CN219685074U - Aeroengine blade polishing clamp - Google Patents

Abstract

The utility model relates to an aeroengine blade polishing clamp which is used for clamping an aeroengine blade to be polished with high stability and high precision, and comprises a clamp body, an end face positioning block, a rotary pressing plate, a sliding block, a wedge shaft and an adjusting nut; the front end of the clamp body is slidingly arranged in the clamp body along the edge plate groove and the tenon root groove, and after the assembly, the vertical axis of the clamp body is overlapped with the blade stacking shaft of the aero-engine blade; the end face positioning block is fixedly connected to the rear end face of the clamp body, and the rear end faces of the flange plate and the tenon root are completely shielded; the rotary pressing plate is rotatably arranged on the front end face of the clamp body by taking the inclined wedge shaft as a rotary shaft, and the front end faces of the flange plate and the tenon root are completely shielded; when the wedge shaft gradually moves forwards along the longitudinal axis direction of the clamp body, the wedge surface gradually contacts with the inclined top wall until the wedge surface and the inclined top wall completely coincide, so that the top end surface of the sliding block contacts with the tenon root bottom surface of the aero-engine blade and compresses the aero-engine blade.

Description

Aeroengine blade polishing clamp

Technical Field

The utility model relates to an aero-engine blade polishing clamp, in particular to a vibration damping clamp capable of being rapidly clamped and used for polishing the blade body profile of an aero-engine rotor blade, and belongs to the technical field of aero-engine blade processing.

Background

The blade is used as a key part, plays an important role in the aero-engine, and the processing quality of the blade directly influences the overall performance of the aero-engine. The number of blades in the aero-engine is large, the precision requirement is high, the machining in multiple steps is needed, and the installation convenience, the positioning precision and the machining reference transmission precision of the clamp are very important.

The surface integrity of the aero-engine blade has important significance for the fatigue life of the blade and the performance of the engine. When the blade body is polished, the blade body is fixed through the tenons, and a processing coordinate system is set according to the reference surface of the blade, and the processing coordinate system is usually established through the clamp due to the small area of the tenons. At present, the problems of poor positioning stability and low clamping efficiency exist in the clamping of the blade, and the polishing quality is obviously affected by vibration because the suspension part is longer during the processing of the blade. Therefore, the blade polishing clamp has the advantages of ensuring necessary clamping precision, having good clamping stability, being simple to operate and having certain vibration reduction capability in the design of the blade polishing clamp.

Disclosure of Invention

Aiming at the technical problems, the utility model aims to provide an aero-engine blade polishing clamp which solves the problems of large clamping workload, low positioning accuracy and blade processing vibration in the existing aero-engine blade mass production.

In order to achieve the above object, the present utility model provides the following technical solutions:

1. an aero-engine blade polishing clamp for clamping an aero-engine blade 13 to be polished with high stability and high precision is characterized by comprising a clamp body 1, an end surface positioning block 2, a rotary pressing plate 3, a sliding block 4, a wedge shaft 5 and an adjusting nut 10;

the fixture body 1 is provided with a flange plate groove 101 and a tenon root groove 102 for accommodating a flange plate 1302 and a tenon root 1303 of an aero-engine blade 13; the part between the edge plate groove 101 and the tenon root groove 102 of the clamp body 1, which is contacted with the left side and the right side of the tenon root 1303 of the aero-engine blade 13, is a positioning part 103; the positioning parts 103 on the left and right sides are provided with a left positioning surface A and a right positioning surface B which are completely matched with the left and right tenon wedge-shaped surfaces 1305 of the tenon 1303; the front end of the aero-engine blade 13 is slidingly arranged in the clamp body 1 along the edge plate groove 101 and the tenon root groove 102, and after the assembly, the vertical axis Z of the clamp body 1 is overlapped with the blade stacking shaft of the aero-engine blade 13; the front end face of the fixture body 1 is positioned on the same vertical plane with the front end faces of the flange plate 1302 and the tenon root 1303; the rear end face H of the clamp body 1 is positioned on the same vertical plane with the rear end faces of the flange plate 1302 and the tenon root 1303;

