Clamping device for machining blade tenon of aero-engine

Abstract

The invention discloses an aero-engine blade tenon machining and clamping device, and belongs to the technical field of aero-engine blade machining, and the aero-engine blade tenon machining and clamping device comprises a bottom plate, a clamp main body, a locking screw assembly, a cushion block, a first compression spring and a height limiting piece, the two sides of the clamp main body are provided with limiting pieces, and one ends of the limiting pieces are connected with the clamp main body; a limiting cavity is formed between the limiting piece and the side wall of the clamp body to limit the blade, and the locking screw assembly is used for enabling the limiting piece to abut against and move towards the side wall of the clamp body so that the blade can be clamped in the limiting cavity. The height limiting piece comprises a first side plate, a second side plate and a top plate, the first compression spring is used for supporting the bottom of the blade, and the top plate is used for limiting the top of the blade. According to the blade tenon chamfer clamping device, the height of the to-be-machined face of the blade can be automatically limited, the height of the to-be-machined face of the blade is a fixed value through the first compression spring and the height limiting piece, and then direct machining can be achieved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine blade processing, and in particular, to an aircraft engine blade tenon processing clamping device. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] The tenon of an aircraft engine turbine blade is subjected to extremely complex loads, and rounding the sharp edges of the tenon helps alleviate the problem of local stress concentration. At present, the CNC rounding processing method based on the forming milling cutter is widely used. The clamping and positioning scheme of the parts is as follows: a tenon and groove fixture matching the blade tenon tooth shape is used to limit the other degrees of freedom except the tenon generatrix direction. After the part is clamped, the operator uses a dial indicator to measure the height value of the part to be processed, and adjusts the part coordinate system according to the height value before processing.

[0004] Under the current fixture solution, due to the difference in the length of the blade tenon, there is a certain difference in the height of the surface to be processed after the parts are clamped. The clamping height of the blade needs to be measured and compensated, which brings certain processing errors and poor consistency of part processing. And because each part needs to be measured, the production efficiency is greatly reduced, which is not conducive to mass processing.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] The inventor found through research that there are many blades in aircraft engines and high processing quality requirements. In order to achieve high-quality and efficient processing of blade tenon chamfers, it is difficult to fully achieve it by relying solely on current clamping technology. It is necessary to adopt a more efficient method that guarantees processing quality, ensure that the height of the surface to be processed is a fixed value after the parts are clamped, and realize direct processing without measuring and adjusting the part coordinate system.

[0007] In view of at least one of the above technical problems, the present application provides an aircraft engine blade tenon processing clamping device, which can realize a blade tenon chamfering clamping device that automatically limits the height of the blade surface to be processed. Through a first compression spring and a height limiting part, the height of the blade surface to be processed is made a fixed value, thereby enabling direct processing.

[0008] According to one aspect of the present application, a clamping device for machining tenons of an aero-engine blade is provided, which is used to clamp a blade so as to chamfer the tenon of the blade. The clamping device for machining tenons of an aero-engine blade comprises a base plate, a fixture body, a locking screw assembly, a cushion block, a first compression spring and a height limiting member:

[0009] The clamp body is arranged on the bottom plate, and limiting pieces are arranged on both sides of the clamp body, one end of the limiting piece is connected to the clamp body, and a limiting cavity is formed between the limiting piece and the side wall of the clamp body, and the limiting cavity is used to limit the blade in the horizontal direction, and the locking screw assembly is used to push the limiting piece toward the side wall of the clamp body to clamp the blade in the limiting cavity;

[0010] The pad is arranged on the bottom plate, and the pad is located below the limiting cavity. The first compression spring is vertically arranged on the pad. The height limiting part is arranged on the bottom plate. The height limiting part includes a first side plate, a second side plate and a top plate. The first side plate and the second side plate are detachably arranged on the bottom plate. The first side plate and the second side plate are used to support the top plate. The first compression spring is used to support the bottom of the blade and provide a vertical upward elastic force to the blade. The top plate is used to limit the top of the blade and cooperate with the first compression spring to fix the blade in the limiting cavity.

