An aircraft engine inspection tool

Abstract

The present invention discloses an aircraft engine inspection tool, which relates to the field of aircraft engine detection technology, and includes an engine frame and a horizontal plate, wherein the engine frame is provided with a horizontal plate, wherein the horizontal plate is provided with a storage mechanism, wherein the movable rods are provided with guide rods, wherein the movable rods are provided with fixing components, and wherein the left and right sides of the horizontal plate are provided with fixing threaded sleeves. The aircraft engine inspection tool is provided with a supporting rack rod, and when the inspection tool and the aircraft engine are fixed, the gear mechanism can be driven to rotate by an adjustable wrench, and the gear mechanism drives the supporting rack rod to move upward, so that the electromagnet at the upper end of the supporting rack rod abuts against the aircraft engine, and the aircraft engine is adsorbed by the electromagnet, thereby completing the fixing of the inspection tool, and no manual hand-held borescope is required, thereby reducing the difficulty of the staff in inspecting the aircraft engine, and facilitating the viewing of the data on the display screen.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine detection, in particular to an aircraft engine inspection tool. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.

[0003] After more than a hundred years of development, aircraft engines have developed into mature products with extremely high reliability. The aircraft engines in use include various types such as turbojet / turbofan engines, turboshaft / turboprop engines, ramjet engines and piston engines. They are not only used as power for military and civilian aircraft, drones and cruise missiles for various purposes, but also gas turbines derived from aircraft engines are widely used in ground power generation, marine power, mobile power stations, natural gas and oil pipeline pumping stations and other fields.

[0004] The borescope is an important tool for aircraft engine inspection. Its main function is to check whether there are problems such as wear, cracks, corrosion, defects, etc. in aviation or civil aviation engines. It can not only measure the size and shape of the aperture inside the key components of the engine to determine whether the design requirements are met, but also intuitively reflect the quality or damage status inside the engine, providing a reliable basis for quality control or situation-based monitoring decisions. The use of borescopes plays a positive role in ensuring flight safety and preventing engine shutdowns in the air, especially in the R&D and manufacturing stages and the early troubleshooting of aircraft. It can intuitively and comprehensively evaluate the quality of aircraft parts, timely discover and quantify defects, and eliminate safety hazards.

[0005] For example, the automatic inspection device for aircraft engine blade borescope with application number 202210966246.9 drives the detection head into the aircraft engine to detect the engine blades through the telescopic adjustment tube and the main body, guides the wind to the cleaning element through the air duct, blows away the dust or foreign matter contaminated on the detection head through the cleaning element, and then the two cleaning elements move inwards and kiss the detection head, which can clean the dust or foreign matter that cannot be blown away on the detection head, so that the detection head can remain clear and the staff can clearly inspect the engine blades. However, the device still has certain defects;

[0006] When inspecting aircraft engine blades, the borescope needs to be manually held and the blades need to be manually rotated to complete the inspection of each blade of the aircraft engine. Since the borescope itself has many and complex internal components, it is heavy, which increases the difficulty for staff to inspect aircraft engines.

[0007] So we proposed an aircraft engine inspection tool to solve the problems raised above. Summary of the invention

[0008] The purpose of the present invention is to provide an aircraft engine inspection tool to solve the problem raised by the above background technology that when inspecting aircraft engine blades, the aircraft engine inspection tools currently on the market need to manually hold the body of the borescope and manually rotate the aircraft engine blades to complete the inspection of each blade of the aircraft engine. Since the borescope itself has many and complex internal components, the borescope has a large weight, which increases the difficulty of inspecting the aircraft engine for the staff.

[0009] To achieve the above-mentioned object, the present invention provides the following technical solutions: an aircraft engine inspection tool, comprising an engine frame and a horizontal plate, wherein the engine frame is provided with a horizontal plate, the horizontal plate is provided with a storage mechanism, and movable rods are passed through the left and right sides of the horizontal plate, guide rods are installed on the movable rods, and threaded grooves are provided on the movable rods, a fixing assembly is installed on the movable rods, and fixed threaded sleeves are installed on the left and right sides of the horizontal plate;

[0010] A borescope body is installed above the horizontal plate;

[0011] A support base is installed below the horizontal plate, and an embedding groove is opened on the rear side of the support base, and a positioning mechanism is installed on the upper surface of the embedding groove, a built-in groove is opened inside the support base, and a fixing rod is installed inside the built-in groove, a supporting rack rod is sleeved above the fixing rod, an electromagnet is installed on the upper end of the supporting rack rod, a connecting block is installed inside the built-in groove, and a storage groove is opened inside the connecting block, and a gear mechanism is installed in the storage groove.

