Aircraft engine blade strength detection tool
By using protective shells and sponge pads to protect the flaw detection assembly in the aircraft engine blade detection tooling, the problem of easy head damage is solved, and a longer service life and wider adaptive detection capability is achieved.
Patent Information
- Application Number
- CN202420654081.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-01
- Publication Date
- 2024-12-13
- Estimated Expiration
- 2034-04-01
AI Technical Summary
The magnetic heads of existing magnetic powder detectors are prone to collision with external objects when not in use, resulting in damage and reducing service life.
An aircraft engine blade strength detection tool is designed, using protective shells and sponge pads to protect the flaw detection assembly, reduce external collision damage, and adapt to blades of different sizes and thicknesses through an adjustable structure, combined with searchlights and control switches for inspection.
It effectively extends the service life of the flaw detection assembly, improves the detection ability of blades of different sizes and thicknesses, and ensures the accuracy and safety of detection.
Smart Images
Figure CN222166933U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of engine blade detection, in particular to an aircraft engine blade strength detection tool. Background Art
[0002] Aircraft engine blades are an important part of the engine. Engine blades are usually designed into aerodynamic shapes to improve engine efficiency and performance. Aircraft engine blades are components in the engine that undertake key functions such as compression, acceleration, and combustion. Their working status directly affects the performance of the engine and flight safety. Through strength testing, cracks, defects and other problems in the blades can be discovered in time to avoid accidents caused by blade failure.
[0003] Magnetic particle detection is a non-destructive detection method that will not cause damage to aircraft engine blades or affect their normal use. It is a safe and reliable detection method. However, the magnetic heads of most magnetic particle detectors are directly exposed on the outside of the detection body. If the magnetic head collides with an external object when not in use, it will cause damage to the magnetic head and reduce its service life. Utility Model Content
[0004] In view of the fact that the magnetic heads of most magnetic particle detectors in the prior art are directly exposed outside the detection body, if the magnetic head collides with an external object when not in use, it will cause damage to the magnetic head and reduce the service life of the magnetic head. The utility model designs an aircraft engine blade strength detection tool.
[0005] The utility model solves the technical problem by adopting the following technical solution: an aircraft engine blade strength detection tool, comprising a detection body, a gripping handle is arranged at the top of the detection body, a receiving groove for receiving a flaw detection component is arranged at the bottom of the detection body, a searchlight for flaw detection of the engine blade is arranged inside the receiving groove, a control switch for controlling the flaw detection component and the searchlight is arranged at the bottom of the gripping handle, and the control switch is electrically connected with the flaw detection component and the searchlight;
[0006] The bottom end of the detection body is slidably connected with a protective shell to reduce the damage of the flaw detection component to the outside; a sponge pad is arranged at one end of the protective shell close to the flaw detection component to reduce the damage of the outside; two ends of the detection body are symmetrically provided with snap-in grooves for facilitating the snap-in installation of the protective shell; a snap-in slide rod is fixed inside the protective shell to be slidably connected with the snap-in slide rod; the snap-in slide rod is symmetrically fixed inside the protective shell.
[0007] Preferably, the flaw detection assembly includes a connecting block rotatably connected to the detection body, an adjusting block slidably inside the connecting block, and a sliding block slidably connected inside the adjusting block. A limiting groove is provided at the top of the connecting block for limiting the limiting rod, and the limiting grooves are also provided at both ends of the detection body.
[0008] Preferably, a fastening screw groove for fixing with a fastening screw is opened at one end of the adjusting block, and the fastening screw grooves are symmetrically and evenly opened at both ends of the adjusting block, and the fastening screw grooves are also symmetrically opened at both ends of the connecting block.
[0009] Preferably, sliding rods slidably connected to the sliding grooves are symmetrically fixed at both ends of the sliding block, and the sliding grooves are symmetrically opened inside the sliding block.
[0010] Preferably, a rotating rod rotatably connected to a rotating plate is disposed at the bottom end of the sliding block, a through slot for increasing the thickness of different engine blades is opened at one end of the rotating plate, and the through slot is rotatably abutted against the rotating rod.