[0011] In some embodiments of the present application, the locking screw assembly includes a first locking screw and a second locking screw, and connecting through holes are opened on the limit members on both sides. The first locking screw and the second locking screw are used to pass through the connecting through holes respectively and connect with the locking screw holes on the side walls of the clamp body, and push the limit members toward the side walls of the clamp body when screwed into the locking screw holes.

[0012] In some embodiments of the present application, a screw assembly is provided on the first side plate and the second side plate, the screw assembly is connected to the top plate, and the screw assembly is used to drive the top plate to rise and fall.

[0013] In some embodiments of the present application, the screw assembly includes a screw and a guide rod, the screw is rotatably disposed on the top of the first side plate, the guide rod is vertically disposed on the top of the second side plate, one end of the top plate is sleeved on the screw and is threadedly connected to the screw, and the other end of the top plate is sleeved on the guide rod.

[0014] In some embodiments of the present application, a rotating assembly is provided at the top of the screw rod, and the rotating assembly includes a rotating part and a pushing part. One end of the rotating part is connected to the top of the screw rod, and the pushing part is movably arranged at the other end of the rotating part. The aircraft engine blade tenon processing and clamping device also includes a locking assembly, and the locking assembly is used to lock the limiting part with the first side plate and the second side plate respectively. The pushing part is used to press the locking assembly through the limiting hole preset on the top plate through its bottom end, and the pushing part is also used to drive the rotating part to rotate after being lifted out of the limiting hole by the operator.

[0015] In some embodiments of the present application, the locking assembly includes a first locking member and a second locking member, the first locking member is arranged on the side walls of the first side panel and the second side panel, the second locking member is arranged on the side walls of the limiting members on both sides, the first locking member is used to slide into the bottom of the second locking member and be pressed and limited by the second locking member when the height limiting member is placed on the bottom plate, and the pushing member is used to press and limit the top of the second locking member through its bottom end.

[0016] In some embodiments of the present application, a first protrusion is provided at the bottom of the outer end of the first locking piece, and a guide portion and a second protrusion are respectively provided at the top and bottom of the outer end of the second locking piece, the guide portion is used to guide the first locking piece to slide under the second locking piece, and the second protrusion is used to lock the first protrusion.

[0017] In some embodiments of the present application, two limiting grooves are opened on the bottom plate, and the two limiting grooves are respectively used to limit the bottom of the first side plate and the second side plate. A second compression spring is vertically arranged in each limiting groove, and the second compression springs on both sides are respectively used to support the bottom of the first side plate and the second side plate.

[0018] In some embodiments of the present application, a handle is provided on the top of the pushing member, and the rotating assembly further includes a third compression spring, which is compressed between the handle and the rotating member.

[0019] In some embodiments of the present application, a mounting screw hole is opened on the base plate, and a connecting screw hole is opened on the clamp body. The connecting screw hole is used to set a connecting bolt, and the connecting bolt cooperates with the mounting screw hole to connect and fasten the clamp body to the base plate.

[0020] This application has the following beneficial effects:

[0021] The present application discloses an aircraft engine blade tenon processing and clamping device, which forms a limit cavity through a fixture body cooperating with a limit piece, and places a blade into the limit cavity to limit the blade in a horizontal direction, and a cushion block is provided at the bottom of the limit cavity, and a first compression spring is provided on the cushion block to support and limit the bottom of the blade, and cooperates with a top plate of the height limiting piece to limit the top of the blade, thereby limiting the height of the blade's surface to be processed, and through the first compression spring and the height limiting piece, the height of the blade's surface to be processed is fixed, so that direct processing can be achieved, reducing the time for measuring and adjusting processing parameters, and having higher processing quality and smaller processing errors than traditional fixture solutions.

