An aircraft engine turbine surface defect detection device

Abstract

The present invention discloses an aircraft engine turbine surface defect detection device, which relates to the field of surface defect detection technology. The following scheme is proposed, including a body, and also including: a conveying mechanism, which is installed on one side of the interior of the body and is used to automatically convey the aircraft engine turbine to be detected, and the conveying mechanism includes a first threaded rod rotatably connected to one side of the interior of the body, a first moving block threadedly connected to the first threaded rod, and a linkage frame fixedly connected to the top of the first moving block; a height adjustment mechanism, which is installed on the top of the linkage frame. The present invention not only automatically conveys the material to be detected through the conveying mechanism, but also performs lateral movement detection on the object to be detected through the multi-angle detection mechanism, and can also synchronously perform circular rotation detection processing, which effectively ensures the accuracy and comprehensiveness of the detection of surface defects of the aircraft engine turbine.

Description

Technical Field

[0001] The invention relates to the technical field of surface defect detection, and in particular to a surface defect detection device for an aircraft engine turbine. Background Art

[0002] The aircraft engine is the core of the entire aircraft, and its performance directly determines the overall performance of the aircraft. In the aircraft gas turbine engine, the turbine blades have the worst working environment and the most complex stress. Turbine blades are one of the most prone to failure in aircraft engines. Therefore, in the engine production process, defect detection of aircraft engine turbine blades is an important link. Aircraft engine worm gears have the characteristics of large parts batches, many models, and most defects are surface defects. The existing aircraft engine blade inspection method is mainly based on manual visual inspection, supplemented by traditional non-destructive testing technology. This inspection method has a large workload and low efficiency. Long-term visual inspection is prone to visual fatigue, which is very likely to cause missed inspections and pose a great threat to aviation safety. For this reason, we proposed an aircraft engine turbine surface defect detection device. Summary of the invention

[0003] The present invention provides an aircraft engine turbine surface defect detection device to solve the above-mentioned deficiencies in the prior art.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions:

[0005] An aircraft engine turbine surface defect detection device comprises an engine body and also comprises:

[0006] A conveying mechanism, the conveying mechanism is installed on one side of the interior of the body, and is used to automatically convey the aircraft engine turbine to be inspected, the conveying mechanism comprising a first threaded rod rotatably connected to one side of the interior of the body, a first moving block threadedly connected to the first threaded rod, and a linkage frame fixedly connected to the top of the first moving block;

[0007] A height adjustment mechanism, which is installed on the top of the linkage frame and is used to adjust the height of the aircraft engine turbine to be tested. The height adjustment mechanism includes a first linkage sleeve rotatably connected to the bottom of the linkage frame, a second threaded rod threadedly connected to the inside of the first linkage sleeve, and a support plate fixedly connected to one end of the second threaded rod;

[0008] A clamping mechanism, which is installed on the top of the support plate and is used to clamp and fix the aircraft engine turbine to be tested, and the clamping mechanism includes an operating chamber fixedly connected to the top of the support plate and a threaded operating rod rotatably connected inside the operating chamber;

[0009] A multi-angle detection mechanism is installed on one side of the interior of the fuselage, and is used to perform lateral and circumferential synchronous detection on the surface of the aircraft engine turbine. The multi-angle detection mechanism includes a reciprocating screw rotatably connected to the interior of the fuselage, a second moving block threadedly connected to the reciprocating screw, and a linkage ring movably sleeved with the second moving block.

[0010] Furthermore, the interior of the body also includes a driving mechanism and a control mechanism, the driving mechanism is used to output power to the conveying mechanism and the multi-angle detection mechanism, one end of the driving mechanism is connected to the control mechanism, one end of the control mechanism is connected to the conveying mechanism, and a transmission mechanism is provided between the control mechanism and the multi-angle detection mechanism.

[0011] Furthermore, the conveying mechanism also includes a first guide rod fixedly connected to the inside of the machine body, a first guide block is fixedly connected to the bottom side of the linkage frame corresponding to the first guide rod, the first guide rod is movably sleeved inside the first guide block, one end of the first threaded rod is fixedly connected to the first driven gear, one side of the linkage frame is fixedly connected to a cover plate, a through opening is opened on one side of the machine body, and the cover plate is closely fitted with the through opening.

