A kind of aircraft engine blade strength detection device and detection method

Abstract

The present invention relates to the technical field of blade strength detection, and discloses an aero-engine blade strength detection device and detection method, the device comprises a body, a turntable is provided on the top wall of the body, a mounting groove is provided on the top wall of the body, a pressure assembly for driving the turntable to descend is provided on the top of the turntable, a connecting plate is fixedly installed on the top of the pressure assembly, a ball head is fixedly installed on the middle of the top of the connecting plate, a ball head is provided on the outer sleeve of the ball head, and a carrier plate is provided on the outer fixed sleeve of the ball head. The present invention adjusts the angle of the pressure rod and the avoidance of the limit assembly so that the steel ball can be perpendicular to the detection surface, so that the concave area of ​​the blade can be detected more accurately, so that the detection is not limited by the concave area of ​​the blade, and the steel ball can be adsorbed and fixed when the limit assembly avoids, so that the steel ball can be prevented from detaching from the pressure rod when the pressure rod rises, thereby ensuring subsequent normal use.

Description

Technical Field

[0001] The invention belongs to the technical field of blade strength detection, and in particular relates to an aero-engine blade strength detection device and a detection method. Background Art

[0002] The blades of aerospace engines are the components with the worst working conditions and are also the most important rotating components. Among the hot end components of aircraft engines, the blades are subjected to high-temperature gas scouring and temperature changes during engine startup and shutdown cycles, and the rotor blades are subjected to centrifugal force at high speeds, so their strength needs to be strictly tested.

[0003] The hardness of the blade is an essential process for strength testing. The existing test is carried out using a Brinell hardness tester. The blade is placed on a carrier, and the surface of the blade is squeezed by a descending pressure rod and a steel ball. The steel ball will leave a pit on the blade, which is then photographed by a camera for analysis to obtain a hardness value. However, when the existing Brinell hardness tester is in use, its pressure rod and steel ball are vertically arranged. When facing the concave surface of the blade, the steel ball cannot be pressed vertically relative to the test surface due to the curved surface of the blade, resulting in very inaccurate measured results. In addition, when the steel ball is pressed down, the bottom edge of the pressure rod may collide with the curved surface, causing the pressure rod to get stuck, affecting the smooth descent and pressing of the steel ball and thus affecting the test.

[0004] Therefore, it is necessary to invent an aircraft engine blade strength detection device and detection method to solve the above problems. Summary of the invention

[0005] In view of the above problems, the present invention provides an aircraft engine blade strength detection device and detection method to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A device for detecting the strength of an aircraft engine blade comprises a body, a turntable is provided on the top wall of the body, a mounting groove is provided on the top wall of the body, a pressure assembly for driving the turntable to descend is provided on the top of the turntable, a connecting plate is fixedly installed on the top of the pressure assembly, a ball head is fixedly installed on the middle part of the top of the connecting plate, the outer sleeve of the ball head is provided with a ball head sleeve, the outer fixed sleeve of the ball head sleeve is provided with a carrier plate, the carrier plate is fixedly connected to the inner wall of the mounting groove, the top wall of the mounting groove is provided with a fixing assembly for fixing the ball head, a camera and a pressure rod are respectively provided on the bottom of the turntable, a spherical groove is provided on the bottom of the pressure rod, a steel ball is provided in the spherical groove, a limiting assembly for limiting the steel ball is provided on the outside of the pressure rod, and a supporting assembly for fixing the blade is provided on the table top of the body.

[0008] Furthermore, the fixing assembly includes a cylinder fixedly installed in the middle of the top wall of the mounting groove, the bottom end of the cylinder rod of the cylinder is fixedly connected to a pressure plate, and a rubber pad is provided at the bottom of the pressure plate, and the rubber pad contacts the ball head.

[0009] Furthermore, the limit assembly includes multiple cross plates, and the multiple cross plates are equidistantly arranged below the pressure rod. A sliding rod is fixedly installed on the top of the cross plate, and the top of the sliding rod passes through the pressure rod and is fixedly installed with a limit plate. The outer sleeve of the sliding rod is provided with a first spring, and the two ends of the first spring are respectively fixedly connected to the cross plate and the pressure rod. A cross groove is provided at the bottom of the cross plate, and a cross block is slidably installed in the cross groove. The side of the cross block away from the steel ball is fixedly connected to the inner wall of the cross groove through a second spring. A limiting block is fixedly installed on the bottom of the cross block, and a groove cooperating with the steel ball is provided on the inner side of the limiting block. The multiple grooves and spherical grooves together constitute a slot body for accommodating steel balls, and two-thirds of the total volume of the steel balls is located in the slot body.

