A maintenance tool for engine blade shape detection and flaw detection

Abstract

The present invention relates to the technical field of engine blade maintenance, and discloses a maintenance tool for engine blade shape detection and flaw detection. The design includes a driving mechanism, a borescope lens, and a handheld display device. The driving mechanism includes a driving motor, a rotating shaft connector, a telescopic rod, and a suction cup assembly. The driving motor is electrically connected to the handheld display device through a transmission wire, and the rotation of the driving motor can be controlled by the handheld display device. The handheld display device is provided with a rotating rocker for adjusting the rotation of the borescope lens head and a rotor control knob for controlling the driving mechanism to drive the engine rotor. By connecting the driving mechanism and the borescope lens to the handheld display device together, when detecting the shape and damage of the engine blade, the handheld display device can be used to control the speed desired by the engine rotor installation inspection personnel to drive and control.

Description

Technical Field

[0001] The invention relates to the technical field of engine blade maintenance, and in particular to a maintenance tool for engine blade shape detection and flaw detection. Background Art

[0002] The turbofan engine of an aircraft is one of the most technically complex and important structures on the aircraft. The blades of the aircraft engine are a key part of the aircraft engine. Regular inspection and maintenance of these blades is essential to ensure the safety and reliability of the engine. The working conditions of the turbofan engine blades are very harsh, especially the engine blades in the combustion chamber, which are constantly eroded by the flames generated by the combustion of fuel during operation. Therefore, the frequency of inspection and maintenance of the aircraft engine blades is very high.

[0003] There are a large number of blades on the aircraft engine. Currently, the most common and simple way to inspect aircraft blades is to use a borescope to check for damage and deformation of the blades. The advantage of using a borescope for flaw detection is that it does not require excessive disassembly of the engine. It only requires opening the engine hood, which greatly reduces the difficulty of inspecting the engine blades.

[0004] Although there are many types of aircraft engines on the market, the core components of any engine are composed of a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine. When using a borescope for inspection, the inspection of the low-pressure compressor is relatively simple and does not require insertion. A rigid sleeve handle is installed under the probe guide joint. By twisting the auxiliary probe, the dynamic and static blades of the compressor can be inspected. The blade inspection of the internal high-pressure compressor, combustion chamber, high-pressure turbine, etc. requires the borescope to be inserted through the reserved holes in the engine so that the condition of the blades inside the engine can be observed.

[0005] When inspecting the engine blades at a deeper position in the engine, not only does it need to insert the lens through the reserved hole, but it also requires two engineers who work in harmony to operate at the same time. One engineer is responsible for operating the borescope to observe the condition of the engine blades, and the other engineer is responsible for rotating the engine blades. The inspection operation of the engine blades with the borescope itself has high technical requirements for the inspectors. If the two engineers do not work in harmony, it is even more difficult to ensure the inspection effect, and it is easy to miss the inspection. At present, this method that requires two engineers to cooperate with each other to realize the inspection of combustion chamber blades is not only difficult to operate, but also further increases the risk of human subjectivity in the inspection, making it difficult to ensure the quality of the inspection.

[0006] At present, a rotating device for borescope detection of civil engines with publication number CN108332972B discloses a device that can cooperate with a borescope to drive the rotor of an aircraft engine to rotate. However, the problem with this patent is that the device is too bulky and the installation and disassembly process is relatively cumbersome. Summary of the invention

[0007] The present invention aims to provide a maintenance tool for engine blade shape detection and flaw detection to solve the problem of the difficulty in operating existing aircraft engine blade maintenance equipment.

[0008] The present invention is achieved through the following technical solutions:

[0009] A maintenance tool for engine blade shape detection and flaw detection, comprising a driving mechanism, a borescope lens and a handheld display device, wherein the driving mechanism comprises a driving motor, a rotating shaft connector, a telescopic rod and a suction cup assembly, the driving motor is electrically connected to the handheld display device via a transmission wire, the rotation of the driving motor can be controlled by the handheld display device, and the handheld display device is provided with a rotating rocker for adjusting the rotation of the borescope lens head and a rotor control knob for controlling the driving mechanism to drive the engine rotor.