[0012] Furthermore, the height adjustment mechanism also includes a first gear fixedly mounted on the first linkage sleeve, a rack is fixedly connected to the interior of the body corresponding to the first gear, one side of the rack is meshed with the first gear for transmission, a limiting rod is fixedly connected to the bottom of the support plate, a limiting hole is provided on one side of the linkage frame corresponding to the limiting rod, and the limiting rod is movably mounted inside the limiting hole.

[0013] Furthermore, the clamping mechanism also includes a linkage plate threadedly connected to the threaded operating rod, a plurality of traction plates are rotatably connected to the linkage plate, a plurality of traction plates are respectively rotatably connected to driven plates, a plurality of driven plates are respectively fixedly connected to arc-shaped clamping plates, a limiting block is fixedly connected to the interior of the operating bin, a plurality of driven plates are respectively provided with limiting grooves, a trapezoidal limiting block is fixedly connected at the corresponding limiting grooves on the limiting block, the trapezoidal limiting block is movably sleeved inside the limiting groove, a movable hole is provided at the corresponding driven plate on the operating bin, the driven plate is movably sleeved inside the movable hole, and one side of the plurality of arc-shaped clamping plates is respectively abutted against the outside of the operating bin.

[0014] Furthermore, the multi-angle detection mechanism also includes a second guide rod fixedly connected to the inside of the machine body, a second guide block movably sleeved on the second guide rod, one end of the second guide block movably sleeved on the linkage ring, one side of the second guide block and the second movable block are fixedly connected to the same balance ring, a movable opening is opened on one side of the balance ring, a linkage rod is rotatably connected inside the movable opening, a second linkage sleeve is rotatably connected to one side of the balance ring, a second gear is fixedly connected to the second linkage sleeve, a driven block is fixedly connected inside the second linkage sleeve, a moving groove is opened on the linkage rod corresponding to the driven block, the driven block is movably sleeved inside the moving groove, and a mounting ring is fixedly connected inside the linkage ring.

[0015] Furthermore, a plurality of detectors are fixedly connected to the internal array of the mounting ring, a gear ring is fixedly connected to the outside of the mounting ring, one side of the gear ring is meshed with the second gear for transmission, one end of the connecting rod is fixedly connected to the first pulley, one end of the reciprocating screw rod is fixedly connected to a double pulley corresponding to the first pulley, and the outside of the double pulley is connected to the first pulley via a same first belt.

[0016] Furthermore, the driving mechanism includes a driving motor fixedly connected to the inner bottom end of the machine body, and the output shaft of the driving motor is fixedly connected to the third gear.

[0017] Furthermore, the control mechanism includes a control rod rotatably connected to the lower part of the body, a gear column is fixedly connected to the control rod corresponding to the third gear, one side of the gear column is meshed with the third gear for transmission, a push rod motor is fixedly connected to the inner bottom end of the body, an output end of the push rod motor is fixedly connected to a control board, a mounting hole is opened on the control board corresponding to the control rod, the control rod is fixedly installed inside the mounting hole through a transmission bearing, two ends of the control rod are respectively fixedly connected to the first transmission gear and the second transmission gear, one side of the first transmission gear is meshed with the first driven gear for transmission.

[0018] Furthermore, the transmission mechanism includes a transmission rod rotatably connected to one side of the interior of the machine body, one end of the transmission rod is fixedly connected to a second driven gear corresponding to the second transmission gear, one side of the second driven gear is meshed with the second transmission gear for transmission, the other end of the transmission rod is fixedly connected to a second pulley corresponding to the double pulley, and the second pulley is connected to the external transmission of the double pulley by a second belt.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] The present invention installs a conveying mechanism, a height adjustment mechanism, a clamping mechanism, a multi-angle detection mechanism, a driving mechanism, a transmission mechanism and a control mechanism to output power to the device, automatically convey the objects to be detected and perform multi-directional detection processing;