[0010] Furthermore, an air passage communicating with the outside is formed on the top wall of the spherical groove, and a negative pressure component for making the inside of the air passage in a negative pressure state is provided on the outside of the air passage.

[0011] Furthermore, the negative pressure component includes an air pump fixedly mounted on the bottom of the turntable, the air pump having an air suction pipe at the air suction end, the air suction pipe having an end away from the air pump fixedly connected to a threaded joint pipe via a hose, the threaded joint pipe being threadedly connected to one end of the air duct, a branch pipe being provided on the outside of the air suction pipe, an opening being provided on the branch pipe, a solenoid valve being provided at the opening, and a control component for controlling the air suction pump and the solenoid valve being provided on the outside of the pressure rod.

[0012] Furthermore, the control component includes a ring plate fixedly mounted on the outside of the pressure rod, the bottom of the ring plate is equidistantly surrounded by sensors corresponding to the limit plate, the top of the limit plate is provided with a metal sheet that cooperates with the sensor, and the bottom of the turntable is provided with a controller that cooperates with the sensor for controlling the vacuum pump and the solenoid valve.

[0013] Furthermore, the supporting assembly includes an adjusting assembly arranged on the table top of the machine body, an electromagnet is fixedly installed on the bottom of the adjusting assembly, a movable groove is provided on the table top of the machine body, the bottom wall of the movable groove is made of iron, an external fixed sleeve of the adjusting assembly is provided with a rubber ring, the outer side of the rubber ring is fixedly connected to the inner wall of the movable groove, a carrier is fixedly installed on the top of the adjusting assembly, an electric push rod is symmetrically fixedly installed on the top of the carrier, and a splint is fixedly installed on the opposite ends of the two electric push rods.

[0014] The present invention also provides a method for detecting blade strength using the above-mentioned aero-engine blade strength detection device, comprising the following steps:

[0015] S1. When in use, the blade is fixed by the support assembly. When the concave area of ​​the blade needs to be detected, the fixation of the ball head by the fixing assembly is cancelled, and then the position of the support assembly is adjusted to move the blade above, and at the same time, the turntable is turned to rotate the pressure assembly, the connecting plate, and the ball head to adjust the angle of the pressure rod;

[0016] S2, when the pressure rod is adjusted to face the area of ​​the blade to be inspected, the ball head is fixed by the fixing assembly, the support assembly is fixed, and then the turntable, the pressure rod, and the steel ball are driven down by the pressure assembly to contact the inspection surface of the blade, and then pressure is applied to make the steel ball embed into the area to be inspected of the blade. After a period of time, the pressure assembly is reset to make the steel ball leave the blade. At this time, there is a pit left by the steel ball on the blade. Then the turntable with the camera rotates to shoot the pit, and then the machine body analyzes and obtains the hardness of the blade;

[0017] S3. Due to the adjustment of the pressure rod, the steel ball can be perpendicular to the detection surface, so that the detection result is more accurate. When the steel ball presses the blade, if the limit assembly conflicts with the curved surface of the blade, the limit assembly can be adaptively lifted relative to the steel ball to make way, thereby ensuring that the steel ball can smoothly squeeze out a pit on the surface of the blade, thereby ensuring the smooth progress of the detection process of the concave area of ​​the blade. After the detection is completed, the pressure assembly takes the turntable, pressure rod and camera away from the blade to complete the hardness test of the blade.

[0018] Technical effects and advantages of the present invention:

[0019] 1. The present invention adjusts the angle of the pressure rod and the avoidance of the limit assembly so that the steel ball can be perpendicular to the detection surface, so that the concave area of ​​the blade can be detected more accurately, and the detection is not limited by the concave area of ​​the blade;

[0020] 2. The present invention can realize the adsorption and fixation of the steel ball when the limit assembly avoids, so as to prevent the steel ball from being separated from the pressure rod when the pressure rod rises, thereby ensuring the subsequent normal use. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram showing the structure of an aircraft engine blade strength detection device according to an embodiment of the present invention is shown;

[0022] Figure 2 A schematic cross-sectional view of an aircraft engine blade strength detection device according to an embodiment of the present invention is shown;

[0023] Figure 3 The embodiment of the present invention is shown Figure 2 The enlarged structural diagram at A in the middle;

[0024] Figure 4The embodiment of the present invention is shown Figure 2 The enlarged structural diagram at B in the middle;

[0025] Figure 5 The embodiment of the present invention is shown Figure 4 The enlarged structural diagram at C in the middle;

[0026] Figure 6 A schematic diagram showing the structure of a combination of a fixing assembly and a pressure assembly according to an embodiment of the present invention is shown;