[0010] In a possible design, the rotating shaft connecting member includes a first disc, a second disc, a rubber sleeve and an expansion support pillar, one end of the rubber sleeve is fixed to the second disc, one end of the expansion support pillar is fixed to the first disc, the first disc and the second disc are slidingly matched, the rubber sleeve and the expansion support pillar are located at the same axial position, the expansion support pillar can slide relative to the rubber sleeve, and the expansion support pillar can expand the diameter of the rubber sleeve after being inserted into the rubber sleeve.

[0011] In a possible design, a guide post is fixed on the second disc, and the first disc and the second disc are slidably fitted together through the guide post. An arc notch is provided on the guide post, and a handle is hinged on the first disc. A locking prism is fixed on the handle. A plane is provided on the locking prism. When the plane faces the arc notch, the locking prism and the guide post can slide freely relative to each other. When the arc surface on the locking prism rotates to overlap with the arc notch, the locking prism locks the guide post and fixes it.

[0012] In a possible design, the body of the drive motor is fixed on a motor fixing seat, the motor fixing seat is hinged to one end of the telescopic rod, the motor fixing seat and the first disc are also fixed by a ball bearing, the outer ring of the ball bearing is fixed to the first disc, the inner ring of the ball bearing is fixed to the motor fixing seat, and the motor shaft of the drive motor is fixed to the first disc at the center of the first disc.

[0013] In a possible design, the suction cup assembly includes a sealing cover, a sealing rubber ring, a piston sliding in the sealing cover, an eccentric disc and a pull rod. A negative pressure chamber is provided in the sealing cover, and the piston slides in the negative pressure chamber. The sealing rubber ring is fixed on the sealing cover at the opening position of the negative pressure chamber. The piston is fixed to one end of the pull rod, and the other end of the pull rod is hinged to the eccentric disc. The eccentric disc is circular, and there is a certain distance between the intersection point of the pull rod and the eccentric disc and the center of the eccentric disc. The circumferential position of the eccentric disc is in contact with the sealing cover.

[0014] In a possible design, a plurality of sealing rings are provided between the piston and the sealing cover, and a shifting rod is fixed on the eccentric disc.

[0015] In a possible design, a torsion spring is further provided between the rotating shaft connector and the telescopic rod.

[0016] In a possible design, it also includes a lens fixing assembly, which includes a second threaded tube, a first threaded tube and a ball head sleeve, the second threaded tube is threadedly connected to the first threaded tube, the ball head sleeve is arranged between the second threaded tube and the first threaded tube, a clamping rubber ring is provided between the ball head sleeve and the second threaded tube, another clamping rubber ring is provided between the ball head sleeve and the first threaded tube, and the first threaded tube and the second threaded tube are integrally hinged with the ball head sleeve.

[0017] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0018] 1. The present invention connects the driving mechanism and the borescope lens to a handheld display device. When inspecting the shape and damage of the engine blades, the handheld display device can be used to control the speed desired by the engine rotor installation inspector, thereby ensuring that the inspector can clearly see each position on the aircraft engine blades, reducing the subjective risk of human intervention in the inspection, improving the inspection effect of the engine blades, and eliminating more hidden risks of the engine blades.

[0019] 2. The driving mechanism of the present invention has the effects of simple assembly and disassembly and portability. When inspecting the engine blades, only one inspector is needed to complete the inspection of the blades of an aircraft engine, which can effectively reduce the number of personnel in the engine blade inspection and allow more inspectors to inspect the remaining engines at the same time, thereby effectively improving the inspection efficiency of the engine blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of this application, and do not constitute a limitation of the embodiments of the present invention. In the drawings:

[0021] Figure 1 It is a structural schematic diagram of the present invention;

[0022] Figure 2 A schematic diagram of the structure of a driving mechanism in an embodiment of the present invention;

[0023] Figure 3 A half-section diagram of a driving mechanism in an embodiment of the present invention;

[0024] Figure 4 for Figure 3 Enlarged view of point A in the middle;

[0025] Figure 5 for Figure 3 Enlarged view of point B in the middle;

[0026] Figure 6 It is a schematic diagram of the structure when the driving mechanism in an embodiment of the present invention is installed on an aircraft engine;

[0027] Figure 7 For the drive mechanism Figure 2 Schematic diagram of the structure when observing in the opposite direction;

[0028] Figure 8 for Figure 7 Enlarged view of point C in the middle;

[0029] Fig. 9 It is a schematic diagram of the state of the expansion support pillar at the threaded hole position when it is not inserted into the rubber sleeve;

[0030] Fig.10 It is a schematic diagram of the state of the expansion support pillar at the threaded hole position when it is inserted into the rubber sleeve;

[0031] Fig.11 It is a schematic diagram of the cooperation between the guide column and the handle in an unlocked state;

[0032] Fig.12 It is a schematic diagram of the cooperation between the guide column and the handle in the locked state;

[0033] Fig.13 Schematic diagram of the structure of the lens fixing assembly in an embodiment of the present invention.