[0012] Preferably, the storage mechanism comprises a storage groove and a limiting slide groove, the storage groove is provided inside the horizontal plate, and the limiting slide groove is provided on the top of the storage groove.

[0013] With the above structural design, the movable rod can be easily stored through the design of the storage groove, thereby reducing the area occupied by the borescope inspection tool after the aircraft engine inspection is completed.

[0014] Preferably, the width of the limiting slide groove is equal to the diameter of the guide rod, and a sliding connection structure is formed between the guide rod and the limiting slide groove.

[0015] With the above structural design, when the movable rod is moved, the movable rod slides along the limiting sliding groove in the storage groove through the upper guide rod, so that the movable rod is more stable when moving and will not deviate.

[0016] Preferably, magnetic blocks are installed on opposite sides of the movable rod, and protective balls are installed on opposite ends of the movable rod.

[0017] By adopting the above-mentioned structural design, when the movable rod is stored, the fixing assembly is separated from the fixed threaded sleeve on the horizontal plate, and the fixing assembly is rotated to one end away from the horizontal plate, and then the movable rods on the left and right sides are moved relative to each other, so that the movable rods are adsorbed by the magnetic suction block, thereby completing the limiting of the movable rod when it is stored.

[0018] Preferably, the fixing assembly includes a first threaded sleeve and a second threaded sleeve, the first threaded sleeve is connected to the second threaded sleeve, the center line of the first threaded sleeve coincides with the second threaded sleeve, the first threaded sleeve is threadedly connected to the fixed threaded sleeve, and the second threaded sleeve is threadedly connected to the thread groove on the movable rod.

[0019] By adopting the above-mentioned structural design, the movable rod is pulled outward, and the protective ball on the movable rod is abutted against the inner wall of the surface of the aerospace engine, and then the fixing component is rotated, and the second threaded sleeve on the fixing component moves along the movable rod, thereby driving the first threaded sleeve to move, so that the first threaded sleeve moves to the position of the fixed threaded sleeve, and the first threaded sleeve is connected to the fixed threaded sleeve, so as to complete the limiting of the movable rod, so that the movable rod abuts against the inner wall of the aerospace engine to prevent the inspection tool from falling without a support point when the fastening components of the inspection basis are loosened. Therefore, the movable rod can play a protective role.

[0020] Preferably, the borescope body includes a display screen, an operation panel, an exploration wire and an exploration probe. The operation panel is installed on the borescope body, and the display screen is installed above the operation panel. The exploration wire is installed above the display screen, and the exploration probe is installed at the end of the exploration wire.

[0021] With the above structural design, the aircraft engine blades can be inspected through the exploration probe on the exploration wire, the display screen can display the data of the exploration probe, and the exploration probe can be controlled through the operation panel.

[0022] Preferably, the positioning mechanism includes an arc-shaped abutment block and a vacuum suction cup, the arc-shaped abutment block is installed on the upper surface of the embedded groove, and the vacuum suction cup is installed below the arc-shaped abutment block, the vacuum suction cup is distributed in an arc-shaped structure, and the vacuum suction cup and the arc-shaped abutment block are detachably connected.

[0023] With the above structural design, when the inspection tool needs to be fixed, the vacuum suction cup below the arc-shaped abutment block is abutted against the inner wall of the aircraft engine, and pre-positioning with the inner wall of the aircraft engine is achieved through the vacuum suction cup.

[0024] Preferably, the center line of the supporting rack rod and the center line of the fixing rod coincide with each other, and a sliding connection structure is formed between the supporting rack rod and the fixing rod.

[0025] With the above structural design, the supporting rack rod can move up and down along the fixed rod when subjected to force, and the fixed rod plays a role of limiting and guiding the supporting rack rod, making the supporting rack rod more stable when it moves up and down under force.

[0026] Preferably, a baffle is installed at the lower end of the supporting rack rod, and the baffle is connected to the connecting block via a telescopic spring.

[0027] With the above structural design, when disassembling the inspection tool, the electromagnet is directly powered off, and then the supporting rack rod can move downward under the action of gravity and the rebound force of the telescopic spring, so that the electromagnet is away from the aircraft engine, and then the inspection tool can be manually pulled out.

