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CN-121558479-B - Multifunctional aviation blade tensile detection device

CN121558479BCN 121558479 BCN121558479 BCN 121558479BCN-121558479-B

Abstract

The invention relates to the technical field of detection, and particularly discloses a multifunctional aviation blade tensile detection device which comprises an equipment body, wherein an objective table and a rotary table are arranged on a table top of the equipment body, a pressure head assembly is arranged on the bottom surface of the rotary table, the pressure head assembly comprises an upper mounting plate and a lower mounting plate, the lower mounting plate is movably arranged on the bottom surface of the upper mounting plate, a first spring is arranged on the inner top surface of the upper mounting plate and the top surface of the lower mounting plate, and the upper mounting plate, the lower mounting plate, the first spring, a connecting sleeve and a connecting rod are arranged.

Inventors

  • SONG YANG
  • CHEN ZHENGXIN
  • WANG YUANBIN
  • WANG YONG
  • XIAO XIMING

Assignees

  • 成都航宇超合金技术有限公司

Dates

Publication Date
20260508
Application Date
20260123

Claims (7)

  1. 1. The multifunctional aviation blade tensile detection device comprises an equipment body (1), wherein an objective table (2) is arranged on a table top of the equipment body (1), a rotary table (3) is arranged on the top surface of the equipment body (1), and a pressure head component (4) is arranged on the bottom surface of the rotary table (3), and the multifunctional aviation blade tensile detection device is characterized in that a stretching component (24) is further arranged on the top surface of the objective table (2) and the bottom surface of the rotary table (3), and the stretching component (24) comprises a first clamp (25) and a second clamp (26) which can fix the upper end and the lower end of a blade; The pressure head assembly (4) comprises an upper mounting plate (41) and a lower mounting plate (42), the lower mounting plate (42) is movably arranged on the bottom surface of the upper mounting plate (41), a first spring (43) is arranged on the inner top surface of the upper mounting plate (41) and the top surface of the lower mounting plate (42), a cylinder (38) is arranged above the upper mounting plate (41), the end part of a telescopic rod of the cylinder (38) is connected with the top surface of the upper mounting plate (41), a pressure rod (44) is vertically arranged on the bottom surface of the lower mounting plate (42), steel balls (46) are arranged below the pressure rod (44), a plurality of limiting blocks (47) for wrapping the steel balls (46) are arranged around the outer side of the pressure rod (44) at equal intervals, the plurality of limiting blocks (47) can be surrounded into a cone, a plurality of connecting sleeves (52) are arranged around the outer side of the pressure rod (44) on the bottom surface of the lower mounting plate (42), a connecting rod (49) is slidably arranged on the connecting sleeve (52), the lower end of the connecting rod (49) is connected with the top surface of the upper limiting block (41), a transmission part is arranged between the outer wall surface of the connecting rod (49) and the outer side of the first transmission part, and the second transmission part is arranged on the center of the second transmission part, and the transmission part is arranged on the second transmission part; When the upper mounting plate (41) initially applies pressure to the first spring (43), the limiting block (47) can be abutted against the blade, the connecting rod (49) can drive the first transmission part to move upwards, and when the upper mounting plate (41) continuously applies pressure to the first spring (43), the second transmission part which moves downwards can drive the first transmission part to continuously ascend; The upper mounting plate (41) is in a bottle cap shape, the lower mounting plate (42) is in a circular plate shape, the lower mounting plate (42) is opposite to the inside of the upper mounting plate (41), the top surface of the upper mounting plate (41) is provided with a plurality of first through grooves (5) with long strip structures along the periphery of the outer side of a telescopic rod of the air cylinder (38), the first through grooves (5) are mutually communicated with the inner top surface of the upper mounting plate (41), the bottom surface of the lower mounting plate (42) is provided with a plurality of second through grooves (51) with long strip structures along the periphery of the outer side of a compression rod (44), the second through grooves (51) are mutually communicated with the top surface of the lower mounting plate (42), the second through grooves (51) are oppositely arranged with the first through grooves (5), a connecting sleeve (52) is arranged at the inner side end part of the second through grooves (51) in a sliding mode along the vertical direction, the upper end of the connecting sleeve (52) is opposite to the first through grooves (5), the second through grooves (51) are provided with second springs (53) along the outer side direction, and one ends of the second springs (53) are connected with the connecting sleeves (52); The first transmission part comprises a first rack (492) and a gear (57), the first rack (492) is arranged at the upper end of the outer wall of the connecting rod (49) along the vertical direction, a slot (56) is formed in the outer side surface of the connecting sleeve (52) in a communicating manner, the gear (57) is rotatably arranged in the slot (56), the second transmission part comprises a fixed block (6) and a second rack (61), the fixed block (6) is a cylinder, and the second rack (61) is arranged on the outer wall surface of the fixed block (6) in a surrounding manner along the vertical direction; An inner cavity (521) with a wide upper part and a narrow lower part is formed from the bottom surface of the connecting sleeve (52) to the inside, the upper end of the connecting rod (49) also extends to the inner upper end of the inner cavity (521), a connecting block (491) is arranged at the inner upper end of the inner cavity (521) in a matching and sliding way, one end of the connecting block (491) is connected with the connecting rod (49), a slot (56) is formed at the inner upper end of the inner cavity (521), a limit groove (7) with a strip-shaped structure is formed in the rear side surface of the inner wall of the inner cavity (521) along the vertical direction, a limit block (71) is arranged at the inner bottom surface of the limit groove (7) in a sliding way, and one end of the limit block (71) is connected with the connecting rod (49); The outer teeth of the gear (57) extend towards the inner cavity (521) and the outside of the connecting sleeve (52), the centers of the left side and the right side of the gear (57) are provided with central shafts along the centers of the end parts, and one end of each central shaft is rotationally connected with the inner wall surface of the corresponding slot (56); When the limiting block (47) is not moved, the limiting block (71) can be in contact with the bottom surface of the limiting groove (7), the first racks (492) can be mutually separated from the gear (57), when the limiting block (47) drives the connecting rod (49) to move upwards, the limiting block (71) can leave the bottom surface of the limiting groove (7), the first racks (492) can be in meshed contact with the gear (57), the number of the second racks (61) is consistent with that of the gear (57), and when the limiting block (71) moves to a third distance in the limiting groove (7), the second racks (61) can be in meshed contact with the gear (57).
  2. 2. The multifunctional aviation blade tensile detection device according to claim 1, wherein the first clamp (25) is arranged on the bottom surface of the turntable (3), the second clamp (26) is arranged on the top surface of the objective table (2), the first clamp (25) and the second clamp (26) are symmetrically arranged, a first clamping block (252) and a second clamping block (262) are movably arranged in the first clamp (25) and the second clamp (26), and the outer end surfaces of the first clamping block (252) and the second clamping block (262) are in fit arrangement with the outer surface of the blade; The lifting mechanism (22) is arranged at the lower end of the inside of the equipment body (1), the lifting mechanism (22) is a hydraulic cylinder, the end part of a telescopic rod of the hydraulic cylinder stretches into the table top of the equipment body (1), and the bottom surface of the objective table (2) is connected with the end part of the telescopic rod of the hydraulic cylinder.
  3. 3. The multifunctional aviation blade tensile detection device according to claim 2, wherein a first clamping opening (251) with an inverted convex structure is formed in the left side and the right side of the first clamp (25) in a communicating mode, first clamping blocks (252) are movably arranged on two sides of the inner wall of the first clamping opening (251), first fixing pieces (253) are arranged between the outer side face of the first clamp (25) and the inner wall face of the first clamping opening (251) in a threaded mode, second clamping openings (261) with concave structures are formed in the left side and the right side of the second clamp (26) in a communicating mode, second clamping blocks (262) are movably arranged on two sides of the inner wall of the second clamping opening (261), and second fixing pieces (263) are arranged between the outer side face of the second clamp (26) and the inner wall face of the second clamping opening (261) in a threaded mode.