the end face positioning block 2 is fixedly connected to the rear end face H of the clamp body 1 through a bolt 12, and the rear end faces of the flange plate 1302 and the tenon root 1303 are completely shielded;

the bottom center of the clamp body 1 is provided with a sliding groove 104 for accommodating the sliding block 4 along a vertical axis Z thereof, and the sliding groove 104 is communicated with the tenon root groove 102; the sliding block 4 is inserted into the sliding groove 104 from the bottom of the clamp body 1, and a cavity 401 is formed in the middle of the sliding block 4 along the direction of the longitudinal axis X of the clamp body 1; the wedge shaft 5 is an optical axis, and a wedge block 501 is arranged at the rear part of the wedge shaft; the wedge shaft 5 passes through the cavity 401 of the sliding block 4 and the front end surface of the clamp body 1 along the direction of the longitudinal axis X of the clamp body 1, and the wedge shaft 5 can move back and forth along the direction of the longitudinal axis X of the clamp body 1; the top of the wedge 501 is a wedge surface 502, and the cavity 401 has an inclined top wall 402 corresponding to the wedge surface 502 of the wedge 501; when the wedge shaft 5 gradually moves forward along the direction of the longitudinal axis X of the fixture body 1, the wedge surface 502 gradually contacts the inclined top wall 402 until the wedge surface is completely overlapped, so that the top end surface D of the sliding block 4 contacts the tenon root surface 1304 of the aero-engine blade 13 and compresses the aero-engine blade 13;

the rotary pressing plate 3 is rotatably arranged on the front end face of the clamp body 1 by taking the wedge shaft 5 as a rotary shaft, and completely shields the front end faces of the flange plate 1302 and the tenon root 1303; the adjusting nut 10 is connected with the front end of the inclined wedge shaft 5 through a threaded structure, and the inclined wedge shaft 5 is displaced along the X direction of the longitudinal axis of the clamp body 1 and the loosening and fastening of the rotating pressing plate 3 and the clamp body 1 are realized by rotating the adjusting nut 10.

A spacing cavity 105 is arranged above the sliding groove 104 of the clamp body 1, and the spacing cavity 105 divides the positioning parts 103 at two sides of the clamp body 1 into four positioning bosses, so that the middle part of the positioning part 103 of the clamp body 1 is not provided with a positioning surface contacted with the dovetail wedge-shaped surface 1305.

The upper curved surface of the fixture body 1, the upper curved surface of the end surface positioning block 2 and the upper curved surface of the rotating pressing plate 3 are all positioned in an extension surface of the upper surface of the flange plate 1302 of the aero-engine blade 13; after the clamp is assembled, the cross sections of the clamp body 1, the end face positioning block 2 and the rotary pressing plate 3 are round.

The rotating pressing plate 3 is provided with a steel ball positioning column 7, and is used for limiting the rotating pressing plate 3 at a preset position after the fixture body 1 clamps the aero-engine blade 13, wherein the preset position is that the rotating pressing plate 3 completely shields the front end surfaces of the flange plate 1302 and the tenon root 1303, and the upper curved surface of the rotating pressing plate 3 is positioned in the extension surface of the upper surface of the flange plate 1302 of the aero-engine blade 13; the steel ball positioning column 7 is a cylindrical tube with a built-in spring and a steel ball, the steel ball partially protrudes out of one end of the cylindrical tube, and the steel ball can retract into the cylindrical tube but is not separated from the cylindrical tube; the front end face of the clamp body 1 is provided with a positioning pit corresponding to the steel ball positioning column 7, and when the steel balls of the steel ball positioning column 7 fall into the positioning pit, the rotary pressing plate 3 is positioned at a preset position.

The outside of slider 4 is equipped with reset spring 9, reset spring 9 cooperates with the top step of spout 104 and the bottom step of slider 4, realizes slider 4 automatic re-setting.

A gasket 8 is arranged between the top end surface D of the slider 4 and the tenon root bottom surface 1304 of the aero-engine blade 13.

Vibration damping strips 6 which are in contact with left and right flange end surfaces 1306 of the flange 1302 are arranged on the left and right sides of the flange groove 101 of the clamp body 1.

