Detection equipment for external damage of ground test-run aero-engine

Abstract

The utility model relates to a device for detecting external damage of a ground test run aero-engine, which belongs to the technical field of aero-engine external damage detection and comprises a bottom box, and an omnibearing detection component is arranged at the top of the bottom box. The omni-directional detection assembly comprises a vertical frame and a circular truncated cone which are fixedly connected to the top of the bottom box, an air cylinder is fixedly connected to the top of the vertical frame, a detection cover is fixedly connected to an output shaft of the air cylinder, an infrared scanning device is fixedly connected to the inner side of the detection cover, and a first gear is fixedly connected to an output shaft of a motor; and the outer surface of the rotating shaft is fixedly connected with a second gear. According to the detection equipment for the external damage of the ground test-run aero-engine, the aero-engine can be automatically and comprehensively detected, so that compared with existing detection equipment, workers do not need to continuously move the detection equipment to continuously adjust the position, the detection time is short, and the detection efficiency is effectively improved.

Description

Technical Field

[0001] This utility model relates to the field of external damage detection technology for aero-engines, specifically a detection device for external damage of a ground-based aero-engine undergoing trial operation. Background Technology

[0002] An aircraft engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers flight but also serves as a vital driving force for the development of the aviation industry.

[0003] During the production or ground testing of aircraft engines, inspection equipment is needed to check their exterior to confirm whether there is any damage. Currently available inspection equipment can use infrared scanning devices to scan the exterior of aircraft engines to accurately detect damage.

[0004] However, multiple surfaces and parts of an aircraft engine need to be inspected. Currently available inspection equipment cannot automatically perform all-round inspections of aircraft engines. It requires staff to constantly move the inspection equipment to adjust its position, resulting in long inspection times and severely reducing inspection efficiency. Therefore, a ground-based inspection equipment for detecting external damage to aircraft engines is proposed to solve the problems mentioned above. Utility Model Content

[0005] To address the shortcomings of existing technologies, this utility model provides a ground-based detection device for external damage to aircraft engines. This device solves the problem that current detection equipment cannot automatically perform comprehensive inspections of aircraft engines, requiring staff to constantly move the equipment to adjust its position, resulting in long inspection times and severely reduced inspection efficiency.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a detection device for external damage of a ground-based aircraft engine, comprising a base box, wherein an all-around detection component is provided on the top of the base box;

[0007] The omnidirectional detection assembly includes a stand and a frustum fixedly connected to the top of the base box. A cylinder is fixedly connected to the top of the stand, and a detection cover is fixedly connected to the output shaft of the cylinder. An infrared scanning device is fixedly connected to the inner side of the detection cover. A positioning plate is fixedly connected to the top of the frustum. A rotating shaft is rotatably connected to the inner bottom wall of the frustum. A turntable is fixedly connected to the top of the rotating shaft. A rotating groove is opened on the top of the positioning plate. A motor is fixedly connected inside the frustum. A first gear is fixedly connected to the output shaft of the motor, and a second gear is fixedly connected to the outer surface of the rotating shaft.

[0008] Furthermore, the outer diameter of the turntable is smaller than the inner diameter of the rotating groove, and the top end of the rotating shaft passes through the positioning plate and extends to the inner side of the rotating groove.

[0009] Furthermore, the first gear meshes with the second gear for transmission, and the outer diameter of the detection cover is the same as that of the turntable.

[0010] Furthermore, a sliding rod is fixedly connected to the inner side of the support frame, and movable blocks are fixedly connected to the left and right sides of the detection cover, with the movable blocks slidably connected to the sliding rod.

[0011] Furthermore, a magnetic suction platform for adsorption and fixation is fixedly connected to the top of the turntable.

[0012] Furthermore, a fan is fixedly connected to the right side of the bottom box, and a collection sponge is adhered to the inside of the bottom box.

[0013] Furthermore, the front of the base box is hinged to a movable door for sealing, and a door handle is fixedly connected to the outer surface of the movable door.

[0014] Furthermore, the base box, the upright frame, and the truncated cone are all steel structures.

[0015] Furthermore, heat dissipation vents are provided on both the front and back of the frustum.

[0016] Furthermore, a filter grille is fixedly connected to the inner side of the heat dissipation vent, and the filter grille is made of wire mesh.