[0027] Figure 7 A schematic structural diagram of a pressure rod and a steel ball assembly according to an embodiment of the present invention is shown;

[0028] In the figure: 1. body; 2. turntable; 3. pressure assembly; 4. carrier plate; 5. ball head sleeve; 6. ball head; 7. connecting plate; 8. cylinder; 9. pressure plate; 10. rubber pad; 11. camera; 12. pressure rod; 13. steel ball; 14. cross plate; 15. slide bar; 16. limit plate; 17. first spring; 18. cross block; 19. second spring; 20. limit block; 21. airway; 22. vacuum pump; 23. vacuum pipe; 24. hose; 25. solenoid valve; 26. ring plate; 27. sensor; 28. metal sheet; 29. ​​adjustment assembly; 30. electromagnet; 31. rubber sleeve; 32. carrier; 33. electric push rod; 34. clamp; 35. controller. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments.

[0030] The present invention provides an aero-engine blade strength detection device, such as Figures 1 to 7 As shown, it includes a body 1, a turntable 2 is provided on the top wall of the body 1, a mounting groove is opened on the top wall of the body 1, a pressure assembly 3 for driving the turntable 2 to descend is provided on the top of the turntable 2, the pressure assembly 3 is a pressure assembly on the Brinell hardness tester in the prior art for providing downward pressure to the turntable, the pressure rod, and the steel ball, the body 1 is a Brinell hardness tester, the turntable 2 is a turntable on the Brinell hardness tester in the prior art for driving the pressure rod and the camera to rotate and switch, a connecting plate 7 is fixedly installed on the top of the pressure assembly 3, and the top of the connecting plate 7 A ball head 6 is fixedly installed in the middle part, and a ball head sleeve 5 is provided on the outer sleeve of the ball head 6. A carrier plate 4 is provided on the outer fixed sleeve of the ball head sleeve 5. The carrier plate 4 is fixedly connected to the inner wall of the mounting groove. A fixing assembly for fixing the ball head 6 is provided on the top wall of the mounting groove. A camera 11 and a pressure rod 12 are respectively provided at the bottom of the turntable 2. A spherical groove is opened at the bottom of the pressure rod 12. A steel ball 13 is provided in the spherical groove. A limiting assembly for limiting the steel ball 13 is provided on the outside of the pressure rod 12. A supporting assembly for fixing the blades is provided on the table top of the body 1.

[0031] When in use, the blade is fixed by the supporting assembly. When the concave area of ​​the blade needs to be detected, the fixing of the ball head 6 by the fixing assembly is cancelled, and then the position of the supporting assembly is adjusted to move the blade above, and at the same time, the turntable 2 is turned to rotate with the pressure assembly 3, the connecting plate 7, and the ball head 6, so that the angle of the pressure rod 12 is adjusted. When the pressure rod 12 is adjusted to face the area to be detected of the blade, the ball head 6 is fixed by the fixing assembly, the supporting assembly is fixed, and then the turntable 2, the pressure rod 12, and the steel ball 13 are driven down by the pressure assembly 3 to contact the detection surface of the blade, and then pressure is applied to make the steel ball 13 embedded in the area to be detected of the blade. After a period of time, the pressure assembly 3 is reset so that the steel ball 13 leaves the blade. At this time, there is a pit left by the steel ball 13 on the blade, and then the turntable 2 rotates with the camera 11 to shoot the pit, and then the machine body 1 analyzes the hardness of the blade. The adjustment of the pressure rod 12 allows the steel ball 13 to be perpendicular to the detection surface, so that the detection result is more accurate. The steel ball 13 is limited by the limit assembly. When the steel ball 13 needs to be replaced, the limit assembly of the steel ball 13 is cancelled, so that the replacement of the steel ball 13 can be facilitated. When the steel ball 13 squeezes the blade, if the limit assembly conflicts with the curved surface of the blade at this time, the limit assembly can be adaptively lifted relative to the steel ball 13 so that it can make way, thereby ensuring that the steel ball 13 can smoothly squeeze out a pit on the surface of the blade, thereby ensuring the smooth progress of the detection process of the concave area of ​​the blade. After the detection is completed, the pressure assembly 3 takes the turntable 2, the pressure rod 12 and the camera 11 away from the blade to complete the hardness detection of the blade. Subsequently, the angle of the pressure rod 12 and the avoidance of the limit assembly can be adjusted as above, so that the concave area of ​​the blade can be detected more accurately, so that the detection is not limited by the concave area of ​​the blade.