[0011] Preferably, a detection magnetic head for detecting internal damage of the engine blades is fixedly provided at the bottom end of the rotating plate.
[0012] Preferably, the sponge pad is made of shock-proof and collision-proof polystyrene material.
[0013] Beneficial effects of the utility model:
[0014] (1) When the staff needs to perform strength testing on the aircraft engine blade, first apply magnetic powder on its surface, then separate the protective shell from the testing body through the clamping slide groove and the clamping slide rod, then pull the limit rod out of the limit groove at one end of the testing body and the connecting block, and then rotate the connecting block to take it out from the accommodating groove at the bottom of the testing body. The accommodating groove, the protective shell and the sponge pad inside the protective shell can protect the flaw detection component, reduce the force on the flaw detection component due to external collision, and increase the service life of the flaw detection component;
[0015] (2) The adjusting block is slid out from the inside of the connecting block. When it is pulled to the required detection width, the fastening screw is threadedly fixed by passing the fastening screw through the fastening screw grooves at both ends of the connecting block and the adjusting block. Through the connection between the adjusting block, the fastening screw groove, the fastening screw and the connecting block, the staff can adjust the flaw detection assembly to perform strength detection on aircraft engine blades of different widths.
[0016] (3) Slide the sliding block out from the inside of the adjusting block, and pull out the rotating plate inside the sliding block. At this time, the rotating rod at the bottom of the sliding block and the through slot at one end of the rotating plate can be used to test the strength of aircraft engine blades of different thicknesses. After adjusting the flaw detection component, the staff controls the searchlight and the detection magnetic head by holding the control switch at the bottom of the handle to test the strength of the engine blades. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The utility model is further described below in conjunction with the accompanying drawings and embodiments.
[0018] Figure 1 A schematic diagram of the overall structure of an aircraft engine blade strength testing tool provided by the utility model;
[0019] Figure 2 A schematic diagram of the cross-sectional structure of the detection body provided by the utility model;
[0020] Figure 3 for Figure 2 A magnified image of point A;
[0021] Figure 4 A schematic diagram of the expanded structure of the detection subject provided by the utility model;
[0022] Figure 5 A schematic diagram of the structure of the flaw detection assembly provided by the utility model;
[0023] Figure 6 The present invention is a schematic diagram of the cross-sectional structure of the flaw detection assembly provided by the present invention.
[0024] In the figure: 1. Detection body; 2. Holding handle; 3. Accommodation groove; 4. Flaw detection component; 41. Connection block; 42. Limiting groove; 43. Adjustment block; 44. Fastening screw groove; 45. Fastening screw; 46. Sliding block; 47. Sliding groove; 48. Sliding rod; 49. Rotating rod; 410. Rotating plate; 411. Through groove; 412. Detection head; 5. Control switch; 6. Protective shell; 7. Searchlight; 8. Sponge pad; 9. Snap-in slide rod; 10. Snap-in slide groove; 11. Limiting rod. DETAILED DESCRIPTION
[0025] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further described below in conjunction with specific implementation methods.
[0026] Embodiment 1:
[0027] like Figure 1-Figure 6 As shown, the utility model is an aircraft engine blade strength detection tool, comprising a detection body 1, a gripping handle 2 is arranged at the top of the detection body 1, a receiving groove 3 for receiving a flaw detection component 4 is provided at the bottom of the detection body 1, a searchlight 7 for flaw detection of the engine blade is arranged inside the receiving groove 3, a control switch 5 for controlling the flaw detection component 4 and the searchlight 7 is arranged at the bottom of the gripping handle 2, and the control switch 5 is electrically connected to the flaw detection component 4 and the searchlight 7;
[0028] A protective shell 6 for reducing the damage caused by external collisions to the flaw detection component 4 is slidably connected at the bottom end of the detection body 1. A sponge pad 8 for reducing the damage caused by external collisions is arranged at one end of the protective shell 6 close to the flaw detection component 4. Clamping grooves 10 for facilitating the clamping and installation of the protective shell 6 are symmetrically provided at both ends of the detection body 1, and a clamping slide rod 9 for slidably clamping with the clamping slide groove 10 is fixed inside the protective shell 6. The clamping slide rod 9 is symmetrically fixed inside the protective shell 6. The protective shell 6 slidably connected to the detection body 1 and the sponge pad 8 inside the protective shell 6 can effectively reduce the damage caused by external collisions to the flaw detection component 4 and increase the service life of the flaw detection component 4.