[0021] In summary, the equipment is novel in design and simple to operate. The equipment not only automatically conveys the material to be inspected through the conveying mechanism, but also performs lateral movement inspection on the object to be inspected through the multi-angle inspection mechanism, and can also perform circular rotation inspection simultaneously, which effectively ensures the accuracy and comprehensiveness of the surface defect detection of aircraft engine turbines. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the overall top view of the three-dimensional structure of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0023] Figure 2 A schematic diagram of a partial cross-section top view of a three-dimensional structure of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0024] Figure 3 A top-down perspective structural diagram of a driving mechanism, a linkage mechanism and a multi-angle detection mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0025] Figure 4 A top-down perspective structural diagram of a conveying mechanism, a control mechanism and a height adjustment mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0026] Figure 5 This is a bottom-up stereoscopic structural diagram of a driving mechanism and a control mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0027] Figure 6 This is a bottom-up stereoscopic structural diagram of a conveying mechanism and a height adjustment mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0028] Figure 7 A top-down perspective structural diagram of a multi-angle detection mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0029] Figure 8 A schematic diagram of a partial cross-section top view of a three-dimensional structure of a clamping mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0030] Fig. 9 A top-down perspective structural diagram of an operating compartment of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0031] Fig.10 A top-down perspective structural diagram of an arc-shaped clamping plate, a traction plate and a linkage plate of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0032] Fig.11 A schematic diagram of a top-down three-dimensional structure of partial parts of a multi-angle detection mechanism of an aircraft engine turbine surface defect detection device proposed by the present invention;

[0033] Fig.12 The present invention is a bottom-up stereoscopic structural schematic diagram of a first linkage sleeve and a linkage frame of an aircraft engine turbine surface defect detection device proposed by the present invention.

[0034] In the figure: 1, machine body; 2, first threaded rod; 3, first moving block; 4, linkage frame; 5, first guide rod; 6, first guide block; 7, first linkage sleeve; 8, first gear; 9, second threaded rod; 10, support plate; 11, limit rod; 12, operating compartment; 13, threaded operating rod; 14, linkage plate; 15, traction plate; 16, arc clamping plate; 17, limit block; 18, reciprocating screw rod; 19, second moving block; 20, linkage ring; 21, mounting ring; 22, detector; 23, balance ring; 24, second guide block; 2 5. Second guide rod; 26. Second linkage sleeve; 27. Gear ring; 28. Second gear; 29. ​​Linking rod; 30. Double pulley; 31. First pulley; 32. First belt; 33. Rack; 34. Drive motor; 35. Third gear; 36. Control rod; 37. Gear column; 38. First transmission gear; 39. Second transmission gear; 40. First driven gear; 41. Transmission rod; 42. Second driven gear; 43. Second pulley; 44. Second belt; 45. Push rod motor; 46. Control board; 47. Cover plate. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] 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, rather than indicating or implying 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 limiting the present invention.

[0037] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, and it can be the internal connection of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0038] Example 1, reference Figure 1-12 : An aircraft engine turbine surface defect detection device, comprising a body 1, and also comprising a conveying mechanism, the conveying mechanism is installed on one side of the interior of the body 1, and is used for automatically conveying the aircraft engine turbine to be detected, the conveying mechanism comprises a first threaded rod 2 rotatably connected to one side of the interior of the body 1, a first moving block 3 threadedly connected to the first threaded rod 2, and a linkage frame 4 fixedly connected to the top of the first moving block 3, the conveying mechanism also comprises a first guide rod 5 fixedly connected to the interior of the body 1, a first guide block 6 is fixedly connected to the bottom side of the linkage frame 4 corresponding to the first guide rod 5, the first guide rod 5 is movably sleeved inside the first guide block 6, one end of the first threaded rod 2 is fixedly connected to a first driven gear 40, one side of the linkage frame 4 is fixedly connected to a cover plate 47, one side of the body 1 is provided with a through opening, and the cover plate 47 is closely fitted with the through opening;

