Anti-fatigue test equipment for aviation parts

Abstract

The utility model relates to the technical field of aviation part fatigue testing, in particular to an aviation part anti-fatigue testing device which comprises a vibration table moving coil and a cylindrical fixed block installed on the vibration table moving coil, four positioning blocks distributed in an annular array are arranged on the outer wall of the cylindrical fixed block, the four positioning blocks are all detachably connected with blades, and the blades are arranged on the outer wall of the cylindrical fixed block. A mortise matched with a blade tenon is formed in the outer wall of the positioning block, and a pressing assembly used for positioning the position of a blade is arranged at the top of the cylindrical fixing block. According to the anti-fatigue test equipment for the aviation parts, the tenons of the four blades are respectively arranged in the four mortises, the pressing assembly can position the four blades at the same time, so that the disassembly and assembly efficiency of the blades is improved, meanwhile, the four blades are uniformly distributed on the outer side of the cylindrical fixed block, the random vibration load of the vibration table can be transmitted to the four blades to be tested, and the fatigue resistance of the blades is improved. Equivalently and synchronously loading the four blades to ensure the accuracy of anti-fatigue test data.

Description

Technical Field

[0001] The utility model relates to the technical field of fatigue testing of aviation parts, in particular to anti-fatigue testing equipment for aviation parts. Background Art

[0002] The aviation industry has extremely high requirements for the reliability and safety of parts. Parts that are subjected to cyclic loads for a long time are prone to fatigue damage, which affects the normal operation and safety of the aircraft. Therefore, anti-fatigue testing is crucial to ensure the reliability of aviation parts.

[0003] The patent with publication number CN116296186A discloses a multi-blade synchronous random equivalent loading fatigue test device, including a tensioning screw, a blade positioning block, a horizontal top block, a vertical lower top block and a vertical upper top block, the bottom of the blade positioning block is connected to the moving coil of the vibration table, the mounting groove includes a connected tenon groove, a horizontal positioning groove and a vertical positioning groove, the tenon groove cooperates with the tenon of the blade, the vertical lower top block and the vertical upper top block both cooperate with the vertical positioning groove; the vertical lower top block and the vertical upper top block both abut against the horizontal top block; the tensioning screw is a bidirectional screw, and the vertical lower top block and the vertical upper top block are threadedly connected to different thread segments of the tensioning screw. The present invention enables multiple blade test pieces to simultaneously feel the vibration load transmitted by the vibration tester, so that the load can accurately and truly act on the blade being tested, so as to simulate the boundary conditions borne by the working state of the engine, and finally achieve the purpose of testing the fatigue strength of the blade test piece.

[0004] In the specific use of the above-mentioned prior art, the tenon of the blade is installed in the tenon groove of the blade positioning block, and the force limiting wrench is used to rotate the tightening screw to make the vertical lower top block move upward along direction ②, and the vertical upper top block move downward along direction ③. Under the action of the upper right corner inclined surface of the vertical lower top block and the lower right corner inclined surface of the vertical upper top block, the horizontal top block moves along direction ①, and finally tightens the tenon of the blade to make the blade reach a rigid holding state. Although the above operation can fix the position of the blade, the four blades need to be fixed separately, that is, the staff needs to rotate four tightening screws to fix the four blades, which has the problem of inconvenient disassembly and assembly, and because the tenon groove is a horizontal through-type design, the tenon of the blade is not easy to be fixed in the center in the tenon groove. If the four blades are not all fixed in the center, there may be large data differences between the four blades during the experiment, affecting the accuracy of the fatigue test. In view of this, we propose an anti-fatigue testing equipment for aviation parts. Utility Model Content

[0005] The purpose of the utility model is to provide anti-fatigue testing equipment for aviation parts to solve the problems raised in the above background technology.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] An anti-fatigue test device for aviation parts comprises a vibration table dynamic coil, and a cylindrical solid block mounted on the vibration table dynamic coil, the outer wall of the cylindrical solid block is provided with four positioning blocks arranged in a ring array, the four positioning blocks are all detachably connected with blades, the outer wall of the positioning block is provided with a tenon matched with the tenon of the blade, the top of the cylindrical solid block is provided with a clamping assembly for locating the position of the blade, the tenon of the blade is placed in the tenon, the height of the tenon is greater than the height of the tenon of the blade, the top of the tenon needs to reserve a position for the clamping block, the clamping assembly can position the four blades at the same time, thereby improving the efficiency of disassembly and assembly of the blades, and at the same time the four blades are evenly distributed on the outside of the cylindrical solid block to ensure the accuracy of the anti-fatigue test data;