[0032] like Figure 3 As shown, the fixing assembly includes a cylinder 8 fixedly installed in the middle of the top wall of the mounting groove, the bottom end of the cylinder rod of the cylinder 8 is fixedly connected to a pressure plate 9, and a rubber pad 10 is provided at the bottom of the pressure plate 9, which contacts the ball head 6.

[0033] Starting the cylinder 8 shortens its cylinder rod and moves the pressure plate 9 and the rubber pad 10 away from the ball head 6 to cancel the fixation of the ball head 6. Conversely, resetting the cylinder rod of the cylinder 8 can achieve the squeezing of the rubber pad 10 and the ball head 6, and the friction force can fix the ball head 6 so that it cannot move.

[0034] like Figure 4 , Figure 7As shown, the limit assembly includes a plurality of transverse plates 14, which are equidistantly arranged below the pressure rod 12, a slide rod 15 is fixedly installed on the top of the transverse plate 14, and a limit plate 16 is fixedly installed on the top of the slide rod 15 through the pressure rod 12, and a first spring 17 is sleeved on the outside of the slide rod 15, and the two ends of the first spring 17 are respectively fixedly connected to the transverse plate 14 and the pressure rod 12, a transverse groove is provided at the bottom of the transverse plate 14, and a transverse block 18 is slidably installed in the transverse groove, and the side of the transverse block 18 away from the steel ball 13 is fixedly connected to the inner wall of the transverse groove through a second spring 19, and a limiting block 20 is fixedly installed at the bottom of the transverse block 18, and a groove cooperating with the steel ball 13 is provided on the inner side of the limiting block 20, and a plurality of grooves and spherical grooves together form a slot body for accommodating the steel ball 13, and two-thirds of the total volume of the steel ball 13 is located in the slot body.

[0035] When the steel ball 13 needs to be replaced, multiple limiting blocks 20 on both sides are dragged horizontally to make them translate and compress the second spring 19 with the cross block 18 to deform it to generate a force, so that the limiting block 20 is separated from the steel ball 13, and then the steel ball 13 is removed and replaced, and a new steel ball 13 is placed between the limiting blocks 20, and then the limiting block 20 is loosened, and the second spring 19 releases the force to reset the cross block 18 and the limiting block 20, so that the steel ball 13 is clamped. After the steel ball 13 conflicts with the surface of the blade, when the pressure rod 12 is pressed down, the spherical groove conflicts with the steel ball 13, making the steel ball 13 unable to move. As the pressure rod 12 continues to be pressed down, the steel ball 13 descends to squeeze the surface of the blade. If the curved surface of the concave area of ​​the blade conflicts with individual limiting blocks 20 at this time, as the pressure rod 12 descends, the limiting blocks 20 conflicts with the curved surface of the blade and cannot continue to descend. At this time, the pressure rod 12 descends to compress the first spring 17 to deform it, so that the limiting block 20 can be lifted relative to the steel ball 13, so that it can avoid it and ensure the smooth descent of the pressure rod 12 and the steel ball 13. When the steel ball 13 descends, it will squeeze the limiting block 20 that conflicts with the surface of the blade, so that it moves horizontally with the cross block 18 and compresses the second spring 19. Due to the avoidance of the limiting block 20, it is ensured that the steel ball 13 can smoothly descend to squeeze the blade. When the pressure rod 12 rises, since multiple limiting blocks 20 are still in contact with the steel ball 13, the steel ball 13 will not separate from the pressure rod 12, so that it can rise with the pressure rod 12. As the pressure rod 12 rises, the second spring 19 finally releases its force to reset the cross block 18, so that the limiting block 20 is reset.

[0036] like Figure 4 As shown, the top wall of the spherical groove is provided with an air passage 21 communicating with the outside, and the outside of the air passage 21 is provided with a negative pressure component for making the inside of the air passage 21 in a negative pressure state.

[0037] The number of the limiting blocks 20 is at least 10. If more than half of the limiting blocks 20 collide with the curved surface of the blade recess when the steel ball 13 is pressed down, these limiting blocks 20 will be separated from the steel ball 13. Then, when the pressure rod 12 rises, the steel ball 13 will be separated from the pressure rod 12 and remain in the pit due to the loss of the wrapping of too many limiting blocks 20 grooves. Therefore, when the limiting blocks 20 collide with the curved surface of the blade recess, the negative pressure component is triggered as the steel ball 13 descends, so that the air in the airway 21 is extracted, and the air is extracted. The steel ball 13 and the pressure rod 12 must be adsorbed together, so that the inside of the airway 21 is in a negative pressure state, so that the pressure rod 12 and the steel ball 13 are fixed, so that even if too many grooves of the limiting blocks 20 are separated from the steel balls 13, when the pressure rod 12 rises and resets, it can still move with the steel balls 13. When the pressure rod 12 is reset, multiple limiting blocks 20 are reset under the action of the second spring 19, so that the matching grooves wrap the steel balls 13, and then the negative pressure component cancels the negative pressure state in the airway 21, so that the adsorption and fixation of the steel balls 13 are cancelled.