[0034] The reference numerals represent: 1-driving mechanism, 2-borescope lens, 3-handheld display device, 4-transmission wire, 5-telescopic rod, 6-sealing cover, 7-sealing rubber ring, 8-first disc, 9-handle, 901-locking prism, 10-guide column, 1001-arc notch, 11-driving motor, 12-motor fixing seat, 13-eccentric disc, 1301-shift rod, 14-second disc, 15-rubber sleeve, 16-ball bearing, 17-piston, 18-sealing ring, 19-pull rod, 20-expansion support pillar, 21-ball head sleeve, 22-first threaded tube, 23-second threaded tube, 24-clamping rubber ring, 25-rubber sleeve. DETAILED DESCRIPTION

[0035] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with embodiments and drawings. The exemplary embodiments of the present invention and their description are only used to explain the present invention and are not intended to limit the present invention.

[0036] Examples, such as Figures 1 to 12 As shown, a maintenance tool for engine blade shape detection and flaw detection includes a driving mechanism 1, a borescope lens 2 and a handheld display device 3. The driving mechanism 1 includes a driving motor 11, a rotating shaft connector, a telescopic rod 5 and a suction cup assembly. The driving motor 11 is electrically connected to the handheld display device 3 through a transmission wire 4. The rotation of the driving motor 11 can be controlled by the handheld display device 3. The borescope lens 2 is used to observe the blades inside the engine.

[0037] The handheld display device 3 is provided with a rotating rocker for adjusting the rotation of the head of the borescope lens 2 and a rotor control knob for controlling the driving mechanism 1 to drive the engine rotor. During inspection, the handheld display device 3 can be used to adjust the observation angle and control the rotation speed of the observed blade. The operation is convenient, and only one inspector can complete the inspection of the blade and the control of the drilling borescope lens 2 of the engine rotor, which can effectively reduce the personnel consumption during the inspection of aircraft blades. With the same number of people, more aircraft engine blades can be inspected at the same time.

[0038] In this embodiment, the rotating shaft connecting member includes a first disc 8, a second disc 14, a rubber sleeve 15 and an expansion support pillar 20, one end of the rubber sleeve 15 is fixed to the second disc 14, one end of the expansion support pillar 20 is fixed to the first disc 8, the first disc 8 and the second disc 14 are slidingly matched, the rubber sleeve 15 and the expansion support pillar 20 are located at the same axial position, the expansion support pillar 20 can slide relative to the rubber sleeve 15, and the expansion support pillar 20 can expand the diameter of the rubber sleeve 15 after being inserted into the rubber sleeve 15.

[0039] The rotating shaft connecting piece is used to be installed and fixed at the installation position of the rectifier cone of the engine rotor. Before installation, the rectifier cone needs to be disassembled, which can be simply disassembled by electric tools. After disassembly, the rubber sleeve 15 and the expansion support pillar 20 are partially inserted into the threaded hole for installing the rectifier cone. Fig. 9 and Fig.10 When the rubber sleeve 15 is not expanded by the expansion support pillar 20, the outer diameter of the rubber sleeve 15 is smaller than the minor diameter of the threaded hole. The rubber sleeve 15 is inserted into the threaded hole, and the expansion support pillar 20 is pushed into the rubber sleeve 15. When the expansion support pillar 20 is inserted into the rubber sleeve 15, the expansion support pillar 20 expands the tube wall component of the rubber sleeve 15, and the outer wall of the expanded rubber sleeve 15 is embedded in the thread groove of the threaded hole under the extrusion of the expansion support pillar 20 (such as Fig.10 ), so that the first disc 8 can be firmly fixed on the engine rotor through the rubber sleeve 15. It will be very laborious to pull out the rubber sleeve 15 by pulling the first disc 8, but it is easier to pull out the rubber sleeve 15 after pulling out the expansion support pillar 20, and it will not consume too much force to pull out the expansion support pillar 20 from the rubber sleeve 15.