  4. 4. The multifunctional aviation blade tensile detection device according to claim 2, wherein a carrying disc (21) is arranged between the bottom surface of the objective table (2) and the end part of the telescopic rod of the hydraulic cylinder, the carrying disc (21) comprises an upper carrying disc and a lower carrying disc, the diameter of the upper carrying disc is smaller than that of the lower carrying disc, a connecting column is vertically arranged in the center of the top of the upper carrying disc, the top surface of the connecting column is fixedly connected with the top surface of the objective table (2), a plurality of mutually corresponding mounting holes are formed in the top surface and the bottom surface of the upper carrying disc and the lower carrying disc, and the upper carrying disc and the lower carrying disc can be limited and fixed through the mounting holes and fixing screws.
  5. 5. The multifunctional aviation blade tensile detection device according to claim 1, wherein a vertical groove (58) is formed in the top surface and the bottom surface of the first through groove (5) in a communicating manner along the vertical direction, a positioning plate (59) with a rectangular strip structure is vertically arranged below the vertical groove (58) along the back surface of the connecting sleeve (52), the positioning plate (59) and the vertical groove (58) are symmetrically arranged, when the upper mounting plate (41) extrudes the first spring (43), the upper mounting plate (41) can drive the vertical groove (58) to slide on the outer side surface of the positioning plate (59), and when the first spring (43) is uncompressed, the vertical groove (58) and the positioning plate (59) are arranged at intervals; the inner wall surface of the second through groove (51) is provided with a sliding groove (54) along the horizontal direction, a sliding block (55) is arranged in the sliding groove (54) in a sliding mode, and one end of the sliding block (55) is connected with the connecting sleeve (52).
  6. 6. The multifunctional aviation blade tensile detection device according to claim 1, wherein the bottom surface of the compression bar (44) is provided with a pressing groove (45) with an arc structure, the limiting block (47) is provided with an opening mutually matched with the compression bar (44) along the upper end of the inner side, the limiting block (47) is provided with a clamping groove (48) mutually matched with the side surface of the steel ball (46) along the lower end of the inner side, a groove body for accommodating the steel ball (46) can be formed between the clamping groove (48) and the pressing groove (45), two thirds of the total volume of the steel ball (46) is positioned in the groove body, and the rest one third of the total volume of the steel ball (46) protrudes out of the bottom surface of the limiting block (47).
  7. 7. The multifunctional aviation blade tensile detection device according to claim 1, wherein a containing groove (23) with a circular structure is formed in the top surface of the device body (1), a mounting groove (31) with a circular structure is formed in the inner wall surface of the containing groove (23) along the circumferential direction, a rotating groove (32) with a circular structure is formed in the inner wall surface of the mounting groove (31) along the circumferential direction, the rotating disc (3) is arranged in the containing groove (23) along the rotation direction, a rotating ring (33) with a circular structure is fixedly arranged on the outer side surface of the rotating disc (3), the outer end surface of the rotating ring (33) is rotationally connected with the rotating groove (31), an extending groove (34) with a circular structure is formed in the inner wall surface of the containing groove (23) along the circumferential direction, a gear ring (35) with a circular structure is fixedly arranged on the outer side surface of the rotating ring (33), the engaging end outside the gear ring (35) extends into the extending groove (34), a worm (36) is rotatably arranged on the end, far away from the ring (35), of the worm (36) is rotatably arranged along the front and back direction, and one end, which is meshed with the worm (36) of the worm (36); The cylinder (38) is arranged on the top surface of the turntable (3), the end part of the telescopic rod of the cylinder (38) is connected with the center of the top surface of the upper mounting plate (41), and a camera (37) for shooting indentations is arranged on the bottom surface of the turntable (3).