[0029] In this embodiment, the flaw detection component 4 includes a connecting block 41 rotatably connected to the detection body 1, an adjusting block 43 slidably inside the connecting block 41, and a sliding block 46 slidably connected to the inside of the adjusting block 43. A limiting groove 42 is provided at the top of the connecting block 41 for limiting the limiting rod 11, and the limiting groove 42 is also provided at both ends of the detection body 1; through the limiting groove 42 and the limiting rod 11, the staff can conveniently take out and store the flaw detection component 4 in the accommodating groove 3 to protect the flaw detection component 4.
[0030] In this embodiment, a fastening screw groove 44 for fixing with a fastening screw 45 is opened at one end of the adjustment block 43, and the fastening screw groove 44 is symmetrically and evenly opened at both ends of the adjustment block 43, and the fastening screw groove 44 is also symmetrically opened at both ends of the connecting block 41; through the relationship between the fastening screw groove 44, the fastening screw 45 and the adjustment block 43, the flaw detection component 4 can be increased to detect engine blades of different widths, thereby increasing the functionality of the flaw detection component 4.
[0031] Specifically, sliding rods 48 slidably connected to the sliding grooves 47 are symmetrically fixed at both ends of the sliding block 46 , and the sliding grooves 47 are symmetrically arranged inside the sliding block 46 .
[0032] In this embodiment, a rotating rod 49 rotatably connected to a rotating plate 410 is provided at the bottom end of the sliding block 46, and a through slot 411 for increasing the thickness of different engine blades is opened at one end of the rotating plate 410, and the through slot 411 is rotatably abutted against the rotating rod 49; through the connection between the rotating plate 410, the rotating rod 49 and the through slot 411, the flaw detection component 4 can be increased to perform flaw detection on engine blades of different thicknesses, thereby increasing the usability of the flaw detection component.
[0033] Specifically, a detection magnetic head 412 for detecting internal damage of the engine blade is fixedly provided at the bottom end of the rotating plate 410; through the magnetic head 412, tiny surface defects and cracks of the aircraft engine blade can be detected, and even hidden areas can be effectively detected.
[0034] In this embodiment, the sponge pad 8 is made of shock-proof and collision-proof polystyrene material; since the polystyrene material has excellent light weight, shock-proof and collision-proof properties, it can effectively reduce the external damage to the flaw detection component 4.
[0035] Embodiment 2:
[0036] On the basis of Example 1, the sponge pad 8 can be replaced by a polyurethane material with shock-proof and collision-proof properties or a material with the same performance, which provides an effect similar to that of the sponge pad 8 .