[0028] Preferably, the gear mechanism can be connected to the inside of the storage slot through a rotating shaft, the gear mechanism is connected to a movable wrench, the movable wrench is located outside the support base, the gear mechanism is meshed with the supporting rack rod, and the supporting rack rod is slidably connected to the connecting block.

[0029] By adopting the above structural design, when fixing the inspection tool and the aircraft engine, the gear mechanism can be driven to rotate by the adjustable wrench, and the gear mechanism drives the supporting rack rod to move upward, so that the electromagnet at the upper end of the supporting rack rod abuts against the aircraft engine, and the aircraft engine is adsorbed by the electromagnet, thereby completing the fixation of the inspection tool.

[0030] Compared with the prior art, the invention has the following beneficial effects: the aircraft engine inspection tool:

[0031] 1. A supporting rack rod is provided. When fixing the inspection tool and the aircraft engine, the gear mechanism can be driven to rotate by an adjustable wrench, and the gear mechanism drives the supporting rack rod to move upward, so that the electromagnet at the upper end of the supporting rack rod abuts against the aircraft engine, and the aircraft engine is adsorbed by the electromagnet, thereby completing the fixing of the inspection tool. There is no need for manual hand-held borescope, which reduces the difficulty of inspection of the aircraft engine by the staff, and at the same time facilitates the viewing of the data on the display screen;

[0032] 2. A telescopic spring is provided. When disassembling the inspection tool, the electromagnet is directly powered off, and then the supporting rack rod can move downward under the action of gravity and the rebound force of the telescopic spring, so that the electromagnet is away from the aircraft engine, and then the inspection tool can be manually pulled out;

[0033] 3. A movable rod and a fixed threaded sleeve are provided. The movable rod is pulled outward, and the protective ball on the movable rod is abutted against the inner wall of the surface of the aerospace engine. Then the fixed component is rotated, and the second threaded sleeve on the fixed component moves along the movable rod, thereby driving the first threaded sleeve to move, so that the first threaded sleeve moves to the position of the fixed threaded sleeve, and the first threaded sleeve is connected with the fixed threaded sleeve, so that the movable rod can be limited, so that the movable rod abuts against the inner wall of the aerospace engine to prevent the inspection tool from falling without a support point when the fastening components of the inspection basis are loosened. Therefore, the movable rod can play a protective role;

[0034] 4. A storage slot is provided. The design of the storage slot facilitates the storage of the movable rod, thereby reducing the area occupied by the borescope inspection tool after the aircraft engine inspection is completed;

[0035] 5. A vacuum suction cup is provided. When the inspection tool needs to be fixed, the vacuum suction cup below the arc-shaped abutment block is abutted against the inner wall of the aircraft engine, and pre-positioning with the inner wall of the aircraft engine is achieved through the vacuum suction cup. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 This is a schematic diagram of the installation structure of the present invention when inspecting aerospace engines;

[0037] Figure 2 This is a schematic diagram of the support base structure of the present invention;

[0038] Figure 3 For the present invention Figure 2 The enlarged structural diagram at A in the middle;

[0039] Figure 4 This is a schematic diagram of the main cross-sectional structure of the horizontal plate of the present invention;

[0040] Figure 5 For the present invention Figure 4 The enlarged structural diagram at B in the middle;

[0041] Figure 6 This is a schematic diagram of the structure of the movable rod of the present invention when it is stored;

[0042] Figure 7 It is a schematic diagram of the connection structure between the arc-shaped abutment block and the vacuum suction cup of the present invention;

[0043] Figure 8 It is a schematic diagram of the internal structure of the horizontal plate of the present invention;

[0044] Fig. 9 It is a schematic diagram of the position structure of the horizontal plate and the limiting slide groove of the present invention;

[0045] Fig.10 It is a schematic diagram of the structure of the fixing component of the present invention.

[0046] In the figure: 1. engine frame; 2. horizontal plate; 3. storage slot; 4. limit slide slot; 5. movable rod; 6. guide rod; 7. threaded groove; 8. magnetic block; 9. protective ball; 10. fixing assembly; 1001. first threaded sleeve; 1002. second threaded sleeve; 11. fixed threaded sleeve; 12. borescope body; 1201. display screen; 1202. operation panel; 1203. exploration wire; 1204. exploration probe; 13. support base; 14. embedded groove; 15. arc-shaped abutment block; 16. vacuum suction cup; 17. built-in groove; 18. fixing rod; 19. supporting rack rod; 20. baffle; 21. electromagnet; 22. connecting block; 23. storage slot; 24. gear mechanism; 25. movable wrench; 26. telescopic spring. DETAILED DESCRIPTION

[0047] 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.

