Aircraft engine blade machining clamp

Abstract

The utility model discloses an aircraft engine blade processing clamp, which relates to the technical field of aircraft part processing, and comprises an operation panel, the upper side of the operation panel is fixedly connected with a plurality of groups of transversely arranged fixing plates, the upper side of each fixing plate is fixedly connected with a rubber plate, and one end of each fixing plate is rotatably connected with a bridle. A mounting plate is fixedly connected to the tail end of the driving motor, a second screw hole is formed outside the mounting plate, a mounting groove is formed in the upper side of the operating plate, a sliding plate is slidably connected to the interior of the fixing plate, a reset mechanism is mounted at the bottom of the sliding plate, a connecting seat is fixedly connected to the upper side of the sliding plate, and a first screw hole is formed outside the connecting seat; a tightening mechanism is mounted on the inner side of the mounting groove. According to the device, through linkage tightening of the elastic rubber plate and the flexible bridle, self-adaption to the curvature change of the curved surface of the blade and bidirectional uniform pressure applying are achieved, the driving motor automatically controls tightness and resetting, rapid dismounting is achieved, the machining stability and the attaching precision are ensured, and the blade clamping efficiency and the surface adaptability are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft part processing technical field, specifically, relate to a kind of aircraft engine blade processing fixture. BACKGROUND

[0002] Aircraft engine blade is the core component of aero-engine, and its complex curved surface structure requires high machining precision and clamping stability. Traditional machining fixture adopts rigid clamping mode, directly fixes the blade through bolt or jaw, which is difficult to adapt to the local deformation of blade surface, and easily leads to uneven clamping contact surface, even causes blade deformation or surface damage. In addition, the manual adjustment of clamping force is inefficient, and the pressure distribution cannot be accurately controlled. When disassembling, it needs to be gradually loosened, which is time-consuming and labor-consuming. When dealing with high-precision machining requirements, this kind of fixture often affects the processing quality due to insufficient fit, and it is difficult to meet the high standard requirements of modern aviation manufacturing.

[0003] To solve the above problems, the prior art tries to use elastic gasket or split clamping structure, such as adding rubber layer or segmented pressing plate on the clamping surface. However, this kind of improved scheme still has limitations. The elastic gasket can only buffer the contact stress in one direction, and cannot actively adapt to the change of blade curvature. Although the split structure improves the local fit, it has poor overall linkage, which leads to dispersion of clamping force. At the same time, most of the fixtures rely on manual operation, lack of automatic tightening and resetting mechanism, and the clamping efficiency is limited. With the increasing complexity of blade design, the shortcomings of traditional method in adaptive fit, quick assembly and disassembly and pressure uniformity are more and more prominent. Therefore, aiming at the above technical problems, a kind of aircraft engine blade processing fixture is proposed. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a kind of aircraft engine blade processing fixture, which is automatically controlled by elastic rubber plate and flexible belt linkage tightening, self-adapting blade surface curvature change and bidirectional uniform pressure, driving motor automatic control loose and reset, realizing quick disassembly, ensuring processing stability and fit precision, improving blade clamping efficiency and surface adaptability.

[0005] The utility model realizes the following technical scheme:

[0006] An aircraft engine blade processing clamp, including an operation plate, the upper side of the operation plate is fixedly connected with a plurality of groups of transversely arranged fixed plates, the upper side of the fixed plate is fixedly connected with a rubber plate, one end of the fixed plate is rotatably connected with a belt, the end of the driving motor is fixedly connected with a mounting plate, the outer portion of the mounting plate is provided with a second screw hole, the upper side of the operation plate is provided with a mounting groove, and the position of the mounting groove is matched with the fixed plate, the inner portion of the fixed plate is slidably connected with a sliding plate, the bottom of the sliding plate is provided with a reset mechanism, the upper side of the sliding plate is fixedly connected with a connecting seat, the outer portion of the connecting seat is provided with a first screw hole, and the inner side of the mounting groove is provided with a tightening mechanism.

[0007] Preferably, the rubber plate is made of elastic plastic material.

[0008] Preferably, one end of the upper side of the fixed plate is fixedly connected with a connecting piece, the outer portion of the connecting piece is rotatably connected with a rotating sleeve, and the belt is fixedly connected to the outer portion of the rotating sleeve.

[0009] Preferably, the reset mechanism comprises a telescopic rod and a compression spring, the telescopic rod and the compression spring are fixedly connected between the inner bottom of the mounting groove and the lower side of the sliding plate, the number of the telescopic rod and the compression spring is two groups and is symmetrically arranged, and the compression spring is sleeved on the outer side of the telescopic rod.

[0010] Preferably, the inner side of the mounting groove is fixedly connected with a limiting plate, and the limiting plate is located above the sliding plate.

[0011] Preferably, the upper side of the connecting seat is provided with a slot, the slot is matched with the mounting plate, and the first screw hole is matched with the second screw hole.