The wedge surface 502 of the wedge 501 is a semi-cylindrical convex surface, and the sloped top wall 402 of the cavity 401 is a semi-cylindrical concave surface.

The wedge surface 502 of the wedge 501 and the inclined top wall 402 of the cavity 401 are at an angle of 7 ° to the horizontal.

The bottom plane G of the clamp body 1 is parallel to a blade datum plane of the aero-engine blade 13, and is provided with a positioning hole and a threaded connection hole for positioning and connecting with processing equipment.

Compared with the prior art, the utility model has the beneficial effects that:

according to the utility model, by positioning the wedge-shaped surfaces on two sides of the blade tenon and the tenon end surfaces, the positioning tenon groove is of an intermittent structure, so that the positioning stability is high, and the positioning stability is superior to that of two continuous positioning surfaces. The fixture body is provided with a machining reference which is coincident with the blade coordinate system, so that the machining coordinate system is convenient to establish. The clamp is clamped and loosened by only operating one nut, and the blade is high in dismounting efficiency.

According to the utility model, the blade is damped by the damping strip contacted with the blade edge plate and the gasket arranged between the top end surface of the sliding block and the tenon root bottom surface of the aero-engine blade, so that the processing quality is improved, and the method has important significance for high-precision processing and mass production of the blade.

Drawings

FIG. 1 is a schematic structural view of an aircraft engine blade 13;

FIG. 2 is a schematic exploded view of the aero-engine blade burnishing jig of the present utility model;

FIG. 3 is a schematic side view of the aero-engine blade burnishing jig of the present utility model;

FIG. 4 is a schematic diagram of a front view of an aircraft engine blade burnishing jig of the present utility model;

FIG. 5 is a schematic rear view of the aero-engine blade burnishing jig of the present utility model;

FIG. 6 is a schematic top view of the aero-engine blade burnishing jig of the present utility model;

FIG. 7 is a schematic bottom view of the aircraft engine blade polishing fixture of the present utility model;

fig. 8a is a schematic diagram of the front view structure of the fixture body 1;

FIG. 8b is a schematic top view of the clip body 1;

FIG. 8c is a schematic view of the E-direction structure of FIG. 8 b;

fig. 9a is a schematic cross-sectional view of the slider 4;

fig. 9b is a schematic front view of wedge shaft 5;

FIG. 10a is a cross-sectional view taken along line A-A of FIG. 4;

FIG. 10b is an enlarged view of region I of FIG. 10 a;

FIG. 11a is a cross-sectional view taken along the direction B-B of FIG. 6;

FIG. 11b is an enlarged view of region II of FIG. 11 a;

FIG. 12a is a cross-sectional view taken along the direction C-C of FIG. 6;

FIG. 12b is an enlarged view of area III of FIG. 12 a;

FIG. 13a is a cross-sectional view taken along direction D-D of FIG. 6;

fig. 13b is an enlarged view of area IV in fig. 13 a;

fig. 14a and 14b are schematic views of the clamping of an aero-engine blade 13 by the clamp according to the utility model.

Wherein the reference numerals are as follows:

1. clamp body 101 and flange plate groove

102. Tenon root groove 103 and positioning part

104. Chute 105, spacer cavity

X, longitudinal axis Y, transverse axis

Z and vertical axis

2. End face positioning block

3. Rotary pressing plate

4. Slider 401, cavity

402. Inclined top wall

5. Wedge shaft 501 and wedge block

502. Wedge surface

6. Vibration damping strip 7 and steel ball positioning column

8. Gasket 9, return spring

10. Adjusting nut 11, screw

12. Bolt 13 and aeroengine blade

1301. Blade body 1302 and edge plate

1303. Tenon 1304, tenon bottom surface

1305. Tenon wedge-shaped surface 1306 and edge plate end surface

Detailed Description

The utility model will be further described with reference to the drawings and examples.

The structure of the aero-engine blade 13 is shown in fig. 1, and the aero-engine blade 13 comprises a blade body 1301, a flange 1302 and a tenon root 1303; wherein the platform 1302 has left and right platform end surfaces 1306; tenon 1303 has a tenon bottom face 1304 and left and right tenon wedge faces 1305; the front end surfaces of the flange 1302 and the tenon 1303 are located in the same vertical plane, and the rear end surfaces of the flange 1302 and the tenon 1303 are located in the same vertical plane.