[0039] A height adjustment mechanism is installed on the top of the linkage frame 4, and is used to adjust the height of the aircraft engine turbine to be tested. The height adjustment mechanism includes a first linkage sleeve 7 rotatably connected to the bottom of the linkage frame 4, a second threaded rod 9 threadedly connected to the inside of the first linkage sleeve 7, and a support plate 10 fixedly connected to one end of the second threaded rod 9. The height adjustment mechanism also includes a first gear 8 fixedly sleeved on the first linkage sleeve 7, a rack 33 is fixedly connected to the inside of the body 1 corresponding to the first gear 8, one side of the rack 33 is meshed with the first gear 8 for transmission, a limit rod 11 is fixedly connected to the bottom of the support plate 10, a limit hole is opened on one side of the linkage frame 4 corresponding to the limit rod 11, and the limit rod 11 is movably sleeved inside the limit hole;

[0040] A clamping mechanism is installed on the top of the support plate 10, which is used to clamp and fix the aircraft engine turbine to be tested. The clamping mechanism includes an operating chamber 12 fixedly connected to the top of the support plate 10 and a threaded operating rod 13 rotatably connected to the inside of the operating chamber 12. The clamping mechanism also includes a linkage plate 14 threadedly connected to the threaded operating rod 13, a plurality of traction plates 15 are rotatably connected to the linkage plate 14, and a plurality of traction plates 15 are respectively rotatably connected to driven plates, and arc-shaped clamping plates 16 are respectively fixedly connected to the plurality of driven plates, and a limited block 17 is fixedly connected to the inside of the operating chamber 12, and a plurality of driven plates are respectively provided with limited slots, and a trapezoidal limited block is fixedly connected to the corresponding limited slot on the limit block 17, and the trapezoidal limited block is movably sleeved inside the limited slot, and a movable hole is opened at the corresponding driven plate on the operating chamber 12, and the driven plate is movably sleeved inside the movable hole, and one side of the plurality of arc-shaped clamping plates 16 is respectively in contact with the outside of the operating chamber 12;

[0041] A multi-angle detection mechanism is installed on one side of the interior of the fuselage 1, and is used for synchronously detecting the surface of the aircraft engine turbine in the lateral and circumferential directions. The multi-angle detection mechanism includes a reciprocating screw 18 rotatably connected to the interior of the fuselage 1, a second moving block 19 threadedly connected to the reciprocating screw 18, and a linkage ring 20 movably sleeved with the second moving block 19. The multi-angle detection mechanism also includes a second guide rod 25 fixedly connected to the interior of the fuselage 1, a second guide block 24 movably sleeved on the second guide rod 25, one end of the second guide block 24 movably sleeved on the linkage ring 20, the second guide block 24 and one side of the second moving block 19 are fixedly connected with the same balancing ring 23, a movable opening is opened on one side of the balancing ring 23, and a linkage rod 29 is rotatably connected inside the movable opening, and the balancing ring 2 A second linkage sleeve 26 is rotatably connected to one side of 3, a second gear 28 is fixedly connected to the second linkage sleeve 26, a driven block is fixedly connected inside the second linkage sleeve 26, a moving groove is provided on the linkage rod 29 corresponding to the driven block, the driven block is movably sleeved inside the moving groove, a mounting ring 21 is fixedly connected inside the linkage ring 20, a plurality of detectors 22 are fixedly connected to the internal array of the mounting ring 21, a gear ring 27 is fixedly connected to the outside of the mounting ring 21, one side of the gear ring 27 is meshed with the second gear 28 for transmission, one end of the linkage rod 29 is fixedly connected to the first pulley 31, one end of the reciprocating screw rod 18 is fixedly connected to the double pulley 30 corresponding to the first pulley 31, and the outside of the double pulley 30 is transmission-connected to the first pulley 31 with the same first belt 32.

[0042] In the present invention, the interior of the body 1 also includes a driving mechanism and a control mechanism. The driving mechanism is used to output power to the conveying mechanism and the multi-angle detection mechanism. One end of the driving mechanism is connected to the control mechanism, and one end of the control mechanism is connected to the conveying mechanism. A transmission mechanism is provided between the control mechanism and the multi-angle detection mechanism. The driving mechanism includes a driving motor 34 fixedly connected to the bottom end of the interior of the body 1, and the output shaft of the driving motor 34 is fixedly connected to the third gear 35.