[0038] like Figure 4 As shown, the negative pressure component includes an air pump 22 fixedly mounted on the bottom of the turntable 2, and an air suction pipe 23 is provided at the air suction end of the air pump 22. The end of the air suction pipe 23 away from the air pump 22 is fixedly connected with a threaded joint pipe through a hose 24. The threaded joint pipe is threadedly connected to the inside of one end of the air duct 21. A branch pipe is provided on the outside of the air suction pipe 23, and an opening is provided on the branch pipe. A solenoid valve 25 is provided at the opening. A control component for controlling the air suction pump 22 and the solenoid valve 25 is provided on the outside of the pressure rod 12.

[0039] After part of the limiting block 20 collides with the blade, as the pressure rod 12 descends, the pressure rod 12 moves relative to the limiting block 12. At this time, the control component drives the vacuum pump 22 to cooperate with the airway 21, the hose 24, and the vacuum pipe 23 to extract the air in the airway 21, so that the interior of the airway is in a negative pressure state. Then the vacuum pump 22 stops, so that the steel ball 13 that conflicts with the pressure rod 12 can be sucked. When the pressure rod 12 rises and resets, after the limiting block 20 is reset, the control component drives the solenoid valve 25 to open, so that the outside air enters the airway 21 through the vacuum pipe 23 and the hose 24, canceling the negative pressure state of the airway 21 and canceling the adsorption and fixation of the steel ball 13.

[0040] like Figure 4 As shown, the control component includes a ring plate 26 fixedly mounted on the outside of the pressure rod 12, and sensors 27 corresponding to the limit plate 16 are equidistantly arranged around the bottom of the ring plate 26. The sensor 27 is an inductive sensor. A metal sheet 28 cooperating with the sensor 27 is provided on the top of the limit plate 16. A controller 35 cooperating with the sensor 27 for controlling the vacuum pump 22 and the solenoid valve 25 is provided at the bottom of the turntable 2. The controller 35 is a PLC controller.

[0041] When part of the limiting block 20 conflicts with the blade, as the pressure rod 12 and the steel ball 13 are pressed down, the pressure rod 12 moves with the ring plate 26 and the sensor 27 relative to the metal sheet 28 above the limiting block 20 in the conflicting state, so that the metal sheet 28 approaches the sensor 27. At this time, the sensor 27 detects the approach of the metal sheet 28 and cooperates with the controller 35 to drive the vacuum pump 22 to work for a period of time and then stop. When the pressure rod 12 rises and resets, since the metal sheet 28 has not left the monitoring range of the sensor 27, the solenoid valve 25 will not open at this time, so the airway 21 is still in a negative pressure state, so that the steel ball 13 is adsorbed and fixed. As the pressure rod 12 rises, multiple limiting blocks 20 separate from the blade and reset under the action of the second spring 19. When the metal sheet 28 leaves the range of the sensor 27, the sensor 27 cooperates with the controller 35 to control the solenoid valve 25 to open, so that the outside air enters the exhaust pipe 23 and enters the airway 21, canceling the negative pressure state of the airway 21 and canceling the adsorption and fixation of the steel ball 13.

[0042] like Figure 2 As shown, the support assembly includes an adjustment assembly 29 arranged on the table top of the body 1, an electromagnet 30 is fixedly installed at the bottom of the adjustment assembly 29, a movable groove is provided on the table top of the body 1, and the bottom wall of the movable groove is made of iron. The external fixed sleeve of the adjustment assembly 29 is provided with a rubber ring 31, and the outer side of the rubber ring 31 is fixedly connected to the inner wall of the movable groove. A carrier 32 is fixedly installed on the top of the adjustment assembly 29. The adjustment assembly 29 is an adjustment assembly for carrying a carrier plate for placing objects for height adjustment in the automated Brinell hardness tester in the prior art. Electric push rods 33 are symmetrically fixedly installed on the top of the carrier 32, and clamps 34 are fixedly installed on the opposite ends of the two electric push rods 33.

[0043] Place the blade between the two clamps 34, start the electric push rod 33 to extend it and move the clamps 34 to clamp and fix the two sides of the blade, push the adjustment component 29 to move the carrier 32 to adjust the position of the blade, and after the adjustment is completed, start the electromagnet 30 to adsorb and fix it to the bottom wall of the movable groove, thereby completing the fixation of the adjusted position of the carrier 32.