As shown in fig. 2, 3, 4, 5, 6 and 7, the present utility model provides an aero-engine blade polishing jig for clamping aero-engine blades 13 to be polished with high stability and high precision, the jig comprising a jig body 1, an end face positioning block 2, a rotating pressing plate 3, a slider 4, a cam shaft 5 and an adjusting nut 10.

As shown in fig. 8a, 8b and 8c, the fixture body 1 is provided with a flange groove 101 and a dovetail groove 102 for accommodating a flange 1302 and a dovetail 1303 of an aero-engine blade 13; the part between the edge plate groove 101 and the tenon root groove 102 of the clamp body 1, which is contacted with the left side and the right side of the tenon root 1303 of the aero-engine blade 13, is a positioning part 103; the positioning portions 103 on the left and right sides have left and right positioning surfaces a and B (see fig. 11a, 11B, 12a, and 12B) that completely coincide with the left and right dovetail wedge-shaped surfaces 1305 of the dovetail 1303; the front end of the aero-engine blade 13 is slidingly arranged in the clamp body 1 along the edge plate groove 101 and the tenon root groove 102, and after the assembly, the vertical axis Z of the clamp body 1 is overlapped with the blade stacking shaft of the aero-engine blade 13; as shown in fig. 10a, the front end surface of the fixture body 1 and the front end surfaces of the flange plate 1302 and the tenon root 1303 are located on the same vertical plane. The rear end face H of the fixture body 1 and the rear end faces of the flange plate 1302 and the tenon root 1303 are positioned on the same vertical plane.

As shown in fig. 5, the end surface positioning block 2 is fixedly connected to the rear end surface H of the fixture body 1 through a bolt 12, so that the rear end surfaces of the flange plate 1302 and the tenon root 1303 are completely shielded; the contact surface of the end surface positioning block 2 and the rear end surface H of the clamp body 1 is an end surface positioning surface C.

As shown in fig. 2 and 7, a sliding groove 104 for accommodating the sliding block 4 is arranged at the bottom center of the clamp body 1 along the vertical axis Z, and the sliding groove 104 is communicated with the tenon root groove 102; the sliding block 4 is inserted into the sliding groove 104 from the bottom of the clamp body 1, and a cavity 401 is formed in the middle of the sliding block 4 along the direction of the longitudinal axis X of the clamp body 1; the wedge shaft 5 is an optical axis, and a wedge block 501 is arranged at the rear part of the wedge shaft; the cam shaft 5 passes through the cavity 401 of the slider 4 and the front end surface of the clamp body 1 along the longitudinal axis X direction of the clamp body 1, and the cam shaft 5 can move back and forth along the longitudinal axis X direction of the clamp body 1. As shown in fig. 9a and 9b, the top of the wedge 501 is a wedge surface 502, and the cavity 401 has an inclined top wall 402 corresponding to the wedge surface 502 of the wedge 501; as the cam shaft 5 moves progressively forward along the longitudinal axis X of the clamp body 1, the wedge surface 502 comes into contact with the inclined top wall 402 until it fully coincides such that the tip end face D of the slider 4 comes into contact with the dovetail bottom face 1304 of the aero-engine blade 13 and compresses the aero-engine blade 13.

As shown in fig. 3 and fig. 4, the rotating pressing plate 3 is rotatably arranged on the front end surface of the fixture body 1 by taking the wedge shaft 5 as a rotating shaft, so that the front end surfaces of the flange plate 1302 and the tenon root 1303 are completely shielded; the contact surface of the rotary pressing plate 3 and the front end surface of the clamp body 1 is a pressing plate positioning surface E; the adjusting nut 10 is connected with the front end of the inclined wedge shaft 5 through a threaded structure, and the inclined wedge shaft 5 is displaced along the X direction of the longitudinal axis of the clamp body 1 and the loosening and fastening of the rotating pressing plate 3 and the clamp body 1 are realized by rotating the adjusting nut 10.