[0040] Furthermore, refer to Fig.11 and Fig.12A guide column 10 is fixed on the second disc 14, and a through hole matching the guide column 10 is provided on the first disc 8. The first disc 8 and the second disc 14 are slidably matched through the guide column 10. An arc notch 1001 is provided on the guide column 10. A handle 9 is hinged on the first disc 8, and a locking prism 901 is fixed on the handle 9. A plane is provided on the locking prism 901. When the plane faces the arc notch 1001, the locking prism 901 and the guide column 10 can slide freely relative to each other. When the arc surface on the locking prism 901 rotates to coincide with the arc notch 1001, the locking prism 901 locks and fixes the guide column 10. The arc diameter on the locking prism 901 is the same as the diameter of the arc notch 1001. After the expansion support pillar 20 is fully inserted into the rubber sleeve 15, the arc notch 1001 and the locking prism 901 are coaxial, and the handle 9 is turned to rotate the locking prism 901 into the arc notch 1001. In this state, the locking prism 901 fixes the guide column 10, thereby fixing the first disc 8 and the second disc 14. Therefore, pulling the first disc 8 in this state is equivalent to pulling the second disc 14, so that the entire driving mechanism 1 can be stably fixed on the aircraft engine rotor, and the handle 9 will not collide with the telescopic rod 5 when rotating, which can ensure the normal rotation of the device. When unlocking, after turning the handle 9, the locking prism 901 and the arc notch 1001 are no longer in contact with each other, and the handle 9 is pulled. The handle 9 drives the first disc 8, and the first disc 8 drives the expansion support pillar 20 to be pulled out of the rubber sleeve 15. At this time, it is very easy to pull out the expansion support pillar 20. After the expansion support pillar 20 is pulled out, the rubber sleeve 15 can be easily withdrawn from the threaded hole. The entire disassembly and assembly process is simple and easy to operate, and the connection can be guaranteed to be firm after fixing.

[0041] In this embodiment, the body part of the driving motor 11 is fixed on the motor fixing seat 12, and the motor fixing seat 12 is hinged to one end of the telescopic rod 5. The motor fixing seat 12 and the first disc 8 are also fixed by a ball bearing 16. The outer ring of the ball bearing 16 is fixed to the first disc 8, and the inner ring of the ball bearing 16 is fixed to the motor fixing seat 12. The motor shaft of the driving motor 11 is fixed to the first disc 8 at the center position of the first disc 8. The first disc 8 can be controlled to rotate by the driving motor 11. When the first disc 8 is fixed to the aircraft engine rotor, the engine rotor can be driven to rotate by the first disc 8.

[0042] In this embodiment, the suction cup assembly includes a sealing cover 6, a sealing rubber ring 7, a piston 17 slidably arranged in the sealing cover 6, an eccentric disc 13 and a pull rod 19. A negative pressure chamber is provided in the sealing cover 6, and the piston 17 slides in the negative pressure chamber. The sealing rubber ring 7 is fixed on the sealing cover 6 at the opening position of the negative pressure chamber. When the sealing cover 6 adsorbs the inner wall of the engine fairing, the sealing rubber ring 7 can ensure the sealing performance of the sealing cover 6 when it cooperates with the fairing. The piston 17 is fixed to one end of the pull rod 19, and the other end of the pull rod 19 is hinged to the eccentric disc 13. The eccentric disc 13 is circular. There is a certain distance between the intersection point of 9 and the eccentric disk 13 and the center of the eccentric disk 13. The circumferential position of the eccentric disk 13 contacts and cooperates with the sealing cover 6. By rotating the eccentric disk 13, the eccentric disk 13 can drive the piston 17 to move through the pull rod 19, so that a vacuum cavity is formed at the position of the piston 17 close to the side of the sealing rubber ring 7, and the sealing cover 6 is firmly adsorbed on the inner wall of the engine fairing. In order to ensure the sealing between the piston 17 and the inner wall of the sealing cover 6, a plurality of sealing rings 18 are also provided between the piston 17 and the sealing cover 6. In order to facilitate the rotation of the eccentric disk 13, a lever 1301 is also fixed to the eccentric disk 13.