[0044] The present invention also provides a method for blade strength detection using the above-mentioned aircraft engine blade strength detection device, comprising the following steps:

[0045] S1. When in use, the blade is fixed by the support assembly. When the concave area of ​​the blade needs to be detected, the fixation of the ball head 6 by the fixing assembly is cancelled, and then the position of the support assembly is adjusted to move the blade above, and at the same time, the turntable 2 is turned to rotate the pressure assembly 3, the connecting plate 7, and the ball head 6, so that the angle of the pressure rod 12 is adjusted;

[0046] S2, when the pressure rod 12 is adjusted to face the area of ​​the blade to be inspected, the ball head 6 is fixed by the fixing assembly, the support assembly is fixed, and then the turntable 2, the pressure rod 12, and the steel ball 13 are driven down by the pressure assembly 3 to contact the inspection surface of the blade, and then pressure is applied to make the steel ball 13 embedded in the area to be inspected of the blade. After a period of time, the pressure assembly 3 is reset to make the steel ball 13 leave the blade. At this time, there is a pit left by the steel ball 13 on the blade, and then the turntable 2 with the camera 11 is rotated to shoot the pit, and then the body 1 analyzes and obtains the hardness of the blade;

[0047] S3. Due to the adjustment of the pressure rod 12, the steel ball 13 can be perpendicular to the detection surface, so that the detection result is more accurate. When the steel ball 13 presses the blade, if the limit assembly conflicts with the curved surface of the blade, the limit assembly can be adaptively lifted relative to the steel ball 13 so that it can make way, thereby ensuring that the steel ball 13 can smoothly squeeze out a pit on the surface of the blade, thereby ensuring the smooth progress of the detection process of the concave area of ​​the blade. After the detection is completed, the pressure assembly 3 takes the turntable 2, the pressure rod 12 and the camera 11 away from the blade to complete the hardness detection of the blade.

[0048] Working principle: Place the blade between the two clamping plates 34, start the electric push rod 33 to extend it and move the clamping plates 34 to clamp and fix the two sides of the blade. When the concave area of ​​the blade needs to be detected, start the cylinder 8 to shorten its cylinder rod and move the pressure plate 9 and rubber pad 10 away from the ball head 6 to cancel the fixation of the ball head 6. Then push the adjustment component 29 to move the carrier 32 to adjust the position of the blade. After the adjustment is completed, start the electromagnet 30 to adsorb and fix it to the bottom wall of the movable groove to complete the fixation of the adjusted position of the carrier 32. At the same time, turn the turntable 2 to rotate it with the pressure component 3, the connecting plate 7, and the ball head 6 to adjust the angle of the pressure rod 12 until the pressure rod 12 is facing the desired position of the blade. When the area to be detected is reached, the cylinder rod of the cylinder 8 is reset, so that the rubber pad 10 and the ball head 6 can be squeezed, and the friction force can fix the ball head 6 so that it cannot move. Then, the pressure component 3 drives the turntable 2, the pressure rod 12, and the steel ball 13 to descend and contact the detection surface of the blade. Then, pressure is applied to make the steel ball 13 embedded in the area to be detected of the blade. After a period of time, the pressure component 3 is reset, so that the steel ball 13 leaves the blade. At this time, there is a pit left by the steel ball 13 on the blade. Then, the turntable 2 with the camera 11 rotates to shoot towards the pit. Then, the body 1 analyzes the hardness of the blade. Due to the adjustment of the pressure rod 12, the steel ball 13 can be perpendicular to the detection surface, so that The detection result is more accurate. The grooves of multiple limiting blocks 20 cooperate with the spherical grooves to limit the steel ball 13. When the steel ball 13 squeezes the blade, when the pressure rod 12 is pressed down, the spherical groove conflicts with the steel ball 13, making the steel ball 13 unable to move. As the pressure rod 12 continues to press down, the steel ball 13 descends to squeeze the surface of the blade. If the curved surface of the concave area of ​​the blade conflicts with individual limiting blocks 20 at this time, as the pressure rod 12 descends, the limiting block 20 conflicts with the curved surface of the blade and cannot continue to descend. At this time, the pressure rod 12 descends to compress the first spring 17 to deform it, so that the limiting block 20 can be lifted relative to the steel ball 13, so that it can avoid it, ensuring the smooth descent of the pressure rod 12 and the steel ball 13. When the pressure rod 12 is lowered, the limiting block 20 in contact with the surface of the blade will be squeezed to make it move horizontally with the cross block 18 to compress the second spring 19. Due to the avoidance of the limiting block 20, it is ensured that the steel ball 13 can smoothly descend to squeeze the blade. When the pressure rod 12 rises, since multiple limiting blocks 20 are still in contact with the steel ball 13, the steel ball 13 will not be separated from the pressure rod 12, so that it can rise with the pressure rod 12. As the pressure rod 12 rises, the second spring 19 finally releases the force to reset the cross block 18, so that the limiting block 20 is reset. Subsequently, by adjusting the angle of the pressure rod 12 and the avoidance of the limit assembly, the concave area of ​​the blade can be detected more accurately, so that the detection is not limited by the concave area of ​​the blade;If more than half of the limiting blocks 20 collide with the curved surface of the blade recess when the steel ball 13 is pressed down, these limiting blocks 20 will be separated from the steel balls 13. Subsequently, when the pressure rod 12 rises, the steel balls 13 will be separated from the pressure rod 12 and remain in the pit due to the loss of the wrapping of too many limiting blocks 20 grooves. Therefore, when the limiting blocks 20 collide with the curved surface of the blade recess, the limiting blocks 20 that are now in conflict cannot continue to descend. At this time, as the pressure rod 12 and the steel balls 13 descend, the pressure rod 12 moves with the ring plate 26 and the sensor 27 relative to the metal sheet 28 above the limiting blocks 20 in the conflicting state, so that the metal sheet 28 approaches the sensor 27. At this time, the sensor 27 detects the approach of the metal sheet 28 and cooperates with the controller 35 to drive the vacuum pump 22 to work for a period of time and then stop, so that the air in the air duct 21, the hose 24, and the vacuum pipe 23 are cooperated to extract the air in the air duct 21, so that the interior is in a negative pressure state, and then the vacuum pump 22 stops. The steel ball 13 that contacts the pressure rod 12 can be sucked. When the pressure rod 12 rises and resets, since the metal sheet 28 has not left the monitoring range of the sensor 27, the solenoid valve 25 will not open at this time. Therefore, the airway 21 is still in a negative pressure state, so that the steel ball 13 is adsorbed and fixed. As the pressure rod 12 rises, the plurality of limiting blocks 20 separate from the blades and reset under the action of the second spring 19. When the metal sheet 28 leaves the range of the sensor 27, the sensor 27 cooperates with the controller 35 to control the solenoid valve 25 to open, so that the outside air enters the exhaust pipe 23 and the airway 21, canceling the negative pressure state of the airway 21 and canceling the adsorption and fixation of the steel ball 13. Since the steel ball 13 is fixed when the pressure rod 12 rises, even if the grooves of the limiting blocks 20 are too many and separated from the steel ball 13, when the pressure rod 12 rises and resets, it can still move with the steel ball 13, so that the steel ball 13 will not leave the pressure rod 12. ;