[0022] Of course, any product implementing this application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0024] Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application;

[0025] Figure 2 It is a schematic diagram of the position of the cushion block in the preferred embodiment of the present application;

[0026] Figure 3 It is a structural schematic diagram of a height limiting member of a preferred embodiment of the present application;

[0027] Figure 4 It is a structural schematic diagram of a latch assembly of a preferred embodiment of the present application;

[0028] Figure 5 is a schematic diagram of the installation of the second compression spring of the preferred embodiment of the present application;

[0029] Legend: 1. Bottom plate; 2. Clamp body; 21. Limiting piece; 22. Limiting cavity; 3. First locking screw; 4. Height limiting piece; 41. First side plate; 42. Second side plate; 43. Top plate; 5. Connecting bolt; 6. Pin; 7. Second locking screw; 8. Blade; 9. Spacer; 10. First compression spring; 11. Screw rod; 12. Guide rod; 13. Rotating piece; 14. Pushing piece; 141. Handle; 15. First locking piece; 151. First protrusion; 16. Second locking piece; 161. Guide; 162. Second protrusion; 17. Second compression spring; 18. Limiting groove. DETAILED DESCRIPTION

[0030] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0031] Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 2 It is a schematic diagram of the position of the cushion block in the preferred embodiment of the present application; Figure 3 It is a structural schematic diagram of a height limiting member of a preferred embodiment of the present application; Figure 4 It is a structural schematic diagram of a latch assembly of a preferred embodiment of the present application; Figure 5 It is a schematic diagram of the installation of the second compression spring of the preferred embodiment of the present application.

[0032] A clamping device for processing and clamping a tenon of an aero-engine blade is used for clamping a blade 8 so as to chamfer the tenon of the blade. The clamping device for processing and clamping a tenon of an aero-engine blade comprises a base plate 1, a fixture body 2, a locking screw assembly, a cushion block 9, a first compression spring 10 and a height limiting member 4:

[0033] The clamp body 2 is arranged on the bottom plate 1, and limiting members 21 are arranged on both sides of the clamp body 2. One end of the limiting member 21 is connected to the clamp body 2, and a limiting cavity 22 is formed between the limiting member 21 and the side wall of the clamp body 2. The limiting cavity 22 is used to limit the blade 8 in the horizontal direction. The locking screw assembly is used to push the limiting member 21 toward the side wall of the clamp body 2 to clamp the blade 8 in the limiting cavity 22.

[0034] The pad block 9 is arranged on the base plate 1, and the pad block 9 is located below the limiting cavity 22. The first compression spring 10 is vertically arranged on the pad block 9. The height limiting component 4 is arranged on the base plate 1. The height limiting component 4 includes a first side plate 41, a second side plate 42 and a top plate 43. The first side plate 41 and the second side plate 42 are detachably arranged on the base plate 1. The first side plate 41 and the second side plate 42 are used to support the top plate 43. The first compression spring 10 is used to support the bottom of the blade 8 and provide a vertical upward elastic force to the blade 8. The top plate 43 is used to limit the top of the blade 8 and cooperate with the first compression spring 10 to fix the blade 8 in the limiting cavity 22.

[0035] The present application provides an aircraft engine blade tenon processing and clamping device, which forms a limiting cavity 22 through a fixture body 2 and a limiting piece 21. A blade 8 is placed in the limiting cavity 22 to limit the blade 8 in the horizontal direction. At the same time, a cushion block 9 is provided at the bottom of the limiting cavity 22. A first compression spring 10 is provided on the cushion block 9 to support and limit the bottom of the blade 8. The top plate 43 of the height limiting piece 4 is cooperated to limit the top of the blade 8, thereby limiting the height of the surface to be processed of the blade 8. Through the first compression spring 10 and the height limiting piece 4, the height of the surface to be processed of the blade 8 is fixed, so that direct processing can be achieved, reducing the time for measuring and adjusting processing parameters, and having higher processing quality and smaller processing error than the traditional fixture solution.

[0036] Preferably, please refer to Figure 1 and Figure 2 As shown, the locking screw assembly includes a first locking screw 3 and a second locking screw 7, and connecting through holes are opened on the limit members 21 on both sides. The first locking screw 3 and the second locking screw 7 are used to pass through the connecting through holes respectively and connect with the locking screw holes on the side walls of the clamp body 2, and push the limit members 21 toward the side walls of the clamp body 2 when screwed into the locking screw holes.

[0037] It is understandable that the first locking screw 3 and the second locking screw 7 can respectively push the limiting members 21 on both sides close to the side wall of the clamp body 2, thereby compressing the limiting cavity 22 to achieve the horizontal compression and limiting of the blade 8. The variable-sized limiting cavity 22 can facilitate the placement of the blade 8, and can cooperate with the locking screw assembly to stably clamp and limit the blade 8.