[0037] Working principle: When the staff needs to perform strength test on the aircraft engine blade, first apply magnetic powder on its surface, then separate the protective shell 6 from the detection body 1 through the snap-in slide groove 10 and the snap-in slide rod 9, then pull the limit rod 11 out of the detection body 1 and the limit groove 42 at one end of the connecting block 41, then rotate the connecting block 41 to take it out from the accommodating groove 3 at the bottom of the detection body 1, and the flaw detection component 4 can be protected by the accommodating groove 3, the protective shell 6 and the sponge pad 8 inside the protective shell 6, reduce the force on the flaw detection component 4 due to external collision, and increase the service life of the flaw detection component 4, then slide the adjustment block 43 out from the inside of the connecting block 41, and when it is pulled to the required detection width, insert the fastening screw 45 through the connecting block 41 to adjust the adjustment block 43. The connecting block 41 is threadedly fixed with the fastening screw grooves 44 at both ends of the adjusting block 43. Through the connection between the adjusting block 43, the fastening screw grooves 44, the fastening screws 45 and the connecting block 41, the staff can conveniently adjust the flaw detection component 4 to perform strength testing on aircraft engine blades of different widths. Then, the sliding block 46 is slid out from the inside of the adjusting block 43, and the rotating plate 410 inside the sliding block 46 is pulled out. At this time, the rotating rod 49 at the bottom end of the sliding block 46 and the through groove 411 at one end of the rotating plate 410 can perform strength testing on aircraft engine blades of different thicknesses. After adjusting the flaw detection component 4, the staff controls the searchlight 7 and the detection magnetic head 412 to perform strength testing on the engine blades by holding the control switch 5 at the bottom of the handle 2.
[0038] The above shows and describes the basic principles, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions in the specification are only to illustrate the principles of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the protection required by the utility model. The scope of protection required by the utility model is defined by the attached claims and their equivalents.
Claims
1. An aircraft engine blade strength testing tool, characterized in that: The invention comprises a detection body (1), wherein a gripping handle (2) is arranged at the top of the detection body (1), a receiving groove (3) for receiving a flaw detection component (4) is arranged at the bottom of the detection body (1), a searchlight (7) for detecting flaws on engine blades is arranged inside the receiving groove (3), a control switch (5) for controlling the flaw detection component (4) and the searchlight (7) is arranged at the bottom of the gripping handle (2), and the control switch (5) is electrically connected to the flaw detection component (4) and the searchlight (7); The bottom end of the detection body (1) is slidably engaged with a protective shell (6) for reducing damage to the flaw detection component (4) from external collisions. A sponge pad (8) for reducing damage from external collisions is arranged at one end of the protective shell (6) close to the flaw detection component (4). Both ends of the detection body (1) are symmetrically provided with engaging grooves (10) for facilitating the engaging and installing the protective shell (6). The protective shell (6) is fixedly provided with an engaging slide rod (9) for slidably engaging with the engaging slide groove (10). The engaging slide rod (9) is symmetrically fixed inside the protective shell (6).
2. The aircraft engine blade strength testing tool according to claim 1, characterized in that: The flaw detection assembly (4) comprises a connecting block (41) rotatably connected to the detection body (1), an adjusting block (43) slidably inside the connecting block (41), and a sliding block (46) slidably connected inside the adjusting block (43); a limiting groove (42) for limiting the limiting rod (11) is provided at the top end of the connecting block (41), and the limiting groove (42) is also provided at both ends of the detection body (1).
3. The aircraft engine blade strength testing tool according to claim 2 is characterized by: A fastening screw groove (44) for fixing the fastening screw rod (45) is provided at one end of the adjusting block (43), and the fastening screw groove (44) is symmetrically and evenly provided at both ends of the adjusting block (43). The fastening screw groove (44) is also symmetrically provided at both ends of the connecting block (41).
4. The aircraft engine blade strength testing tool according to claim 2, characterized in that: Sliding rods (48) slidably connected to the sliding grooves (47) are symmetrically fixed at both ends of the sliding block (46), and the sliding grooves (47) are symmetrically arranged inside the sliding block (46).
5. The aircraft engine blade strength testing tool according to claim 2, characterized in that: A rotating rod (49) rotatably connected to a rotating plate (410) is disposed at the bottom end of the sliding block (46); a through slot (411) for increasing the thickness of different engine blades is opened at one end of the rotating plate (410); and the through slot (411) is rotatably abutted against the rotating rod (49).
6. The aircraft engine blade strength testing tool according to claim 5, characterized in that: A detection magnetic head (412) for detecting internal damage of the engine blades is fixedly arranged at the bottom end of the rotating plate (410).
7. The aircraft engine blade strength testing tool according to claim 1, characterized in that: The sponge pad (8) is made of shock-proof and collision-proof polystyrene material.