[0008] A threaded connection groove is provided in the middle of the top of the cylindrical solid block, and the clamping assembly includes a threaded rod threadedly connected in the threaded connection groove, the threaded rod can be adjusted up and down, a round rod is provided at the top of the threaded rod, and a cross-shaped pressing plate is rotatably connected to the outer wall of the round rod, and a circular hole for the round rod to pass through is provided in the middle of the bottom of the cross-shaped pressing plate, and the cross-shaped pressing plate can be rotated horizontally. When the pressing block is completely removed from the mortise, there is no need to rotate the threaded rod. It is only necessary to rotate the cross-shaped pressing plate at a certain angle to move the pressing block away from the top of the mortise to avoid affecting the removal of the blade tenon from the mortise, so as to facilitate the staff to quickly complete the disassembly and assembly of the blade;

[0009] The four ends of the bottom of the cross-shaped pressure plate are provided with pressure blocks adapted to the mortise and tenon, the top of the round rod is provided with a detachable rectangular sleeve block, and the bottom of the outer wall of the rectangular sleeve block is provided with a frame-shaped top plate that fits the cross-shaped pressure plate. When the threaded rod is tightened, the frame-shaped top plate generates pressure on the top of the cross-shaped pressure plate, thereby pressing the cross-shaped pressure plate against the top of the cylindrical solid block to prevent the pressure block from moving upward from the mortise and tenon during use and affecting the stability of the blade.

[0010] Preferably, an annular base is provided at the bottom of the outer wall of the cylindrical solid block, and four mounting holes a arranged in an annular array are opened on the top of the annular base. The annular base is detachably connected to the moving coil of the vibration table by a second bolt.

[0011] Preferably, a circular bottom plate is provided at the bottom of the outer wall of the round rod, and a circular groove is provided at the bottom of the cross-shaped pressure plate and at the bottom end of the circular hole. The diameter of the circular groove is larger than the diameter of the circular hole. The circular bottom plate is located in the circular groove. When the threaded rod moves upward, the circular bottom plate can support the cross-shaped pressure plate and move upward synchronously, so that the four pressure blocks can be quickly moved out of the four mortise grooves respectively.

[0012] Preferably, the pressing block is inserted into the top of the mortise, and the bottom of the pressing block abuts against the top of the tenon of the blade, thereby fixing the blade.

[0013] Preferably, a rectangular connecting block is provided at the top of the round rod, the rectangular connecting block passes through the circular hole, and the rectangular connecting block is detachably connected to the rectangular sleeve block by a first bolt, so that the round rod can be disassembled and assembled with the rectangular sleeve block, which facilitates the assembly of the clamping assembly.

[0014] Preferably, mounting holes b are provided on the four sides of the rectangular sleeve block, and threaded grooves are provided on the four sides of the rectangular connecting block. The four mounting holes b are respectively connected to the four threaded grooves. The threaded end of the first bolt passes through the mounting hole b and is threadedly connected to the threaded groove. The rectangular connecting block is installed in the rectangular sleeve block by the four first bolts, which is convenient for the staff to assemble the clamping assembly.

[0015] Preferably, a hand wheel is provided on the top of the rectangular sleeve block to facilitate the staff to drive the threaded rod to rotate.

[0016] Compared with the prior art, the beneficial effects of the utility model are:

[0017] 1. The anti-fatigue test equipment for aviation parts has four blades with tenons inserted into four tenons respectively. The clamping assembly can position the four blades at the same time, thereby improving the efficiency of blade disassembly and assembly. At the same time, the four blades are evenly distributed on the outside of the cylindrical solid block. The random vibration load of the vibration table can be transmitted to the four blades to be tested, and the four blades are loaded equivalently and synchronously to ensure the accuracy of the anti-fatigue test data.