[0038] Preferably, please refer to Figure 3 , 4 As shown, a screw assembly is provided on the first side plate 41 and the second side plate 42 , and the screw assembly is connected to the top plate 43 , and the screw assembly is used to drive the top plate 43 to rise and fall.

[0039] Specifically, the screw assembly includes a screw 11 and a guide rod 12. The screw 11 is rotatably arranged on the top of the first side plate 41, and the guide rod 12 is vertically arranged on the top of the second side plate 42. One end of the top plate 43 is sleeved on the screw 11 and connected to the screw by a thread, and the other end of the top plate 43 is sleeved on the guide rod 12.

[0040] It can be understood that the top plate 43 can be raised and lowered by the screw assembly to achieve height adjustment of the top plate 43, which is convenient for placing the blade 8; at the same time, the top plate can also be limited to different heights to adapt to the clamping requirements of different blades 8, which is conducive to improving the adaptability of the clamping device.

[0041] It should be noted that in the processing of aircraft engine blades, group processing is often faced, and the blades 8 need to be ground or milled at different heights. The present application uses a liftable top plate 43 to help quickly and accurately adjust the vertical height of the blade 8 in the limit groove, so as to better control the cutting depth and meet the processing requirements.

[0042] Preferably, please refer to Figure 3 , 4 As shown, a rotating assembly is arranged on the top of the screw rod 11, and the rotating assembly includes a rotating member 13 and a pushing member 14. One end of the rotating member 13 is connected to the top of the screw rod 11, and the pushing member 14 is movably arranged on the other end of the rotating member 13. The aircraft engine blade tenon processing and clamping device also includes a positioning assembly, and the positioning assembly is used to position the limiting member 21 with the first side plate 41 and the second side plate 42 respectively. The pushing member 14 is used to press the positioning assembly through the preset limiting hole on the top plate 43 through its bottom end, and the pushing member 14 is also used to drive the rotating member 13 to rotate after being lifted out of the limiting hole by the operator.

[0043] Specifically, the locking assembly includes a first locking member 15 and a second locking member 16. The first locking member 15 is arranged on the side walls of the first side panel 41 and the second side panel 42, and the second locking member 16 is arranged on the side walls of the limiting members 21 on both sides. The first locking member 15 is used to slide into the bottom of the second locking member 16 and be pressed and limited by the second locking member 16 when the height limiting member 4 is placed on the bottom plate 1, and the pushing member 14 is used to press and limit the top of the second locking member 16 through its bottom end.

[0044] It is understandable that after the pusher 14 is lifted off the top plate, the operation can be more conveniently driven by the pusher 14 to rotate the rotating member 13 and the screw rod 11 to realize the lifting and lowering of the top plate 43, so the convenience of the lifting and lowering operation can be effectively improved by the pusher 14. At the same time, after the pusher 14 passes through the top plate 43, the top of the second clamping member 16 can be pressed and limited to improve the stability of the pressing and limiting of the first clamping member 15 and the first side plate 41 and the second side plate 42, thereby ensuring the limiting stability of the top plate 43 on the blade 8 and the accuracy of the height limit.

[0045] Therefore, the pusher 14 has multiple functions. In addition, in order to improve the use convenience of the pusher 14, optionally, a handle 141 is provided on the top of the pusher 14, and the rotating assembly further includes a third compression spring, which is compressed between the handle 141 and the rotating member 13.

[0046] It is understandable that the third compression spring is used to provide elastic force to tighten the handle 141 to the rotating member 13, thereby ensuring the installation stability of the pushing member 14 when the height limiting member 4 is in a stationary state, and avoiding the pushing member 14 from detaching when the device is transported.

[0047] Preferably, please refer to Figure 4 As shown, a first protrusion 151 is provided at the bottom of the outer end of the first locking member 15, and a guide portion 161 and a second protrusion 162 are respectively provided at the top and bottom of the outer end of the second locking member 16. The guide portion 161 is used to guide the first locking member 15 to slide under the second locking member 16, and the second protrusion 162 is used to lock the first protrusion 151.