[0043] More specifically, one end of the telescopic rod 5 is hinged to the motor fixing seat 12 through a hinge seat, and the other end of the telescopic rod 5 is hinged to the sealing cover 6 through another hinge seat. The telescopic rod 5 includes two telescopic sleeves that slide with each other, and the friction force between the two telescopic sleeves is designed. The friction force is at least large enough to ensure that the suction cup assembly and the telescopic rod connected to the suction cup assembly will not cause the telescopic rod 5 to extend as a whole under the action of gravity alone.

[0044] It should be noted that the drive mechanism 1 in this embodiment is not too large as a whole, is light in weight, and is easy to install and disassemble, and can be completed by only one person. When inspecting the engine of an aircraft, only two people are needed to complete the inspection of all blades, which can effectively improve the inspection efficiency. At the same time, the rotation of the aircraft engine rotor is still controlled by the inspector himself, and the inspection operation is simple. The inspection speed of the damage after the engine shape inspection can be controlled by the inspector himself, which can further ensure the inspection quality.

[0045] Furthermore, a torsion spring is provided between the rotating shaft connector and the telescopic rod 5, and the torsion spring provides a force for the telescopic rod 5 to approach the engine shaft. The mass of the aircraft engine rotor is large, and therefore it also has a large inertia. When the driving mechanism 1 drives the engine rotor to rotate, if the suction cup accidentally falls off, the inertia of the engine rotor may continue to drive the entire driving mechanism 1 to rotate, and the telescopic rod or suction cup assembly in the driving mechanism 1 may scratch the fairing or air inlet wall of the aircraft. Through the torsion spring, when the aircraft suction cup accidentally falls off, the torsion spring will bring the telescopic rod 5 closer to the position of the engine rotor axis, thereby avoiding the risk of damage to the aircraft engine when the suction cup accidentally falls off. Moreover, when performing a borescope inspection, the rotation speed of the engine rotor is very low. Therefore, the telescopic rod 5 will not offset the torsion of the torsion spring due to excessive centrifugal force, thereby effectively ensuring that the driving device will not cause any damage to the aircraft engine when in use.

[0046] Example 2, reference Fig.11 During the inspection process, if the inspector holds the handheld display device 3 in one hand and the borescope lens 2 in the other hand to perform blade inspection, it is still inconvenient. Based on this, a lens fixing assembly is further provided, and the lens fixing assembly includes a second threaded tube 23, a first threaded tube 22 and a ball head sleeve 21. The second threaded tube 23 is threadedly connected with the first threaded tube 22. The ball head sleeve 21 is arranged between the second threaded tube 23 and the first threaded tube 22. A clamping rubber ring 24 is provided between the ball head sleeve 21 and the second threaded tube 23. Another clamping rubber ring 24 is provided between the ball head sleeve 21 and the first threaded tube 22. The first threaded tube 22 and the second threaded tube 23 are integrally connected to the ball head sleeve 21 with a ball, so that the first threaded tube 22 After relative rotation with the second threaded tube 23, the squeezing force of the first threaded tube 22 and the second threaded tube 23 on the ball head sleeve 21 can be changed, thereby changing the friction between the ball head sleeve 21 and the clamping rubber ring 24. A shooting channel for the borescope lens 2 is provided in the middle of the ball head sleeve 21. In the case that there is no external force pulling the borescope lens 2, the borescope lens 2 can be kept relatively fixed with the ball head sleeve 21 by friction. In order to prevent the borescope lens 2 from being worn, the ball head sleeve 21 is made of non-metallic material, such as hard silicone or PVC material. A rubber sleeve 25 is also fixed to the outside of the first threaded tube 22. When the first threaded tube 22 is inserted into the reserved hole position, the elasticity of the rubber sleeve 25 can fix the entire lens fixing assembly.

[0047] By means of the above device, when inspecting the engine blades, the borescope lens 2 is extended into the engine from the reserved hole of the engine, and the lens fixing assembly is inserted into the reserved hole position for fixing, and then the insertion depth of the borescope lens 2 is adjusted, and at the same time, the insertion angle of the borescope lens 2 is adjusted by rotating the ball head sleeve 21, so as to ensure that the lens position of the borescope lens 2 can reach a position where the blades can be fully observed and that the borescope lens 2 will not be hit by the rotating blades. When adjusted to this state, there is no need to hold the borescope lens 2 with one hand, and then the inspector only needs to hold the handheld display device 3 with one hand and control the rotation joystick with the thumb, and operate the control knob with the other hand, which can make the inspection process simpler and more convenient.