[0012] Preferably, the tightening mechanism comprises a rotating shaft and a pull rope, the rotating shaft is rotatably connected to the inner portion of the mounting groove, the pull rope is fixedly connected to the outer portion of the rotating shaft, and the other end of the pull rope is fixedly connected to the lower side of the sliding plate.

[0013] Preferably, the outer portion of the operation plate is fixedly connected with a driving motor, and the rotating shaft is fixedly connected with the driving motor.

[0014] The technical scheme of the utility model has at least the following beneficial effects:

[0015] The utility model provides a kind of aircraft engine blade processing fixture, by the synergistic effect of elastic rubber plate and flexible band, self-adapting complex curved surface of blade, avoid the local stress concentration or deformation caused by traditional rigid clamping, ensure clamping uniformity, by drive motor drive tightening and reset, realize automatic tightness control, improve the efficiency of assembly and disassembly and reduce manual intervention, by bidirectional flexible pressure makes blade upper and lower surface simultaneously closely adhere, in combination with elastic support and flexible constraint, enhance processing stability, in addition reset mechanism cooperation quick release structure, simplify disassembly process, reduce operation time, its self-adapting curved surface characteristics significantly improve clamping precision, reduce processing error, especially applicable to the efficient processing demand of high-precision, high-curvature blade, give consideration to reliability and practicality. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is the overall structure schematic diagram of the utility model;

[0017] Figure 2 It is Figure 1 the enlarged view of A;

[0018] Figure 3 It is Figure 1 the enlarged view of B;

[0019] Figure 4 It is the side sectional view of the utility model;

[0020] Figure 5 It is Figure 4 the enlarged view of C;

[0021] Figure 6 It is Figure 4 the enlarged view of D;

[0022] Signs: 1, operating plate;2, fixed plate;3, rubber plate;4, connecting piece;5, rotating sleeve;6, band;7, installation groove;8, sliding plate;9, telescopic rod;10, compression spring;11, limit plate;12, connecting seat;13, first screw hole;14, mounting plate;15, second screw hole;16, drive motor;17, rotating shaft;18, pull rope. DETAILED DESCRIPTION

[0023] The technical scheme in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model, and obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the utility model.

[0024] Please refer to Figures 1-6The utility model provides a kind of aircraft engine blade processing fixture, including operation plate 1, the upper side of operation plate 1 is fixedly connected with multiple groups of transverse arrangement fixed plate 2, the upper side of fixed plate 2 is fixedly connected with rubber plate 3, one end of fixed plate 2 is rotatably connected with belt 6, the end of driving motor 16 is fixedly connected with mounting plate 14, second screw hole 15 is opened in the outside of mounting plate 14, the upper side of operation plate 1 is equipped with installation groove 7, and the position of installation groove 7 is matched between fixed plate 2, the inside of fixed plate 2 is slidably connected with slide 8, and reset mechanism is installed in the bottom of slide 8, the upper side of slide 8 is fixedly connected with connecting seat 12, first screw hole 13 is opened in the outside of connecting seat 12, and tightening mechanism is installed in the inside of installation groove 7.

[0025] Rubber plate 3 is made of elastic plastic material. Elastic plastic material can be deformed to fit the bottom surface of the blade, providing flexible support and avoiding scratching the surface.

[0026] The upper side of one end of fixed plate 2 is fixedly connected with connecting piece 4, rotating sleeve 5 is rotatably connected to the outside of connecting piece 4, and belt 6 is fixedly connected to the outside of rotating sleeve 5. Rotating sleeve 5 allows belt 6 to rotate flexibly with the angle of the blade surface, ensuring that the coverage range is adapted to different curvatures.

[0027] The reset mechanism includes telescopic rod 9 and compression spring 10, which are fixedly connected between the inside bottom of installation groove 7 and the lower side of slide 8, and the number of telescopic rod 9 and compression spring 10 is two groups and is symmetrically arranged, and compression spring 10 is sleeved on the outside of telescopic rod 9. Telescopic rod 9 and compression spring 10 cooperate to provide elastic reset force, maintaining the sliding stability of slide 8.

[0028] The inside of installation groove 7 is fixedly connected with limit plate 11, and limit plate 11 is above slide 8. Limit plate 11 can prevent slide 8 from moving too much, and constrain its travel range.

[0029] The upper side of connecting seat 12 is provided with a slot, and the slot is matched between mounting plate 14, and the first screw hole 13 is matched with the second screw hole 15. After the slot and the screw hole are aligned, they are fixed by bolts, realizing the quick locking of mounting plate 14 and connecting seat 12.

[0030] The tightening mechanism includes rotating shaft 17 and pull rope 18, rotating shaft 17 is rotatably connected to the inside of installation groove 7, pull rope 18 is fixedly connected to the outside of rotating shaft 17, and the other end of pull rope 18 is fixedly connected to the lower side of slide 8. Pull rope 18 rotates with rotating shaft 17, and is converted into linear displacement of slide 8 to drive belt 6 to tighten.