As shown in fig. 2, 13a and 13b, preferably, a space 105 is provided above the chute 104 of the fixture body 1, and the space 105 divides the positioning portions 103 at two sides of the fixture body 1 into four positioning bosses, so that the middle portion of the positioning portion 103 of the fixture body 1 has no positioning surface contacting with the dovetail wedge-shaped surface 1305. The optimal state of the positioning structure is point contact, and the farther the distance is, the better the positioning structure is. The larger the positioning surface is, the more disadvantageous the positioning accuracy and stability are. The dovetail wedge-shaped surface 1305 of the aero-engine blade 13 cannot completely eliminate errors in actual machining, and the spacer cavity 105 is beneficial to improving positioning stability according to the lever principle while reducing the area of a positioning surface, so that the polishing precision of the blade is ensured.

As shown in fig. 3 and 4, preferably, the upper curved surface of the fixture body 1, the upper curved surface of the end surface positioning block 2, and the upper curved surface of the rotating pressing plate 3 are all located in an extension plane of the upper surface of the flange plate 1302 of the aero-engine blade 13, so as to avoid interference during processing.

As shown in fig. 6 and 7, preferably, after the jig is assembled, the cross sections of the jig body 1, the end face positioning block 2 and the rotating pressing plate 3 are circular, so that the jig has a cylindrical curved surface F.

As shown in fig. 10b, preferably, the rotating pressing plate 3 is provided with a steel ball positioning column 7, which is used for limiting the rotating pressing plate 3 to a preset position after the fixture body 1 clamps the aero-engine blade 13, wherein the preset position is that the rotating pressing plate 3 completely shields the front end surfaces of the flange plate 1302 and the tenon root 1303, and the upper curved surface of the rotating pressing plate 3 is located in the extension surface of the upper surface of the flange plate 1302 of the aero-engine blade 13; the steel ball positioning column 7 is a cylindrical tube with a built-in spring and a steel ball, the steel ball partially protrudes out of one end of the cylindrical tube, and the steel ball can retract into the cylindrical tube but is not separated from the cylindrical tube; the front end face of the clamp body 1 is provided with a positioning pit corresponding to the steel ball positioning column 7, and when the steel balls of the steel ball positioning column 7 fall into the positioning pit, the rotary pressing plate 3 is positioned at a preset position.

As shown in fig. 2 and 10a, preferably, a return spring 9 is disposed on the outer side of the sliding block 4, and the return spring 9 is matched with a top step of the sliding groove 104 and a bottom step of the sliding block 4 to realize automatic return of the sliding block 4.

As shown in fig. 2 and 11a, preferably, a gasket 8 is arranged between the top end surface D of the slider 4 and the tenon root base surface 1304 of the aero-engine blade 13, so as to provide vertical vibration reduction for the tenon root base surface; the pad 8 is fixed to the tip surface D of the slider 4 by a screw 11.

Preferably, the gasket 8 is made of polytetrafluoroethylene, and the polytetrafluoroethylene material can play a certain role in vibration reduction, and meanwhile, the sliding block 4 is prevented from damaging the tenon bottom surface 1304 by pressing.

As shown in fig. 2, 11a, 12a and 13a, preferably, the left and right sides of the flange groove 101 of the clamp body 1 are provided with vibration damping strips 6 contacting the left and right flange end surfaces 1306 of the flange 1302.

Preferably, the vibration absorbing strip 6 is made of nitrile rubber, and the nitrile rubber can effectively inhibit vibration in processing as a damping material.

As shown in fig. 2 and 10a, the wedge surface 502 of the wedge 501 is preferably a semi-cylindrical convex surface, and the inclined top wall 402 of the cavity 401 is preferably a semi-cylindrical concave surface.

Preferably, wedge surface 502 of wedge 501 and sloped top wall 402 of cavity 401 are at an angle of 7 ° to the horizontal.

As shown in fig. 3 and 7, the bottom plane G of the clamp body 1 is parallel to the blade reference plane of the aero-engine blade 13 and is provided with positioning holes and threaded connection holes for positioning and connecting with machining equipment.