[0048] See also Figure 1-10The present invention provides a technical solution: an aircraft engine inspection tool, including an engine frame 1, a horizontal plate 2, a storage groove 3, a limiting slide groove 4, a movable rod 5, a guide rod 6, a threaded groove 7, a magnetic block 8, a protective ball 9, a fixing assembly 10, a first threaded sleeve 1001, a second threaded sleeve 1002, a fixed threaded sleeve 11, a borescope body 12, a display screen 1201, an operation panel 1202, an exploration wire 1203, an exploration probe 1204, a support base 13, an embedding groove 14, an arc-shaped abutment block 15, a vacuum suction cup 16, a built-in groove 17, a fixing rod 18, a supporting rack rod 19, a baffle 20, an electromagnet 21, a connecting block 22, a storage groove 23, a gear mechanism 24, an adjustable wrench 25 and a telescopic spring 26, an engine frame 1 is provided with a horizontal plate 2 inside, and a storage mechanism is provided inside the horizontal plate 2, and the storage mechanism includes a storage groove 3 and a limiting slide groove 4. The storage groove 3 is provided inside the horizontal plate 2, and the limiting slide groove 4 is provided on the top of the storage groove 3. The design of the storage groove 3 makes it easy to store the movable rod 5, so that after the aircraft engine inspection is completed, the area occupied by the borescope inspection tool is reduced. The width of the limiting slide groove 4 is equal to the diameter of the guide rod 6, and a sliding connection structure is formed between the guide rod 6 and the limiting slide groove 4. When the movable rod 5 is moved, the movable rod 5 slides along the limiting slide groove 4 in the storage groove 3 through the upper guide rod 6, so that the movable rod 5 is more stable when moving and will not deviate. The left and right sides of the horizontal plate 2 are penetrated by The movable rod 5 is provided with a magnetic block 8 on the opposite side of the movable rod 5, and a protective ball 9 is provided on the reverse end of the movable rod 5. When the movable rod 5 is stored, the fixing component 10 is separated from the fixing threaded sleeve 11 on the horizontal plate 2, and the fixing component 10 is rotated to one end away from the horizontal plate 2, and then the movable rods 5 on the left and right sides are relatively moved so that the movable rod 5 is adsorbed by the magnetic block 8, thereby completing the limiting of the movable rod 5 when stored. The movable rod 5 is provided with a guide rod 6, and a threaded groove 7 is provided on the movable rod 5. The movable rod 5 is provided with a fixing component 10, and the fixing component 10 includes a first threaded sleeve 1001 and a second threaded sleeve 1002. The first threaded sleeve 1001 is connected to the second threaded sleeve 1002. The first threaded sleeve 1001 is connected to the second threaded sleeve 1002. The center line coincides with the second threaded sleeve 1002, the first threaded sleeve 1001 is threadedly connected to the fixed threaded sleeve 11, the second threaded sleeve 1002 is threadedly connected to the thread groove 7 on the movable rod 5, the movable rod 5 is pulled outward, and the protective ball 9 on the movable rod 5 is abutted against the inner wall of the surface of the aerospace engine, and then the fixed component 10 is rotated, and the second threaded sleeve 1002 on the fixed component 10 moves along the movable rod 5, thereby driving the first threaded sleeve 1001 to move, so that the first threaded sleeve 1001 moves to the position of the fixed threaded sleeve 11, and the first threaded sleeve 1001 is connected to the fixed threaded sleeve 11, so as to complete the limiting of the movable rod 5, thereby preventing the loosening of the fastening components based on the inspection by abutting the inner wall of the aerospace engine through the movable rod 5.The inspection tool will fall without a support point, so the movable rod 5 can play a protective role. The left and right sides of the horizontal plate 2 are both equipped with fixed threaded sleeves 11;

[0049] A borescope body 12 is installed above the horizontal plate 2. The borescope body 12 includes a display screen 1201, an operation panel 1202, an exploration wire 1203 and an exploration probe 1204. The operation panel 1202 is installed on the borescope body 12, and the display screen 1201 is installed above the operation panel 1202. The exploration wire 1203 is installed above the display screen 1201, and the exploration probe 1204 is installed at the end of the exploration wire 1203. The aircraft engine blades are inspected by the exploration probe 1204 on the exploration wire 1203. The display screen 1201 can display the data of the exploration probe 1204, and the exploration probe 1204 can be controlled by the operation panel 1202.