[0043] In the present invention, the control mechanism includes a control rod 36 rotatably connected to the lower part of the body 1, a gear column 37 is fixedly connected to the control rod 36 corresponding to the third gear 35, one side of the gear column 37 is meshed with the third gear 35 for transmission, a push rod motor 45 is fixedly connected to the bottom end of the body 1, and a control board 46 is fixedly connected to the output end of the push rod motor 45, a mounting hole is opened on the control board 46 corresponding to the control rod 36, the control rod 36 is fixedly installed inside the mounting hole through a transmission bearing, and the two ends of the control rod 36 are respectively fixedly connected to the first transmission gear 38 and the second transmission gear 39, and one side of the first transmission gear 38 is meshed with the first driven gear 40 for transmission.

[0044] In the present invention, the transmission mechanism includes a transmission rod 41 rotatably connected to one side of the inside of the body 1, one end of the transmission rod 41 is fixedly connected to the second driven gear 42 corresponding to the second transmission gear 39, one side of the second driven gear 42 is meshed with the second transmission gear 39 for transmission, the other end of the transmission rod 41 is fixedly connected to the second pulley 43 corresponding to the double pulley 30, and the second pulley 43 is connected to the external transmission of the double pulley 30 by a second belt 44.

[0045] Working principle, when in use: the aircraft engine turbine is sleeved on the outside of the operating compartment 12, and after sleeved, the threaded operating rod 13 is rotated to drive the linkage plate 14 to move, and the movement of the linkage plate 14 drives the traction plate 15 to extend and contract, and the extension of the traction plate 15 drives the arc clamping plate 16 to move, and the aircraft engine turbine is internally clamped and fixed by the movement of the arc clamping plate 16. After clamping and fixing, the drive motor 34 is started to drive the third gear 35 to rotate through the output shaft, and the rotation of the third gear 35 is meshed with the gear column 37 for transmission, and the rotation of the gear column 37 drives the control rod 36 to rotate, and the rotation of the control rod 36 drives the first transmission gear 38 and the second transmission gear 39 to rotate synchronously respectively. When the aircraft engine turbine is conveyed, the push rod motor 45 is started to drive the control plate 46 to retract and move, and the control rod 36 is driven to move in the opposite direction through the retraction movement of the control plate 46. The reverse direction of the control rod 36 The movement causes the first transmission gear 38 to mesh with the first driven gear 40 for transmission. The rotation of the first driven gear 40 drives the rotation of the first threaded rod 2. The rotation of the first threaded rod 2 drives the first moving block 3 to move, and at the same time drives the linkage frame 4 to move. The movement of the linkage frame 4 drives the second threaded rod 9 and the limit rod 11 to move synchronously. The movement of the linkage frame 4 drives the aircraft engine turbine to move and transport. When the second threaded rod 9 moves, the first gear 8 meshes with the rack 33 for transmission, thereby driving the first linkage sleeve 7 to rotate. The rotation of the first linkage sleeve 7 drives the second threaded rod 9 to move, and at the same time drives the support plate 10 to move upward smoothly through the limit rod 11. The upward movement of the support plate 10 causes the aircraft engine turbine to move upward, so that the aircraft engine turbine enters the interior of the body 1 through the through port. After entering, the through port is closed by the cover plate 47, and the drive motor 34 stops working at the same time.

[0046] After the inspection object enters the machine body 1, the push rod motor 45 is started again, driving the control rod 36 to move forward, and at the same time, the second transmission gear 39 is meshed with the second driven gear 42. The second driven gear 42 rotates to drive the transmission rod 41 to rotate synchronously, and at the same time drives the second pulley 43 to rotate. The rotation of the second pulley 43 drives the rotation of the double pulley 30 through the second belt 44, and at the same time drives the rotation of the first pulley 31 through the first belt 32. The rotation of the first pulley 31 drives the rotation of the linkage rod 29, and the rotation of the double pulley 30 drives the rotation of the reciprocating screw 18. The rotation of the reciprocating screw 18 drives the second moving block 19 to move, and at the same time drives the mounting ring 21 to move through the balance ring 23. The movement of the balance ring 23 synchronously drives the second linkage sleeve 26 to move, and the lateral movement of the mounting ring 21 performs lateral surface defect detection on the object to be inspected;