[0018] 2. The anti-fatigue testing equipment for aviation parts drives the threaded rod to rotate through a hand wheel. When the threaded rod is tightened, the frame-shaped top plate generates pressure on the top of the cross-shaped pressure plate. The four pressure blocks respectively press and position the four blades, thereby pressing the cross-shaped pressure plate against the top of the cylindrical solid block to prevent the pressure block from moving upward from the mortise and tenon during use and affecting the stability of the blade.

[0019] 3. When disassembling the blade, the anti-fatigue testing equipment of this aviation component drives the threaded rod to rotate through the hand wheel to move the threaded rod upward. When the pressure block is completely removed from the tenon groove, there is no need to rotate the threaded rod anymore. It is only necessary to rotate the cross-shaped pressure plate at a certain angle to move the pressure block away from directly above the tenon groove to avoid affecting the removal of the blade tenon from the tenon groove, so as to facilitate the staff to quickly complete the disassembly and assembly of the blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall first state structure of the utility model;

[0021] Figure 2 It is a schematic diagram of the overall second state structure of the utility model;

[0022] Figure 3It is a schematic diagram of the assembly structure of the cylindrical fixing block and the positioning block in the utility model;

[0023] Figure 4 This is a schematic diagram of the structure of the clamping assembly in the utility model;

[0024] Figure 5 This is a schematic diagram of the cross-shaped pressing plate structure in the utility model;

[0025] Figure 6 This is one of the partial structural schematic diagrams of the clamping assembly in the utility model;

[0026] Figure 7 This is the second partial structural schematic diagram of the clamping assembly in the utility model.

[0027] In the figure: 1. Vibrating table moving coil; 2. Cylindrical solid block; 20. Ring base; 200. Mounting hole a; 21. Threaded connection groove; 3. Positioning block; 30. Tenon groove; 4. Blade; 5. Clamping assembly; 50. Threaded rod; 51. Round rod; 52. Round bottom plate; 53. Rectangular connecting block; 530. Threaded groove; 54. Cross-shaped pressure plate; 540. Circular hole; 541. Circular groove; 542. Pressure block; 55. Rectangular sleeve block; 550. Frame-shaped top plate; 551. Mounting hole b; 56. Handwheel; 57. First bolt; 6. Second bolt. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0029] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0030] See also Figure 1-Figure 7 , the utility model provides a technical solution:

[0031] An anti-fatigue test device for aviation parts comprises a vibration table dynamic coil 1, and a cylindrical solid block 2 mounted on the vibration table dynamic coil 1, the outer wall of the cylindrical solid block 2 is provided with four positioning blocks 3 arranged in a ring array, the four positioning blocks 3 are all detachably connected with blades 4, the random vibration load of the vibration table is transmitted to the four blades 4 to be tested through the vibration table dynamic coil 1, the cylindrical solid block 2 and the positioning block 3, and the four blades 4 are subjected to equivalent synchronous loading to achieve fatigue strength testing of multiple blades 4 at the same time, the outer wall of the positioning block 3 is provided with a tenon 30 matched with the tenon of the blade 4, the top of the cylindrical solid block 2 is provided with a clamping assembly 5 for locating the position of the blade 4, the tenon of the blade 4 is placed in the tenon 30, the height of the tenon 30 is greater than the height of the tenon of the blade 4, the top of the tenon 30 needs to reserve the position of the pressing block 542, the clamping assembly 5 can position the four blades 4 at the same time, thereby improving the efficiency of disassembly and assembly of the blade 4, and at the same time, the four blades 4 are evenly distributed on the outside of the cylindrical solid block 2 to ensure the accuracy of the anti-fatigue test data;

[0032] A threaded connection groove 21 is provided in the middle of the top of the cylindrical solid block 2. The clamping assembly 5 includes a threaded rod 50 threadedly connected to the threaded connection groove 21. The threaded rod 50 can be adjusted up and down. A round rod 51 is provided at the top of the threaded rod 50. A cross-shaped pressing plate 54 is rotatably connected to the outer wall of the round rod 51. A circular hole 540 for the round rod 51 to pass through is provided in the middle of the bottom of the cross-shaped pressing plate 54. The cross-shaped pressing plate 54 can be rotated horizontally. When the pressing block 542 is completely removed from the mortise 30, there is no need to rotate the threaded rod 50. It is only necessary to rotate the cross-shaped pressing plate 54 to a certain angle to move the pressing block 542 away from the top of the mortise 30 to avoid affecting the removal of the tenon of the blade 4 from the mortise 30, so as to facilitate the staff to quickly complete the disassembly and assembly of the blade 4.

