is controlled, at this time the lower end of the rotating rod 8 is provided with a driving gear, and the driving gear is located in the center passage 5, and the driving member 7 is plate-shaped, the driving member 7 is provided with convex teeth arranged along the length direction of the driving member 7, and the convex teeth are engaged with the driving gear. Thus, when the driving member 7 is controlled to move in the center passage 5, the rotating rod 8 can be controlled to rotate, thereby driving the cutting piece 11 to move to realize the cutting of the adhesive, and this implementation structure is suitable for the case that the adhesive is a small area, that is, when the adhesive is applied, the adhesive should be applied on the moving track of the cutting piece;

[0032] The second peeling mechanism is a translation cutting, the cutting assembly includes a slider 12 which can translate, the displacement channel 6 is a long opening, the slider 12 is located in the displacement channel, the slider 12 is provided with a protruding part on the side vertical surface, and the displacement channel is provided with a sliding groove extending along the length direction, the protruding part on the slider 12 is located in the sliding groove, so that the slider 12 can move in the displacement channel, but the slider 12 cannot be removed from the displacement channel, the slider 12 can be directly connected with the driving member 7, or an intermediate piece 21 is used to connect the two, when the driving member 7 moves in the central channel 5, the slider 12 can be driven to move in the displacement channel, the cutting piece 11 is also connected with the slider 12, when the slider 12 moves, the cutting piece 11 moves along the moving track of the slider 12, and the area coated with the adhesive should be located on the moving track of the cutting piece 11, so that the adhesive can be cut by the cutting piece;

[0033] No matter which implementation structure is used for the peeling mechanism, in order to increase the stability of the aero-engine cover plate during processing, an inner support groove 13 is arranged in the placing groove 3 on the base 1, an inner support strip 14 is installed in the inner support groove 13, and a compression return spring 15 is connected between the inner support strip 14 and the bottom surface of the inner support groove 13, when the compression return spring 15 is in a normal state, the upper surface of the inner support strip 14 is located outside the inner support groove 13, at the same time, an extension plate 16 is arranged on the inner support strip 14, the extension plate 16 is integrally formed with the inner support strip 14, and both can enter the inner support groove 13, when the aero-engine cover plate 2 is placed in the placing groove 3, the upper surface of the inner support strip 14 contacts the position close to the edge of the aero-engine cover plate 2, which forms a certain support for the aero-engine cover plate 2, and at the same time, there is a gap between the upper surface of the extension plate 16 and the aero-engine cover plate 2, so the adhesive can be coated on the extension plate 16 before placing the aero-engine cover plate 2, and the adhesive has a certain thickness, until the adhesive can contact the aero-engine cover plate, so that the adhesive forms a glue connection after solidification;

[0034] When the aero-engine cover plate 2 is placed in the placing groove 3, the side edge of the aero-engine cover plate 2 is placed on the slider 12 or the cap 10, and the cutting piece 11 is located in the area between the extension plate 16 and the aero-engine cover plate 2, when the cutting piece 11 moves, the solidified adhesive can be cut, and with the movement of the cutting piece 11, the inner support strip 14 can move slightly downward, and during the cutting process of the adhesive, the aero-engine cover plate is not adversely affected.

[0035] In addition, the inner support bar in the application can be installed with an electric heating tube, the electric heating tube is connected with a power line, the power line passes through the base, when there is more adhesive, the inner support bar can be heated first, when the adhesive is softened to a certain degree, it is cut off by the slice, at this time, it is necessary to note that the base is provided with a reserved hole, the reserved hole extends from the side surface of the base to the inner support groove, the two ends of the electric heating tube are exposed from the lower surface of the inner support bar, and then the two ends are connected with the wire.

[0036] Finally, it needs to be pointed out that the specifications of the placing groove 3 on the base and the positions of the concave-convex parts in the application can be designed according to the needs, that is, different specifications of the base can be designed according to different specifications of the aero-engine cover plate, and different bases are rotated according to different needs in use.