The working engineering of the utility model is as follows:

firstly, the aeroengine blade polishing clamp is arranged on processing equipment, so that the distance between a Z axis of a machine tool coordinate system and a vertical axis Z of the clamp body 1 is ensured to be L, the distance between an XY plane of the machine tool coordinate system and a bottom plane G of the clamp body 1, and the distance between a YZ plane of the machine tool coordinate system and a rear end face H of the clamp body 1 is ensured to be M. And the positioning hole and the threaded connecting hole of the bottom plane G of the clamp body 1 are connected and fixed with a machine tool.

Then, the aero-engine blade 13 is clamped to the aero-engine blade polishing jig of the present utility model, the blade is positioned by the left positioning surface a and the right positioning surface B and the end surface positioning surface C, and the blade is clamped by the tip surface D of the slider 4 and the platen positioning surface E, as shown in fig. 14a, 14B: the rotary pressing plate 3 is loosened by rotating the adjusting nut 10, the edge plate groove 101 and the tenon root groove 102 of the clamp body 1 can be exposed after the rotary pressing plate 3 rotates for a certain angle, and after the aero-engine blade 13 is installed into the clamp body 1 in a sliding manner, the rotary pressing plate 3 is reset; the adjusting nut 10 is rotated to fasten the rotating pressing plate 3 and the clamp body 1, and simultaneously drives the inclined wedge shaft 5 to move forwards along the direction of the longitudinal axis X of the clamp body 1, the wedge surface 502 is gradually contacted with the inclined top wall 402 until the wedge surface is completely overlapped, so that the top end surface of the sliding block 4 is contacted with the tenon root bottom surface 1304 of the aero-engine blade 13 and compresses the aero-engine blade 13, and after the assembly is completed, the coordinate system of the aero-engine blade 13 is overlapped with the machine tool machining coordinate system.

Claims (10)

1. The aero-engine blade polishing clamp is used for clamping an aero-engine blade (13) to be polished with high stability and high precision and is characterized by comprising a clamp body (1), an end surface positioning block (2), a rotary pressing plate (3), a sliding block (4), a wedge shaft (5) and an adjusting nut (10);

the fixture body (1) is provided with a flange plate groove (101) and a tenon root groove (102) for accommodating a flange plate (1302) and a tenon root (1303) of an aero-engine blade (13); the part between the edge plate groove (101) and the tenon root groove (102) of the clamp body (1) contacted with the left side and the right side of the tenon root (1303) of the aero-engine blade (13) is a positioning part (103); the positioning parts (103) on the left side and the right side are provided with a left positioning surface and a right positioning surface which are completely matched with the left tenon wedge-shaped surface (1305) and the right tenon wedge-shaped surface (1305) of the tenon (1303); the front end of the aero-engine blade (13) is slidingly arranged in the clamp body (1) along the edge plate groove (101) and the tenon root groove (102), and after the assembly, the vertical axis Z of the clamp body (1) is overlapped with the blade stacking shaft of the aero-engine blade (13); the front end face of the clamp body (1) is positioned on the same vertical plane with the front end faces of the edge plate (1302) and the tenon root (1303); the rear end face of the clamp body (1) is positioned on the same vertical plane with the rear end faces of the flange plate (1302) and the tenon root (1303);

the end face positioning block (2) is fixedly connected to the rear end face of the clamp body (1) through a bolt (12), and the rear end faces of the flange plate (1302) and the tenon root (1303) are completely shielded;

the bottom center of the clamp body (1) is provided with a sliding groove (104) for accommodating the sliding block (4) along a vertical axis Z thereof, and the sliding groove (104) is communicated with the tenon root groove (102); the sliding block (4) is inserted into the sliding groove (104) from the bottom of the clamp body (1), and a cavity (401) is formed in the middle of the sliding block (4) along the X direction of the longitudinal axis of the clamp body (1); the inclined wedge shaft (5) is an optical axis, and a wedge block (501) is arranged at the rear part of the inclined wedge shaft; the wedge shaft (5) passes through the cavity (401) of the sliding block (4) and the front end surface of the clamp body (1) along the longitudinal axis X direction of the clamp body (1), and the wedge shaft (5) can move back and forth along the longitudinal axis X direction of the clamp body (1); the top of the wedge block (501) is provided with a wedge surface (502), and the cavity (401) is provided with an inclined top wall (402) corresponding to the wedge surface (502) of the wedge block (501); when the wedge shaft (5) gradually moves forwards along the direction of the longitudinal axis X of the clamp body (1), the wedge surface (502) gradually contacts with the inclined top wall (402) until the wedge surface and the inclined top wall completely coincide, so that the top end surface of the sliding block (4) contacts with the tenon root bottom surface (1304) of the aero-engine blade (13) and compresses the aero-engine blade (13);