[0048] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A maintenance tool for engine blade shape detection and flaw detection, comprising a drive mechanism (1), a borescope lens (2) and a handheld display device (3), characterized in that: The driving mechanism (1) comprises a driving motor (11), a rotating shaft connecting member, a telescopic rod member (5) and a suction cup assembly; the driving motor (11) is electrically connected to the handheld display device (3) via a transmission wire (4); and the rotation of the driving motor (11) can be controlled via the handheld display device (3); The handheld display device (3) is provided with a rotating rocker for adjusting the rotation of the head of the borescope lens (2) and a rotor control knob for controlling the driving mechanism (1) to drive the engine rotor; The rotating shaft connecting member comprises a first disc (8), a second disc (14), a rubber sleeve (15) and an expansion support pillar (20); one end of the rubber sleeve (15) is fixed to the second disc (14); one end of the expansion support pillar (20) is fixed to the first disc (8); the first disc (8) and the second disc (14) are slidably matched; after the expansion support pillar (20) is inserted into the rubber sleeve (15), the diameter of the rubber sleeve (15) can be expanded.

2. A maintenance tool for engine blade shape detection and flaw detection according to claim 1, characterized in that: A guide column (10) is fixed to the second disc (14); the first disc (8) and the second disc (14) are slidably engaged via the guide column (10); a circular arc notch (1001) is provided on the guide column (10); a handle (9) is hingedly connected to the first disc (8); and a locking prism (901) is fixed to the handle (9).

3. The inspection tool for engine blade shape detection and flaw detection according to claim 1, characterized in that: The body of the drive motor (11) is fixed on a motor fixing seat (12); the motor fixing seat (12) is hinged to one end of the telescopic rod (5); the motor fixing seat (12) is fixed to the first disc (8) via a ball bearing (16); the outer ring of the ball bearing (16) is fixed to the first disc (8); the inner ring of the ball bearing (16) is fixed to the motor fixing seat (12); and the motor shaft of the drive motor (11) is fixed to the first disc (8) at the center of the first disc (8).

4. A maintenance tool for engine blade shape detection and flaw detection according to claim 1, characterized in that: The suction cup assembly comprises a sealing cover (6), a sealing rubber ring (7), a piston (17) slidably arranged in the sealing cover (6), an eccentric disc (13) and a pull rod (19); a negative pressure chamber is arranged in the sealing cover (6); the piston (17) slides in the negative pressure chamber; the sealing rubber ring (7) is fixed at the opening position of the negative pressure chamber on the sealing cover (6); the piston (17) is fixed to one end of the pull rod (19); the other end of the pull rod (19) is hinged to the eccentric disc (13); the eccentric disc (13) is circular; there is a certain distance between the intersection point of the pull rod (19) and the eccentric disc (13) and the center of the eccentric disc (13); the circumferential position of the eccentric disc (13) is in contact with the sealing cover (6).

5. A maintenance tool for engine blade shape detection and flaw detection according to claim 4, characterized in that: A plurality of sealing rings (18) are further provided between the piston (17) and the sealing cover (6), and a lever (1301) is further fixed on the eccentric disc (13).

6. The inspection tool for engine blade shape detection and flaw detection according to claim 1, characterized in that: A torsion spring is also provided between the rotating shaft connecting member and the telescopic rod member (5).

7. The inspection tool for engine blade shape detection and flaw detection according to claim 1, characterized in that: The lens fixing assembly also comprises a lens fixing assembly, the lens fixing assembly comprising a second threaded tube (23), a first threaded tube (22) and a ball head sleeve (21), the second threaded tube (23) being threadedly connected to the first threaded tube (22), the ball head sleeve (21) being arranged between the second threaded tube (23) and the first threaded tube (22), a clamping rubber ring (24) being arranged between the ball head sleeve (21) and the second threaded tube (23), another clamping rubber ring (24) being arranged between the ball head sleeve (21) and the first threaded tube (22), and the first threaded tube (22) and the second threaded tube (23) being integrally spherically hinged to the ball head sleeve (21).

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