[0037] When the base 1 is connected with the machining platform, the base 1 is provided with a pressing plate 17, the pressing plate 17 is provided with a through hole, then the bolt rod passes through the through hole on the pressing plate 17, the base 1 is connected with the machining platform, at the same time, a horizontal supporting plate 18 can also be arranged on one side of the base 1, the horizontal supporting plate 18 is vertically fixed with an end seat 19, the end seat 19 is provided with a horizontal threaded hole, the flat push lead screw 20 passes through the threaded hole, the flat push lead screw 20 moves axially when rotating, and the end of the flat push lead screw 20 is located in the center channel 5, at this time, the end of the flat push lead screw 20 is connected with the end of the driving part 7, for example, a slot is arranged at the end of the driving part 7, the end of the flat push lead screw 20 is provided with an anti-dropping disc, the anti-dropping disc is located in the slot, at this time, a bearing is sleeved on the end of the flat push lead screw 20, then a cover is butted at the end position of the driving part 7, after the cover is locked with the driving part 7, the end of the flat push lead screw 20 cannot be pulled out of the slot, but the flat push lead screw 20 can rotate at this time, so that the flat push lead screw 20 is controlled to rotate to control the driving part 7 to move in the center channel 5.

[0038] In the description of the application, it needs to be pointed out that, unless otherwise specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected; it can be electrically connected; it can be connected by hydraulic oil circuit; it can be directly connected, or indirectly connected through an intermediate medium; it can be the communication inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0039] The above merely describes a specific implementation of the present application, but the protection scope of the present application is not limited thereto, any skilled person in the art can easily think of changes or substitutions within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be mainly based on the protection scope of the claims.

Claims

1. A deformation-preventing fixture for machining aircraft engine cover plates, comprising a base with a placement groove, wherein the aircraft engine cover plate to be machined can be placed in the placement groove, characterized in that: The profile shape of the placing groove is matched with the profile shape of the to-be-processed aero-engine cover plate. The concave-convex part is arranged in the placing groove, and the concave-convex structure of the to-be-processed aero-engine cover plate is supported from inside. The to-be-processed aero-engine cover plate is connected with the bottom surface of the placing groove through the adhesive, the cutting assembly is arranged in the placing groove, and the adhesive can be cut.

2. The anti-deformation fixture for processing the cover plate of an aero-engine according to claim 1, characterized in that: The cutting assembly is connected with the driving member, the driving member is located in the central channel, the central channel is arranged on the base and the central channel horizontally penetrates the base.

3. The anti-deformation fixture for processing the cover plate of an aero-engine according to claim 2, characterized in that: The cutting assembly comprises a rotating rod, a cap is arranged on the rotating rod, a cutting piece is arranged on the cap, the rotating rod drives the cutting piece to move when the rotating rod rotates, and the adhesive is located on the moving track of the cutting piece.

4. The anti-deformation fixture for processing the cover plate of an aero-engine according to claim 3, characterized in that: The lower end of the rotating rod is provided with a driving gear, the driving gear is engaged with the driving member, and the driving member drives the rotating rod to rotate when the driving member moves in the central channel.

5. The anti-deformation fixture for processing the cover plate of an aero-engine according to claim 2, characterized in that: The cutting assembly comprises a sliding block, the sliding block is connected with the driving member, the cutting piece is connected on the sliding block, and the driving member drives the sliding block to translate in the placing groove.

6. The anti-deformation fixture for processing the cover plate of an aero-engine according to claim 1, characterized in that: The placing groove is provided with an inner supporting groove, and an inner supporting strip is arranged in the inner supporting groove; when the to-be-processed aero-engine cover plate is placed in the placing groove, the upper surface of the inner supporting strip is in contact with the position close to the edge of the aero-engine cover plate.

7. The anti-deformation fixture for processing an aero-engine cover plate according to claim 6, characterized in that: The outer extension plate is arranged on the inner supporting strip, there is a spacing between the upper surface of the outer extension plate and the to-be-processed aero-engine cover plate, and the adhesive is applied on the outer extension plate.

8. The anti-deformation fixture for processing an aero-engine cover plate according to claim 7, characterized in that: The compression return spring is connected between the inner supporting strip and the bottom surface of the inner supporting groove, and the inner supporting strip and the outer extension plate can enter the inner supporting groove.

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