[0049] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them.

Claims

1. An aircraft engine blade strength detection device, comprising a body (1), characterized in that: The top wall of the machine body (1) is provided with a turntable (2), the top wall of the machine body (1) is provided with a mounting groove, the top of the turntable (2) is provided with a pressure assembly (3) for driving the turntable (2) to descend, the top of the pressure assembly (3) is fixedly provided with a connecting plate (7), the middle part of the top of the connecting plate (7) is fixedly provided with a ball head (6), the outer sleeve of the ball head (6) is provided with a ball head sleeve (5), the outer fixed sleeve of the ball head sleeve (5) is provided with a carrier plate (4), the carrier plate (4) is fixedly connected to the inner wall of the mounting groove, the top wall of the mounting groove is provided with a fixing assembly for fixing the ball head (6), the bottom of the turntable (2) is provided with a camera (11) and a pressure rod (12), the bottom of the pressure rod (12) is provided with a spherical groove, a steel ball (13) is provided in the spherical groove, the outside of the pressure rod (12) is provided with a limiting assembly for limiting the steel ball (13), and the table top of the machine body (1) is provided with a supporting assembly for fixing the blades; The limit assembly comprises a plurality of transverse plates (14), the plurality of transverse plates (14) being arranged equidistantly around the bottom of the pressure rod (12), a slide bar (15) being fixedly mounted on the top of the transverse plate (14), the top of the slide bar (15) passing through the pressure rod (12) being fixedly mounted on a limit plate (16), the outer portion of the slide bar (15) being sleeved with a first spring (17), the two ends of the first spring (17) being fixedly connected to the transverse plate (14) and the pressure rod (12), respectively, A transverse groove is provided at the bottom, a transverse block (18) is slidably mounted in the transverse groove, a side of the transverse block (18) away from the steel ball (13) is fixedly connected to the inner wall of the transverse groove via a second spring (19), a limiting block (20) is fixedly mounted at the bottom of the transverse block (18), a groove matching the steel ball (13) is provided on the inner side of the limiting block (20), a plurality of the grooves and the spherical grooves together form a groove body for accommodating the steel ball (13), and two thirds of the total volume of the steel ball (13) is located in the groove body.