the rotary pressing plate (3) is rotatably arranged on the front end face of the clamp body (1) by taking the inclined wedge shaft (5) as a rotary shaft, and the front end faces of the flange plate (1302) and the tenon root (1303) are completely shielded; the adjusting nut (10) is connected with the front end of the inclined wedge shaft (5) through a threaded structure, and the inclined wedge shaft (5) is displaced along the X direction of the longitudinal axis of the clamp body (1) and the clamp body (1) is loosened and fastened by rotating the adjusting nut (10).

2. Aeroengine blade burnishing jig according to claim 1, characterized in that a spacer (105) is arranged above the runner (104) of the jig body (1), the spacer (105) dividing the positioning portions (103) on both sides of the jig body (1) into four positioning bosses, which makes the middle part of the positioning portion (103) of the jig body (1) free of positioning surfaces in contact with the dovetail wedge-shaped surfaces (1305).

3. The aircraft engine blade polishing clamp according to claim 1, wherein the upper curved surface of the clamp body (1), the upper curved surface of the end surface positioning block (2) and the upper curved surface of the rotating pressing plate (3) are all located in an extension plane of the upper surface of the flange plate (1302) of the aircraft engine blade (13); after the clamp is assembled, the cross sections of the clamp body (1), the end face positioning block (2) and the rotary pressing plate (3) are round.

4. The aircraft engine blade polishing clamp according to claim 1, wherein the rotating pressing plate (3) is provided with a steel ball positioning column (7) for limiting the rotating pressing plate (3) to a preset position after the clamp body (1) clamps the aircraft engine blade (13), the preset position is that the rotating pressing plate (3) completely shields the front end surfaces of the flange plate (1302) and the tenon root (1303), and an upper curved surface of the rotating pressing plate (3) is positioned in an extension surface of the upper surface of the flange plate (1302) of the aircraft engine blade (13); the steel ball positioning column (7) is a cylindrical tube with a built-in spring and a steel ball, the steel ball partially protrudes out of one end of the cylindrical tube, and the steel ball can retract into the cylindrical tube but is not separated from the cylindrical tube; the front end face of the clamp body (1) is provided with a positioning pit corresponding to the steel ball positioning column (7), and when the steel balls of the steel ball positioning column (7) fall into the positioning pit, the rotary pressing plate (3) is positioned at a preset position.

5. The aeroengine blade polishing clamp according to claim 1, wherein a return spring (9) is arranged on the outer side of the sliding block (4), and the return spring (9) is matched with a top step of the sliding groove (104) and a bottom step of the sliding block (4) to realize automatic return of the sliding block (4).

6. Aero-engine blade burnishing jig according to claim 1, wherein a shim (8) is provided between the top end face of the slider (4) and the dovetail bottom face (1304) of the aero-engine blade (13).

7. Aeroengine blade burnishing jig according to claim 1, wherein the left and right sides of the flange plate groove (101) of the jig body (1) are provided with vibration damping strips (6) in contact with the left and right flange plate end faces (1306) of the flange plate (1302).

8. Aeroengine blade burnishing jig according to claim 1, wherein the wedge surface (502) of the wedge block (501) is a semi-cylindrical convex surface and the inclined top wall (402) of the cavity (401) is a semi-cylindrical concave surface.

9. Aeroengine blade burnishing jig according to claim 1, wherein the wedge surface (502) of the wedge block (501) and the inclined top wall (402) of the cavity (401) are at an angle of 7 ° to the horizontal.

10. Aeroengine blade burnishing jig according to claim 1, wherein the bottom plane of the jig body (1) is parallel to the blade datum plane of the aeroengine blade (13) and provided with locating holes and threaded connection holes for locating and connecting with machining equipment.