[0033] The four ends of the bottom of the cross-shaped pressure plate 54 are provided with pressure blocks 542 adapted to the mortise and tenon 30, and the top of the round rod 51 is provided with a detachable rectangular sleeve block 55, and the bottom of the outer wall of the rectangular sleeve block 55 is provided with a frame-shaped top plate 550 that fits with the cross-shaped pressure plate 54. When the threaded rod 50 is tightened, the frame-shaped top plate 550 generates pressure on the top of the cross-shaped pressure plate 54, thereby pressing the cross-shaped pressure plate 54 against the top of the cylindrical solid block 2, preventing the pressure block 542 from moving upward from the mortise and tenon 30 during use and affecting the stability of the blade 4.

[0034] In this embodiment, an annular base 20 is provided at the bottom of the outer wall of the cylindrical solid block 2. Four mounting holes a200 arranged in a circular array are opened on the top of the annular base 20. The annular base 20 is detachably connected to the vibration table dynamic coil 1 through a second bolt 6.

[0035] Specifically, a circular bottom plate 52 is provided at the bottom of the outer wall of the round rod 51, and a circular groove 541 is provided at the bottom of the cross-shaped pressure plate 54 and at the bottom end of the circular hole 540. The diameter of the circular groove 541 is larger than the diameter of the circular hole 540. The circular bottom plate 52 is located in the circular groove 541. When the threaded rod 50 moves upward, the circular bottom plate 52 can support the cross-shaped pressure plate 54 and move upward synchronously, so that the four pressure blocks 542 can be quickly moved out of the four mortises 30 respectively.

[0036] Furthermore, the pressing block 542 is inserted into the top of the mortise 30 , and the bottom of the pressing block 542 abuts against the top of the tenon of the blade 4 , thereby fixing the blade 4 .

[0037] Furthermore, a rectangular connecting block 53 is provided at the top of the round rod 51, and the rectangular connecting block 53 passes through the circular hole 540. The rectangular connecting block 53 is detachably connected to the rectangular sleeve block 55 by a first bolt 57, so that the round rod 51 can be disassembled and assembled with the rectangular sleeve block 55, which facilitates the assembly of the clamping component 5.

[0038] Furthermore, mounting holes b551 are provided on the four sides of the rectangular sleeve 55, and threaded grooves 530 are provided on the four sides of the rectangular connecting block 53. The four mounting holes b551 are respectively connected to the four threaded grooves 530. The threaded end of the first bolt 57 passes through the mounting hole b551 and is threadedly connected to the threaded groove 530. The rectangular connecting block 53 is installed in the rectangular sleeve 55 by the four first bolts 57, which is convenient for the staff to assemble the clamping assembly 5.

[0039] Furthermore, a hand wheel 56 is provided on the top of the rectangular sleeve block 55 to facilitate the staff to drive the threaded rod 50 to rotate.

[0040] When the anti-fatigue testing equipment for aviation parts of this embodiment is in use, the staff puts the tenons of the four blades 4 into the four tenons 30 respectively, and then turns the hand wheel 56 to drive the threaded rod 50 to rotate, and the threaded rod 50 moves downward. At the same time, the staff moves the four pressure blocks 542 to the top of the four tenons 30 respectively. As the threaded rod 50 continues to move downward, the four pressure blocks 542 move into the four tenons 30 respectively until the threaded rod 50 is tightened. At this time, the frame-shaped top plate 550 generates pressure on the top of the cross-shaped pressure plate 54, and the four pressure blocks 542 respectively press and position the four blades 4, thereby pressing the cross-shaped pressure plate 54 against the top of the cylindrical solid block 2 to prevent the pressure blocks 542 from moving upward from the tenon 30 during use and affecting the stability of the blade 4. Then the staff starts the vibration table, and the random vibration load of the vibration table is vibrated through The dynamic coil 1, the cylindrical solid block 2 and the positioning block 3 are transferred to the four blades 4 to be tested, and the four blades 4 are subjected to equivalent synchronous loading to realize fatigue strength testing of multiple blades 4 at the same time; when the blade 4 needs to be replaced, the staff turns the hand wheel 56 to drive the threaded rod 50 to rotate, the threaded rod 50 moves upward, and the circular bottom plate 52 supports the cross-shaped pressure plate 54 to move upward synchronously, so that the four pressure blocks 542 are quickly moved out of the four tenons 30 respectively. When the pressure blocks 542 are completely moved out of the tenons 30, there is no need to rotate the threaded rod 50. It is only necessary to rotate the cross-shaped pressure plate 54 at a certain angle to move the pressure blocks 542 away from directly above the tenons 30 to avoid affecting the tenons of the blades 4 from moving out of the tenons 30. Then the staff can move the tenons of the blades 4 out of the tenons 30, thereby facilitating the staff to quickly complete the disassembly and assembly of the blades 4.