2. The aircraft engine blade strength detection device according to claim 1, characterized in that: The fixing assembly comprises a cylinder (8) fixedly mounted in the middle of the top wall of the mounting groove, the bottom end of the cylinder rod of the cylinder (8) being fixedly connected to a pressure plate (9), the bottom of the pressure plate (9) being provided with a rubber pad (10), and the rubber pad (10) being in contact with the ball head (6).

3. The aircraft engine blade strength detection device according to claim 2, characterized in that: An air passage (21) communicating with the outside is provided on the top wall of the spherical groove, and a negative pressure component for making the inside of the air passage (21) in a negative pressure state is provided outside the air passage (21).

4. The aircraft engine blade strength detection device according to claim 3, characterized in that: The negative pressure component comprises an air pump (22) fixedly mounted on the bottom of the turntable (2); an air pump (23) is provided at the air pumping end of the air pump (22); an end of the air pump (23) away from the air pump (22) is fixedly connected to a threaded joint pipe via a hose (24); the threaded joint pipe is threadedly connected to the inside of one end of the air duct (21); a branch pipe is provided on the outside of the air pump (23); an opening is provided on the branch pipe; a solenoid valve (25) is provided at the opening; and a control component for controlling the air pump (22) and the solenoid valve (25) is provided on the outside of the pressure rod (12).

5. The aircraft engine blade strength detection device according to claim 4, characterized in that: The control assembly comprises a ring plate (26) fixedly mounted on the outside of the pressure rod (12); sensors (27) corresponding to the limit plate (16) are equidistantly arranged around the bottom of the ring plate (26); a metal sheet (28) cooperating with the sensor (27) is arranged on the top of the limit plate (16); and a controller (35) cooperating with the sensor (27) for controlling the air pump (22) and the solenoid valve (25) is arranged at the bottom of the turntable (2).

6. The aircraft engine blade strength detection device according to claim 5, characterized in that: The support assembly comprises an adjustment assembly (29) arranged on a table top of a machine body (1), an electromagnet (30) being fixedly mounted on the bottom of the adjustment assembly (29), a movable groove being arranged on the table top of the machine body (1), the bottom wall of the movable groove being made of iron, a rubber sleeve (31) being arranged on an external fixed sleeve of the adjustment assembly (29), the outer side of the rubber sleeve (31) being fixedly connected to the inner wall of the movable groove, a carrier (32) being fixedly mounted on the top of the adjustment assembly (29), electric push rods (33) being symmetrically fixedly mounted on the top of the carrier (32), and clamping plates (34) being fixedly mounted on opposite ends of two electric push rods (33).

7. A method for using the aircraft engine blade strength detection device according to claim 6, characterized in that: The following steps are involved: S1. When in use, the blade is fixed by the support assembly. When the concave area of ​​the blade needs to be detected, the fixation of the ball head (6) by the fixing assembly is cancelled, and then the position of the support assembly is adjusted so that the blade above is moved, and at the same time, the turntable (2) is turned so that it rotates with the pressure assembly (3), the connecting plate (7), and the ball head (6), so that the angle of the pressure rod (12) is adjusted; S2, when the pressure rod (12) is adjusted to face the area of ​​the blade to be inspected, the ball head (6) is fixed by the fixing assembly, the support assembly is fixed, and then the turntable (2), the pressure rod (12), and the steel ball (13) are driven down by the pressure assembly (3) to contact the inspection surface of the blade, and then pressure is applied to make the steel ball (13) embed into the inspection area of ​​the blade. After a period of time, the pressure assembly (3) is reset to make the steel ball (13) leave the blade. At this time, there is a pit left by the steel ball (13) on the blade, and then the turntable (2) with the camera (11) is rotated to face the pit to take a picture, and then the body (1) analyzes and obtains the hardness of the blade; S3. Due to the adjustment of the pressure rod (12), the steel ball (13) can be perpendicular to the detection surface, so that the detection result is more accurate. When the steel ball (13) presses the blade, if the limit assembly conflicts with the curved surface of the blade, the limit assembly can be adaptively lifted relative to the steel ball (13) so that it can make way, thereby ensuring that the steel ball (13) can smoothly squeeze out a pit on the surface of the blade, thereby ensuring the smooth progress of the detection process of the concave area of ​​the blade. After the detection is completed, the pressure assembly (3) takes the turntable (2), the pressure rod (12) and the camera (11) away from the blade to complete the hardness detection of the blade.

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