[0031] The outside of operation plate 1 is fixedly connected with driving motor 16, and rotating shaft 17 is fixedly connected with driving motor 16. Driving motor 16 can provide power for the rotation of rotating shaft 17.

[0032] The working principle of the aircraft engine blade machining clamp based on the embodiment is that first, the aircraft engine blade to be machined is laid on the surface of the rubber plate 3 above the fixed plate 2, the elastic property of the rubber plate 3 is utilized to form initial contact with the bottom surface of the blade, then the band 6 is covered on the surface of the blade through the rotation cooperation of the rotating sleeve 5 and the connecting piece 4, and the first screw hole 13 is aligned with the second screw hole 15 through the insertion of the mounting plate 14 into the slot above the connecting seat 12, the locking of the mounting plate 14 and the connecting seat 12 is completed through the fixed bolt penetrating the screw hole, after the driving motor 16 is started, the output end drives the rotating shaft 17 to rotate, the pull rope 18 is wound around the shaft, and then the sliding plate 8 is pulled down along the inside of the fixed plate 2, the extension rod 9 and the compression spring 10 in the reset mechanism are compressed synchronously during the downward movement of the sliding plate 8, and the band 6 is tightened through the displacement of the connecting seat 12, the band 6 applies uniform pressure to the upper surface of the blade under the constraint of the rotating sleeve 5, so that the blade is tightly attached to the elastic supporting surface of the rubber plate 3, in this process, the flexible tightening property of the band 6 and the elastic deformation of the rubber plate 3 cooperate to adapt to the curvature change of the curved surface of the blade, and the up-down double clamping is realized, when the machining is completed, the driving motor 16 is reversed to release the pull rope 18, the reset mechanism pushes the sliding plate 8 to reset, and the band 6 is automatically relaxed, so that the workpiece can be quickly disassembled, through the composite clamping mode of mechanical linkage and elastic contact, the stability of the blade clamping and the curved surface fitting precision are significantly improved, and the high-precision machining requirement is met.

[0033] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirits of the utility model, the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. A jig for machining aircraft engine blades, characterized in that: The device includes an operation panel (1), on which multiple sets of horizontally arranged fixing plates (2) are fixedly connected. A rubber plate (3) is fixedly connected to the upper side of the fixing plate (2). A strap (6) is rotatably connected to one end of the fixing plate (2). A drive motor (16) is fixedly connected to the outside of the operation panel (1). A mounting plate (14) is fixedly connected to the end of the drive motor (16). A second screw hole (15) is opened on the outside of the mounting plate (14). A mounting groove (7) is opened on the upper side of the operation panel (1), and the position of the mounting groove (7) matches that of the fixing plate (2). A sliding plate (8) is slidably connected inside the fixing plate (2). A reset mechanism is installed at the bottom of the sliding plate (8). A connecting seat (12) is fixedly connected to the upper side of the sliding plate (8). A first screw hole (13) is opened on the outside of the connecting seat (12). A tightening mechanism is installed on the inside of the mounting groove (7).

2. The aircraft engine blade machining fixture according to claim 1, characterized in that: The rubber sheet (3) is made of elastic plastic material.

3. The aircraft engine blade machining fixture according to claim 1, characterized in that: A connector (4) is fixedly connected to the upper side of one end of the fixed plate (2), and a rotating sleeve (5) is rotatably connected to the outside of the connector (4), and a strap (6) is fixedly connected to the outside of the rotating sleeve (5).

4. The aircraft engine blade machining fixture according to claim 1, characterized in that: The reset mechanism includes a telescopic rod (9) and a compression spring (10). The telescopic rod (9) and the compression spring (10) are fixedly connected between the bottom inner side of the mounting groove (7) and the bottom side of the slide plate (8). The telescopic rod (9) and the compression spring (10) are in two sets and arranged symmetrically. The compression spring (10) is sleeved on the outside of the telescopic rod (9).

5. The aircraft engine blade machining fixture according to claim 1, characterized in that: A limiting plate (11) is fixedly connected to the inner side of the mounting groove (7), and the limiting plate (11) is located above the sliding plate (8).

6. The aircraft engine blade machining fixture according to claim 1, characterized in that: The upper side of the connector (12) is provided with a slot, and the slot is matched with the mounting plate (14), and the first screw hole (13) is matched with the second screw hole (15).

7. The aircraft engine blade machining fixture according to claim 1, characterized in that: The tightening mechanism includes a rotating shaft (17) and a pull rope (18). The rotating shaft (17) is rotatably connected to the inside of the mounting groove (7), and the pull rope (18) is fixedly connected to the outside of the rotating shaft (17). The other end of the pull rope (18) is fixedly connected to the lower side of the slide plate (8).

8. The aircraft engine blade machining fixture according to claim 7, characterized in that: The rotating shaft (17) and the drive motor (16) are fixedly connected.

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