[0041] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the utility model and are not used to limit the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection of the utility model is defined by the attached claims and their equivalents.

Claims

1. An anti-fatigue testing device for aviation parts, comprising a vibration table dynamic coil (1), and a cylindrical solid block (2) mounted on the vibration table dynamic coil (1), characterized in that: The outer wall of the cylindrical solid block (2) is provided with four positioning blocks (3) arranged in a ring array, and the four positioning blocks (3) are all detachably connected to the blades (4). The outer wall of the positioning block (3) is provided with a tenon (30) that cooperates with the tenon of the blade (4). The top of the cylindrical solid block (2) is provided with a clamping assembly (5) for locating the position of the blade (4). The middle part of the top of the cylindrical solid block (2) is provided with a threaded connection groove (21). The clamping assembly (5) includes a threaded rod (50) threadedly connected to the threaded connection groove (21). The threaded rod (50) is provided with a threaded connection groove (21). A round rod (51) is provided at the top of the threaded rod (50), and a cross-shaped pressing plate (54) is rotatably connected to the outer wall of the round rod (51). A circular hole (540) is provided in the middle of the bottom of the cross-shaped pressing plate (54) for the round rod (51) to pass through. Four ends of the bottom of the cross-shaped pressing plate (54) are provided with pressing blocks (542) that match the tenon groove (30). A detachable rectangular sleeve block (55) is provided at the top of the round rod (51), and a frame-shaped top plate (550) that fits the cross-shaped pressing plate (54) is provided at the bottom of the outer wall of the rectangular sleeve block (55).

2. The anti-fatigue testing equipment for aviation parts according to claim 1, characterized in that: An annular base (20) is provided at the bottom of the outer wall of the cylindrical solid block (2), and four mounting holes a (200) arranged in an annular array are provided at the top of the annular base (20). The annular base (20) is detachably connected to the vibration table moving coil (1) via a second bolt (6).

3. The anti-fatigue testing equipment for aviation parts according to claim 1, characterized in that: A circular bottom plate (52) is provided at the bottom of the outer wall of the round rod (51), and a circular groove (541) is provided at the bottom of the cross-shaped pressing plate (54) and at a position located at the bottom end of the circular hole (540). The diameter of the circular groove (541) is greater than the diameter of the circular hole (540), and the circular bottom plate (52) is located in the circular groove (541).

4. The anti-fatigue testing equipment for aviation parts according to claim 1, characterized in that: The pressing block (542) is inserted into the top of the tenon groove (30), and the bottom of the pressing block (542) abuts against the top of the tenon of the blade (4).

5. The anti-fatigue testing equipment for aviation parts according to claim 1, characterized in that: A rectangular connecting block (53) is provided at the top end of the round rod (51). The rectangular connecting block (53) passes through the circular hole (540). The rectangular connecting block (53) is detachably connected to the rectangular sleeve block (55) via a first bolt (57).

6. The anti-fatigue testing equipment for aviation parts according to claim 5, characterized in that: The four sides of the rectangular sleeve block (55) are each provided with a mounting hole b (551), the four sides of the rectangular connection block (53) are each provided with a threaded groove (530), the four mounting holes b (551) are respectively connected to the four threaded grooves (530), and the threaded end of the first bolt (57) passes through the mounting hole b (551) and is threadedly connected to the threaded groove (530).

7. The anti-fatigue testing equipment for aviation parts according to claim 1, characterized in that: A hand wheel (56) is provided on the top of the rectangular sleeve block (55).

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