[0050] A support base 13 is installed below the horizontal plate 2, and an embedding groove 14 is opened on the rear side of the support base 13, and a positioning mechanism is installed on the upper surface of the embedding groove 14, and the positioning mechanism includes an arc-shaped abutment block 15 and a vacuum suction cup 16. An arc-shaped abutment block 15 is installed on the upper surface of the embedding groove 14, and a vacuum suction cup 16 is installed below the arc-shaped abutment block 15. The vacuum suction cup 16 is distributed in an arc-shaped structure, and the vacuum suction cup 16 is detachably connected to the arc-shaped abutment block 15. When the inspection tool needs to be fixed, the vacuum suction cup 16 below the arc-shaped abutment block 15 is abutted against the inner wall of the aircraft engine, and the vacuum suction cup 16 is fixed to the inner wall of the aircraft engine. The vacuum suction cup 16 realizes pre-positioning with the inner wall of the aircraft engine. A built-in groove 17 is opened inside the support base 13, and a fixing rod 18 is installed inside the built-in groove 17. A supporting rack rod 19 is sleeved on the upper part of the fixing rod 18. The center line of the supporting rack rod 19 coincides with the center line of the fixing rod 18, and a sliding connection structure is formed between the supporting rack rod 19 and the fixing rod 18, so that the supporting rack rod 19 can move up and down along the fixing rod 18 when subjected to force. The fixing rod 18 plays a role of limiting and guiding the supporting rack rod 19, so that the supporting rack rod 19 is more stable when it moves up and down under force, and the supporting rack A baffle plate 20 is installed at the lower end of the rod 19, and the baffle plate 20 is connected to the connecting block 22 by a telescopic spring 26. When the inspection tool is disassembled, the electromagnet 21 is directly powered off, and then the supporting rack rod 19 can move downward under the action of gravity and the rebound force of the telescopic spring 26, so that the electromagnet 21 is away from the aircraft engine, and then the inspection tool can be manually pulled out. The electromagnet 21 is installed at the upper end of the supporting rack rod 19, and the connecting block 22 is installed inside the built-in groove 17, and the connection block 22 is provided with a storage groove 23, and the storage groove 23 is installed with a gear mechanism 24, and the gear mechanism 24 can be moved by The rotating shaft is connected to the inside of the storage slot 23, the gear mechanism 24 is connected to the adjustable wrench 25, the adjustable wrench 25 is located outside the support base 13, the gear mechanism 24 is meshed with the supporting rack rod 19, and the supporting rack rod 19 is slidably connected to the connecting block 22. When fixing the inspection tool and the aircraft engine, the gear mechanism 24 can be driven to rotate by the adjustable wrench 25, and the gear mechanism 24 drives the supporting rack rod 19 to move upward, so that the electromagnet 21 at the upper end of the supporting rack rod 19 abuts against the aircraft engine, and the aircraft engine is adsorbed by the electromagnet 21, thereby completing the fixation of the inspection tool.

[0051] Working principle: When using the aircraft engine inspection tool, first, when the inspection tool needs to be fixed, the vacuum suction cup 16 below the arc-shaped abutment block 15 is abutted against the inner wall of the aircraft engine, and the vacuum suction cup 16 is used to achieve pre-positioning with the inner wall of the aircraft engine, and then the movable rod 5 is pulled outward, and the protective ball 9 on the movable rod 5 is abutted against the surface inner wall of the aerospace engine, and then the fixing component 10 is rotated, and the second threaded sleeve 1002 on the fixing component 10 moves along the movable rod 5, thereby driving the first threaded sleeve 1001 to move, so that the first threaded sleeve 1001 moves to the position of the fixed threaded sleeve 11, and the first threaded sleeve 1001 is connected to the fixed threaded sleeve 11, so as to complete the limiting of the movable rod 5, thereby preventing the inspection tool from falling without a support point when the fastening components of the inspection basis are loosened through the abutment of the movable rod 5 with the inner wall of the aircraft engine, so that the movable rod 5 can play a protective role.