Description

Multifunctional aviation blade tensile detection device Technical Field The invention relates to the technical field of blade detection, in particular to a multifunctional aviation blade tensile detection device. Background Aeroengine blades are the most central rotating parts of an aircraft, in practice, the blades are required to be used in various severe environments, such as in flight, to bear the strong impact and continuous flushing of high-temperature fuel gas, and also to bear the huge centrifugal force generated during high-speed running, and these extreme conditions place extremely high demands on the reliability and durability of the blades, so the blades must go through a set of extremely strict quality detection procedures before leaving the factory. According to the search, chinese patent number CN202510046533.1 discloses an aeroengine blade strength detection device and a detection method, when the device detects the strength of an aeroengine blade, the device is mainly realized by driving a pressure component to move downwards through a cylinder, wherein the pressure component comprises a pressure rod, steel balls arranged below the pressure rod and a plurality of limiting blocks movably arranged along the circumferential direction of the steel balls, when the pressure component drives the steel balls to collide with the limiting blocks, the steel balls can leave a pit on the surface of the blade, along with the continuous application of pressure by the cylinder, the steel balls gradually descend, and the limiting blocks cannot descend continuously along with the curved surface of the blade due to the collision of the steel balls, at the moment, the limiting blocks are in a lifting and avoiding state relative to the steel balls, and through the avoiding action, the smooth descent of the pressure rod and the steel balls can be ensured, so that the problem of clamping stagnation caused by direct collision between the bottom edge of the pressure rod and the curved surface in the traditional detection is avoided, the steel balls can be stably pressed down, and the subsequent detection process can be finally carried out smoothly. However, although the lifting of the pressure component in the above solution can be realized by the cylinder, mechanical performance measurement of the blade is not considered, specifically, mechanical tensile measurement of the blade is not involved, and the conventional mechanical performance measurement and detection device mostly uses pneumatic or hydraulic as a driving mode, so that the solution can utilize the cylinder to integrate the tensile function, thereby realizing the measurement of the mechanical performance of the aviation blade, but in the technical solution, the design of such function is lacking. In the scheme, when the steel balls are driven by the pressure rod to press down the blade, the limiting blocks around the steel balls are abutted against the surface of the blade, and as the pressure rod and the steel balls are continuously pressed down, the bottom surfaces of the limiting blocks are tightly attached to each other, even the curved surfaces of the blade are extruded, which is equivalent to applying a 'tightening' effect or a 'lateral constraint force' to materials around the test points. Therefore, in view of the above-mentioned technical drawbacks, it is necessary to provide a multifunctional aviation blade tensile detection device. Disclosure of Invention The invention aims to provide a multifunctional aviation blade tensile detection device, which aims to solve the problem that mechanical property detection cannot be carried out on an aviation blade in the prior art, and can also prevent a part of limiting blocks at the periphery of a steel ball from being abutted on the surface of the blade when hardness detection is carried out on the blade, so that the depth and the shape of an indentation are ensured to be controllable, and finally the accuracy of a detection result is improved. The invention is realized by the following technical scheme: The multifunctional aviation blade tensile detection device is characterized in that the top surface of the objective table and the bottom surface of the turntable are also provided with a stretching assembly, and the stretching assembly comprises a first clamp and a second clamp which can fix the upper end and the lower end of a blade; The pressure head assembly comprises an upper mounting plate and a lower mounting plate, wherein the lower mounting plate is movably arranged on the bottom surface of the upper mounting plate, a first spring is arranged between the inner top surface of the upper mounting plate and the top surface of the lower mounting plate, an air cylinder is arranged above the upper mounting plate, the end part of a telescopic rod of the air cylinder is connected with the top surface of the upper mounting plate, a pressure rod is vertically arranged on the bottom surface of the lower