[0048] It can be understood that the side wall of the guide portion 161 is a sloped structure, and the side wall of the first protrusion 151 close to the clamp body 2 is also a sloped structure, so that when the height limiting member 4 is placed down to the bottom plate 1, the first protrusion 151 contacts the guide portion 161, and the first protrusion 151 and the first locking member 15 are guided by the guide portion 161, so that the first locking member 15 can slide more smoothly under the second locking member 16, and then the top of the first locking member 15 can be pressed and limited by the second locking member 16, and the second protrusion 162 can lock the first protrusion 151 to enhance the limiting stability of the first locking member 15.

[0049] When the height limiting member 4 needs to be removed for chamfering the blade tenon, the height limiting member 4 can be directly lifted to disengage the first positioning member 15 from the second positioning member 16, thereby achieving very convenient disassembly and assembly of the height limiting member 4, which is beneficial to improving the overall processing efficiency.

[0050] It should be noted that the first locking member 15 and the second locking member 16 are preferably made of elastic material.

[0051] Preferably, please refer to Figure 5 As shown, two limiting grooves 18 are provided on the bottom plate 1, and the two limiting grooves 18 are respectively used to limit the bottom of the first side plate 41 and the second side plate 42, and a second compression spring 17 is vertically arranged in each limiting groove 18, and the second compression springs 17 on both sides are respectively used to support the bottom of the first side plate 41 and the second side plate 42.

[0052] It can be understood that the limiting groove 18 can limit the bottom of the first side plate 41 and the second side plate 42 to improve the overall installation stability of the height limiting component 4.

[0053] At the same time, the second compression spring 17 in the limiting groove 18 can provide an elastic force to push the first side plate 41 and the second side plate 42 upward away from the limiting groove 18, thereby pressing the first locking member 15 against the bottom of the second locking member 16 to achieve a more stable installation of the height limiting member 4.

[0054] Preferably, please refer to Figure 1 As shown, the base plate 1 is provided with mounting screw holes, and the fixture body 2 is provided with connecting screw holes, which are used to set connecting bolts 5, and the fixture body 2 and the base plate 1 are connected and fastened by the connecting bolts and the mounting screw holes.

[0055] It is understandable that the clamp body 2 can be conveniently connected and fixed to the bottom plate 1 by the connecting bolts 5, and the clamp body 2 can also be quickly disassembled by removing the connecting bolts 5. At the same time, in order to improve the installation and positioning accuracy of the clamp body 2, a pin 6 can be set on the base 1 to achieve the positioning of the clamp body 2 and the base 1 through the pin 6, so as to facilitate the disassembly and assembly of the clamp body 2.

[0056] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0057] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. A device for processing and clamping the tenon of an aircraft engine blade, used for clamping a blade (8) so as to chamfer the tenon of the blade, characterized in that: The tenon processing and clamping device for an aircraft engine blade comprises a base plate (1), a clamp body (2), a locking screw assembly, a cushion block (9), a first compression spring (10) and a height limiting member (4): The clamp body (2) is arranged on the bottom plate (1), and limiting members (21) are arranged on both sides of the clamp body (2), one end of the limiting member (21) is connected to the clamp body (2), and a limiting cavity (22) is formed between the limiting member (21) and the side wall of the clamp body (2), and the limiting cavity (22) is used to limit the blade (8) in the horizontal direction, and the locking screw assembly is used to push the limiting member (21) toward the side wall of the clamp body (2) to clamp the blade (8) in the limiting cavity (22); A cushion block (9) is arranged on the bottom plate (1), the cushion block (9) is located below the limiting cavity (22), a first compression spring (10) is vertically arranged on the cushion block (9), a height limiting member (4) is arranged on the bottom plate (1), the height limiting member (4) comprises a first side plate (41), a second side plate (42) and a top plate (43), the first side plate (41) and the second side plate (42) are detachably arranged on the bottom plate (1), the first side plate (41) and the second side plate (42) are used to support the top plate (43), the first compression spring (10) is used to support the bottom of the blade (8) and provide a vertical upward elastic force to the blade (8), and the top plate (43) is used to limit the top of the blade (8) and cooperate with the first compression spring (10) to fix the blade (8) in the limiting cavity (22).