[0052] The gear mechanism 24 is driven to rotate by the movable wrench 25, and the gear mechanism 24 drives the supporting rack rod 19 to move upward, so that the electromagnet 21 at the upper end of the supporting rack rod 19 abuts against the aircraft engine, and the aircraft engine is adsorbed by the electromagnet 21, thereby completing the fixing of the inspection tool, and the staff inspects the aircraft engine blades through the exploration probe 1204 on the exploration wire 1203, and the display screen 1201 can display the data of the exploration probe 1204, and the exploration probe 1204 can be controlled by the operation panel 1202. Thus, a series of work is completed. The contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0053] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine inspection tool, comprising an engine frame (1) and a horizontal plate (2), characterized in that: The engine frame (1) is provided with a horizontal plate (2) inside, and a storage mechanism is provided inside the horizontal plate (2), and the storage mechanism comprises a storage groove (3) and a limiting slide groove (4). The storage groove (3) is provided inside the horizontal plate (2), and a limiting slide groove (4) is provided on the top of the storage groove (3). The storage groove (3) stores the movable rod (5), and the movable rod (5) is penetrated on both sides of the horizontal plate (2). The movable rod (5) is installed with a guide rod (6), and a sliding connection structure is formed between the guide rod (6) and the limiting slide groove (4). The movable rod (5) is provided with A threaded groove (7) is provided, the movable rod (5) is provided with a fixing assembly (10), the left and right sides of the horizontal plate (2) are provided with fixing threaded sleeves (11), the fixing assembly (10) comprises a first threaded sleeve (1001) and a second threaded sleeve (1002), the first threaded sleeve (1001) is connected to the second threaded sleeve (1002), the center line of the first threaded sleeve (1001) coincides with the center line of the second threaded sleeve (1002), the first threaded sleeve (1001) is threadedly connected to the fixing threaded sleeve (11), and the second threaded sleeve (1002) is threadedly connected to the threaded groove (7) on the movable rod (5); A borescope body (12) is installed above the horizontal plate (2); A support base (13) is installed below the horizontal plate (2), and an embedding groove (14) is provided on the rear side of the support base (13), and a positioning mechanism is installed on the upper surface of the embedding groove (14); a built-in groove (17) is provided inside the support base (13), and a fixing rod (18) is installed inside the built-in groove (17); a supporting rack rod (19) is sleeved above the fixing rod (18), and a sliding connection structure is formed between the supporting rack rod (19) and the fixing rod (18); an electromagnet is installed on the upper end of the supporting rack rod (19). (21), a connecting block (22) is installed inside the built-in groove (17), and a storage groove (23) is opened inside the connecting block (22), and a gear mechanism (24) is installed in the storage groove (23), the gear mechanism (24) is connected to the inside of the storage groove (23) through a rotating shaft, the gear mechanism (24) is connected to a movable wrench (25), the movable wrench (25) is located outside the support base (13), the gear mechanism (24) is meshed with the support rack rod (19), and the support rack rod (19) is slidably connected to the connecting block (22).

2. The aircraft engine inspection tool according to claim 1, characterized in that: The width of the limiting sliding groove (4) is equal to the diameter of the guide rod (6).

3. The aircraft engine inspection tool according to claim 1, characterized in that: A magnetic attraction block (8) is installed on the opposite side of the movable rod (5), and a protective ball (9) is installed on the opposite end of the movable rod (5).

4. The aircraft engine inspection tool according to claim 1, characterized in that: The borescope body (12) comprises a display screen (1201), an operation panel (1202), an exploration wire (1203) and an exploration probe (1204); the operation panel (1202) is installed on the borescope body (12), the display screen (1201) is installed above the operation panel (1202), the exploration wire (1203) is installed above the display screen (1201), and the exploration probe (1204) is installed at the end of the exploration wire (1203).

5. The aircraft engine inspection tool according to claim 1, characterized in that: The positioning mechanism comprises an arc-shaped abutment block (15) and a vacuum suction cup (16); the arc-shaped abutment block (15) is mounted on the upper surface of the embedded groove (14), and the vacuum suction cup (16) is mounted below the arc-shaped abutment block (15); the vacuum suction cup (16) is distributed in an arc-shaped structure, and the vacuum suction cup (16) and the arc-shaped abutment block (15) are detachably connected.

6. The aircraft engine inspection tool according to claim 1, characterized in that: The center line of the supporting rack rod (19) coincides with the center line of the fixing rod (18).

7. The aircraft engine inspection tool according to claim 1, characterized in that: A baffle (20) is installed at the lower end of the supporting rack rod (19), and the baffle (20) is connected to the connecting block (22) via a telescopic spring (26).

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