[0047] The rotation of the linkage rod 29 drives the second linkage sleeve 26 to rotate, the rotation of the second linkage sleeve 26 drives the second gear 28 to rotate synchronously, the rotation of the second gear 28 drives the gear ring 27 to rotate synchronously, the rotation of the gear ring 27 drives the mounting ring 21 to rotate in a circle, and the circular motion of the mounting ring 21 is used to perform circular detection on the object to be detected.

[0048] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft engine turbine surface defect detection device, comprising a body (1), characterized in that: Also includes: A conveying mechanism, the conveying mechanism being installed on one side of the interior of the body (1) and being used for automatically conveying the aircraft engine turbine to be inspected, the conveying mechanism comprising a first threaded rod (2) rotatably connected to one side of the interior of the body (1), a first moving block (3) threadedly connected to the first threaded rod (2), and a linkage frame (4) fixedly connected to the top of the first moving block (3); A height adjustment mechanism, the height adjustment mechanism being mounted on the top of the linkage frame (4) and being used to adjust the height of the turbine of the aircraft engine to be tested, the height adjustment mechanism comprising a first linkage sleeve (7) rotatably connected to the bottom of the linkage frame (4), a second threaded rod (9) internally threadedly connected to the first linkage sleeve (7), and a support plate (10) fixedly connected to one end of the second threaded rod (9); A clamping mechanism, the clamping mechanism being mounted on the top of the support plate (10) and being used to clamp and fix the turbine of the aircraft engine to be inspected, the clamping mechanism comprising an operating chamber (12) fixedly connected to the top of the support plate (10) and a threaded operating rod (13) rotatably connected to the inside of the operating chamber (12); A multi-angle detection mechanism, the multi-angle detection mechanism being installed on one side of an interior of a body (1), and being used for synchronously detecting the surface of a turbine of an aircraft engine in a lateral and circumferential manner, the multi-angle detection mechanism comprising a reciprocating screw (18) rotatably connected to the interior of the body (1), a second moving block (19) threadedly connected to the reciprocating screw (18), and a linkage ring (20) movably sleeved on the second moving block (19), and also comprising a second guide rod (25) fixedly connected to the interior of the body (1), a second guide block (24) movably sleeved on the second guide rod (25), one end of the second guide block (24) movably sleeved on the linkage ring (20), and the second guide rod (25) being ... and a second guide block (24) movably sleeved on the linkage ring (20). The two guide blocks (24) and one side of the second movable block (19) are fixedly connected to the same balancing ring (23); a movable opening is provided on one side of the balancing ring (23); a connecting rod (29) is rotatably connected inside the movable opening; a second connecting sleeve (26) is rotatably connected to one side of the balancing ring (23); a second gear (28) is fixedly connected to the second connecting sleeve (26); a driven block is fixedly connected inside the second connecting sleeve (26); a movable groove is provided on the connecting rod (29) at a position corresponding to the driven block; the driven block is movably sleeved inside the movable groove; and a mounting ring (21) is fixedly connected inside the connecting ring (20).

2. The aircraft engine turbine surface defect detection equipment according to claim 1, characterized in that: The body (1) further comprises a driving mechanism and a control mechanism inside, the driving mechanism being used to output power to the conveying mechanism and the multi-angle detection mechanism, one end of the driving mechanism being connected to the control mechanism, one end of the control mechanism being connected to the conveying mechanism, and a transmission mechanism being provided between the control mechanism and the multi-angle detection mechanism.

3. The aircraft engine turbine surface defect detection equipment according to claim 2, characterized in that: The conveying mechanism further comprises a first guide rod (5) fixedly connected to the inside of the machine body (1); a first guide block (6) is fixedly connected to a bottom side of the linkage frame (4) corresponding to the first guide rod (5); the first guide rod (5) is movably sleeved inside the first guide block (6); one end of the first threaded rod (2) is fixedly connected to a first driven gear (40); one side of the linkage frame (4) is fixedly connected to a cover plate (47); a through opening is opened on one side of the machine body (1); and the cover plate (47) is closely fitted to the through opening.