[0017] Compared with the prior art, this utility model provides a detection device for external damage of ground-based aircraft engines undergoing trial operation, which has the following beneficial effects:

[0018] The ground test is running equipment for detecting external damage to aircraft engines. Through a comprehensive detection component, it can automatically perform a full-range inspection of the aircraft engine. During the inspection, the aircraft engine is enclosed inside the inspection cover and rotates continuously on top of the turntable. This allows the infrared scanning device inside the inspection cover to automatically scan multiple surfaces and parts of the aircraft engine. Compared with existing inspection equipment, it eliminates the need for staff to constantly move the inspection equipment to adjust its position, and the inspection time is shorter, effectively improving inspection efficiency. Attached Figure Description

[0019] Figure 1 This is a cross-sectional view of the structure of this utility model;

[0020] Figure 2 This is a top view of the positioning disk of this utility model;

[0021] Figure 3 This is a front view of the structure of this utility model;

[0022] Figure 4 This is a three-dimensional view of the structure of the frustum of this utility model.

[0023] In the diagram: 1. Base box, 2. Stand, 3. Frustum, 4. Cylinder, 5. Detection cover, 6. Infrared scanning device, 7. Positioning plate, 8. Rotating shaft, 9. Turntable, 10. Rotating groove, 11. Motor, 12. First gear, 13. Second gear, 14. Sliding rod, 15. Moving block, 16. Magnetic platform, 17. Fan, 18. Collection sponge, 19. Movable door, 20. Heat dissipation vent, 21. Filter grille. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] Example 1:

[0026] Please see Figures 1 to 2 This embodiment provides a ground-based test device for detecting external damage to an aircraft engine, including a base box 1, with an all-around detection assembly mounted on the top of the base box 1.

[0027] The all-around inspection assembly includes a stand 2 and a frustum 3 fixedly connected to the top of the base box 1. A cylinder 4 is fixedly connected to the top of the stand 2. An inspection cover 5 is fixedly connected to the output shaft of the cylinder 4. An infrared scanning device 6 is fixedly connected to the inner side of the inspection cover 5. A positioning plate 7 is fixedly connected to the top of the frustum 3. A rotating shaft 8 is rotatably connected to the inner bottom wall of the frustum 3. A turntable 9 is fixedly connected to the top of the rotating shaft 8. A rotating groove 10 is opened on the top of the positioning plate 7. A motor 11 is fixedly connected to the inside of the frustum 3. A first gear 12 is fixedly connected to the output shaft of the motor 11. A second gear 13 is fixedly connected to the outer surface of the rotating shaft 8. In use, the operator first needs to hoist the aircraft engine to the top of the turntable 9. Then, the cylinder 4 is started, which drives the inspection cover 5 to move vertically downward, so that the aircraft engine is covered inside the inspection cover 5.

[0028] Once the aircraft engine is completely covered by the inspection cover 5, the motor 11 is started. Through the meshing transmission of the first gear 12 and the second gear 13, the rotating shaft 8 is driven to rotate in the opposite direction to the output shaft of the motor 11, thereby causing the aircraft engine to rotate continuously on the top of the turntable 9. At this time, the infrared scanning device 6 is turned on, which can automatically scan multiple surfaces and parts of the aircraft engine to inspect its exterior and confirm whether there is any damage.

[0029] It should be noted that the outer diameter of the turntable 9 is smaller than the inner diameter of the rotating groove 10, and the top of the rotating shaft 8 passes through the positioning plate 7 and extends to the inner side of the rotating groove 10.

[0030] It should be understood that the first gear 12 and the second gear 13 mesh and drive each other, and the outer diameter of the detection cover 5 and the turntable 9 are the same.

[0031] The inner side of the support frame 2 is fixedly connected to a sliding rod 14, and the left and right sides of the detection cover 5 are fixedly connected to moving blocks 15. The moving blocks 15 are slidably connected to the sliding rod 14. By setting the moving blocks 15 and the sliding rod 14, the sliding limit detection cover 5 is achieved.

[0032] Meanwhile, a magnetic platform 16 for adsorption and fixation is fixedly connected to the top of the turntable 9.

[0033] In addition, a fan 17 is fixedly connected to the right side of the bottom box 1, and a collecting sponge 18 is glued to the inside of the bottom box 1. By setting up the fan 17 and the collecting sponge 18, after the aircraft engine is inspected, it can be placed inside the bottom box 1. The fan 17 blows away the oily debris on its outer surface and in the gaps, and the collecting sponge 18 collects and adheres to it for easy cleaning.