2. The aero-engine blade tenon processing and clamping device according to claim 1 is characterized in that: The locking screw assembly comprises a first locking screw (3) and a second locking screw (7), and connecting through holes are provided on the limiting members (21) on both sides. The first locking screw (3) and the second locking screw (7) are used to pass through the connecting through holes respectively and connect with the locking screw holes on the side wall of the clamp body (2), and when screwed into the locking screw holes, the limiting member (21) is pushed toward the side wall of the clamp body (2).

3. The aerospace engine blade tenon processing and clamping device according to claim 1 is characterized in that: The first side plate (41) and the second side plate (42) are provided with a screw rod assembly, the screw rod assembly is connected to the top plate (43), and the screw rod assembly is used to drive the top plate (43) to rise and fall.

4. The aero-engine blade tenon processing and clamping device according to claim 3 is characterized in that: The screw rod assembly comprises a screw rod (11) and a guide rod (12), wherein the screw rod (11) is rotatably arranged on the top of the first side plate (41), the guide rod (12) is vertically arranged on the top of the second side plate (42), one end of the top plate (43) is sleeved on the screw rod (11) and connected to the screw rod through a thread, and the other end of the top plate (43) is sleeved on the guide rod (12).

5. The aircraft engine blade tenon processing and clamping device according to claim 4 is characterized in that: A rotating assembly is arranged at the top of the screw rod (11), and the rotating assembly comprises a rotating member (13) and a pushing member (14). One end of the rotating member (13) is connected to the top of the screw rod (11), and the pushing member (14) is movably arranged on the other end of the rotating member (13). The aircraft engine blade tenon processing and clamping device also comprises a positioning assembly, and the positioning assembly is used to position the limiting member (21) with the first side plate (41) and the second side plate (42) respectively. The pushing member (14) is used to press the positioning assembly through a preset limiting hole on the top plate (43) through its bottom end. The pushing member (14) is also used to drive the rotating member (13) to rotate after being lifted up by an operator and separated from the limiting hole.

6. The aero-engine blade tenon processing and clamping device according to claim 5, characterized in that: The locking assembly comprises a first locking member (15) and a second locking member (16); the first locking member (15) is arranged on the side walls of the first side plate (41) and the second side plate (42); the second locking member (16) is arranged on the side walls of the limiting members (21) on both sides; the first locking member (15) is used to slide into the bottom of the second locking member (16) and be pressed and limited by the second locking member (16) when the height limiting member (4) is placed on the bottom plate (1); the pushing member (14) is used to press and limit the top of the second locking member (16) through its bottom end.

7. The aircraft engine blade tenon processing and clamping device according to claim 6 is characterized in that: A first protruding portion (151) is provided at the bottom of the outer end of the first locking member (15), and a guiding portion (161) and a second protruding portion (162) are provided at the top and bottom of the outer end of the second locking member (16), respectively; the guiding portion (161) is used to guide the first locking member (15) to slide under the second locking member (16), and the second protruding portion (162) is used to lock the first protruding portion (151).

8. The aircraft engine blade tenon processing and clamping device according to claim 6, characterized in that: Two limiting grooves (18) are provided on the bottom plate (1), and the two limiting grooves (18) are respectively used to limit the bottom of the first side plate (41) and the second side plate (42). A second compression spring (17) is vertically arranged in each limiting groove (18), and the second compression springs (17) on both sides are respectively used to support the bottom of the first side plate (41) and the second side plate (42).

9. The aircraft engine blade tenon processing and clamping device according to claim 5, characterized in that: A handle (141) is provided on the top of the pushing member (14), and the rotating assembly further comprises a third compression spring, which is compressed between the handle (141) and the rotating member (13).

10. The aircraft engine blade tenon processing and clamping device according to claim 1, characterized in that: The base plate (1) is provided with mounting screw holes, and the clamp body (2) is provided with connecting screw holes, which are used to set connecting bolts (5), and the connecting bolts (5) cooperate with the mounting screw holes to connect and fasten the clamp body (2) to the base plate (1).

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