4. The aircraft engine turbine surface defect detection equipment according to claim 1, characterized in that: The height adjustment mechanism further comprises a first gear (8) fixedly sleeved on the first linkage sleeve (7); a rack (33) is fixedly connected to the interior of the body (1) at a position corresponding to the first gear (8); one side of the rack (33) is meshed with the first gear (8) for transmission; a limiting rod (11) is fixedly connected to the bottom of the support plate (10); a limiting hole is provided on one side of the linkage frame (4) at a position corresponding to the limiting rod (11); and the limiting rod (11) is movably sleeved inside the limiting hole.

5. The aircraft engine turbine surface defect detection equipment according to claim 1, characterized in that: The clamping mechanism further comprises a linkage plate (14) threadedly connected to the threaded operating rod (13); a plurality of traction plates (15) are rotatably connected to the linkage plate (14); a plurality of traction plates (15) are rotatably connected to driven plates respectively; a plurality of driven plates are respectively fixedly connected to arc-shaped clamping plates (16); a limiting block (17) is fixedly connected inside the operating bin (12); a plurality of driven plates are respectively provided with limiting grooves; a trapezoidal limiting block is fixedly connected at a position corresponding to the limiting groove on the limiting block (17); the trapezoidal limiting block is movably sleeved inside the limiting groove; a movable hole is provided at a position corresponding to the driven plate on the operating bin (12); the driven plate is movably sleeved inside the movable hole; and one side of the plurality of arc-shaped clamping plates (16) is respectively in contact with the outside of the operating bin (12).

6. The aircraft engine turbine surface defect detection equipment according to claim 1, characterized in that: The internal array of the mounting ring (21) is fixedly connected to a plurality of detectors (22); the outside of the mounting ring (21) is fixedly connected to a gear ring (27); one side of the gear ring (27) is meshed with a second gear (28) for transmission; one end of the linkage rod (29) is fixedly connected to a first belt pulley (31); one end of the reciprocating screw rod (18) is fixedly connected to a double belt pulley (30) at a position corresponding to the first belt pulley (31); and the outside of the double belt pulley (30) is transmission-connected to the first belt pulley (31) via a first belt (32).

7. The aircraft engine turbine surface defect detection equipment according to claim 2, characterized in that: The driving mechanism comprises a driving motor (34) fixedly connected to the inner bottom end of the machine body (1), and an output shaft of the driving motor (34) is fixedly connected to a third gear (35).

8. The aircraft engine turbine surface defect detection equipment according to claim 7, characterized in that: The control mechanism comprises a control rod (36) rotatably connected to the lower part of the machine body (1); a gear column (37) is fixedly connected to the control rod (36) at a position corresponding to the third gear (35); one side of the gear column (37) meshes with the third gear (35) for transmission; a push rod motor (45) is fixedly connected to the lower end of the machine body (1); an output end of the push rod motor (45) is fixedly connected to a control board (46); a mounting hole is provided on the control board (46) at a position corresponding to the control rod (36); the control rod (36) is fixedly mounted inside the mounting hole via a transmission bearing; two ends of the control rod (36) are respectively fixedly connected to a first transmission gear (38) and a second transmission gear (39); one side of the first transmission gear (38) meshes with a first driven gear (40) for transmission.

9. The aircraft engine turbine surface defect detection equipment according to claim 8, characterized in that: The transmission mechanism comprises a transmission rod (41) rotatably connected to one side of the interior of the machine body (1); one end of the transmission rod (41) is fixedly connected to a second driven gear (42) corresponding to a second transmission gear (39); one side of the second driven gear (42) is meshed with the second transmission gear (39) for transmission; the other end of the transmission rod (41) is fixedly connected to a second belt pulley (43) corresponding to a double belt pulley (30); and the second belt pulley (43) is connected to the external transmission of the double belt pulley (30) by a second belt (44).

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