[0034] Example 2:

[0035] Please see Figures 3 to 4 Based on Embodiment 1, the bottom box 1 is hinged to the front of a movable door 19 for sealing, and a door handle is fixedly connected to the outer surface of the movable door 19. The bottom box 1, the upright frame 2 and the truncated cone 3 are all steel structures.

[0036] The truncated cone 3 has heat dissipation vents 20 on both the front and back sides. A filter grille 21 is fixedly connected to the inner side of the heat dissipation vent 20. The filter grille 21 is made of wire mesh. By setting the heat dissipation vent 20 and the filter grille 21, the effects of ventilation and heat dissipation and dust interception are achieved.

[0037] The working principle of the above embodiments is as follows:

[0038] In use, the operator first needs to hoist the aircraft engine to the top of the turntable 9. Then, the cylinder 4 is started, which drives the inspection cover 5 to move vertically downward, so that the aircraft engine is covered inside the inspection cover 5. After the aircraft engine is completely covered by the inspection cover 5, the motor 11 is started. Through the meshing transmission of the first gear 12 and the second gear 13, the rotating shaft 8 is driven to rotate in the opposite direction to the output shaft of the motor 11, so that the aircraft engine rotates continuously on the top of the turntable 9. At this time, the infrared scanning device 6 is turned on, which can automatically scan multiple surfaces and parts of the aircraft engine to check its exterior and confirm whether there is any damage.

[0039] The installation, connection, or setting methods disclosed in this embodiment are all common mechanical connection methods. Any method that can achieve its beneficial effect can be implemented. In addition, the electrical components in this embodiment are all electrically connected to the main controller and the power supply. The main controller can be a conventional known device such as a computer that plays a control role. Those skilled in the art can control the electrical components through simple programming. Moreover, the existing disclosed power connection technology is also common knowledge in the field. Therefore, the specific structural composition and working principle will not be described in detail in this embodiment.

[0040] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0041] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A detection device for external damage of a ground-based aircraft engine undergoing trial operation, comprising a base box (1), characterized in that: The top of the base box (1) is equipped with an all-around detection component; The omnidirectional detection assembly includes a stand (2) and a frustum (3) fixedly connected to the top of the base box (1). A cylinder (4) is fixedly connected to the top of the stand (2). A detection cover (5) is fixedly connected to the output shaft of the cylinder (4). An infrared scanning device (6) is fixedly connected to the inner side of the detection cover (5). A positioning plate (7) is fixedly connected to the top of the frustum (3). A rotating shaft (8) is rotatably connected to the inner bottom wall of the frustum (3). A turntable (9) is fixedly connected to the top of the rotating shaft (8). A rotating groove (10) is opened on the top of the positioning plate (7). A motor (11) is fixedly connected inside the frustum (3). A first gear (12) is fixedly connected to the output shaft of the motor (11). A second gear (13) is fixedly connected to the outer surface of the rotating shaft (8).

2. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The outer diameter of the turntable (9) is smaller than the inner diameter of the rotating groove (10), and the top end of the rotating shaft (8) passes through the positioning plate (7) and extends to the inside of the rotating groove (10).

3. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The first gear (12) meshes with the second gear (13) for transmission, and the outer diameter of the detection cover (5) is the same as that of the turntable (9).

4. The detection equipment for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: A sliding rod (14) is fixedly connected to the inner side of the stand (2), and a moving block (15) is fixedly connected to the left and right sides of the detection cover (5). The moving block (15) is slidably connected to the sliding rod (14).

5. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The top of the turntable (9) is fixedly connected to a magnetic platform (16) for adsorption and fixation.

6. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: A fan (17) is fixedly connected to the right side of the bottom box (1), and a collecting sponge (18) is adhered to the inside of the bottom box (1).

7. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The bottom box (1) is hinged to the front with a movable door (19) for sealing, and a door handle is fixedly connected to the outer surface of the movable door (19).

8. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The base box (1), the upright frame (2), and the truncated cone (3) are all steel structures.

9. The detection device for external damage of a ground-based operational aircraft engine according to claim 1, characterized in that: The frustum (3) has heat dissipation vents (20) on both the front and back sides.

10. The detection device for external damage of a ground-based operational aircraft engine according to claim 9, characterized in that: A filter grille (21) is fixedly connected to the inner side of the heat dissipation vent (20), and the filter grille (21) is made of wire mesh.

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