Aero-engine blade shifting device

Abstract

The utility model discloses an aero-engine blade poking device, and relates to the technical field of aero-engine blade detection. Comprising a body, a stirring assembly is arranged on one side of the body, the side, away from the stirring assembly, of the body is detachably connected with a robot through a connecting piece, a clamping assembly is arranged between the stirring assembly and the connecting piece and arranged on one side of the body, and a clamping assembly is arranged in the middle of the outer wall of the side, provided with the clamping assembly, of the body. A guide component is arranged on the bottom surface of one end of the body away from the connector; the clamping assembly comprises a supporting rod, one end of the supporting rod is fixedly connected with the side wall of the end, close to the connecting piece, of the body, and a clamping groove is reserved between the supporting rod and the body. According to the utility model, the support plate can be clamped in the clamping groove through the clamping assembly, so that the body cannot move back and forth or left and right; the blade is toggled through the toggling assembly, the blade can be toggled automatically, manual labor is effectively reduced, and the detection efficiency of the aero-engine blade is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engine blade detection, in particular to an aero-engine blade shifting device. Background Art

[0002] The blades on the front end of an aircraft engine are usually called "first-stage fan rotor blades or first-stage fan blades", while the blades on the tail nozzle are usually called "low-pressure turbine blades"; currently, the front end of an aircraft engine generally has a support plate, which is a fixed device. The cross-sectional shape of the support plate has various styles, some are curved, and some are airfoil-shaped. There is a certain angle between the leading edge plate and the trailing edge plate of the curved support plate.

[0003] The blades need to be inspected regularly. When the first-stage fan blades or low-pressure turbine blades need to be tested by turning them, a certain amount of external force needs to be applied to rotate the blades in a free state. Usually, a person carries a flashlight and climbs into the aircraft air intake, close to the end face of the engine, and uses his eyes to turn the blades to observe whether there are any abnormalities. Or when it is inconvenient for the inspector to get close to the blades, a hand-cranked lever is used to turn the blades from a distance, and the blade status is observed through a telescope.

[0004] These two methods are relatively traditional. The space inside the air inlet is narrow and long, making it inconvenient for personnel to crawl and they need to wear protective clothing to enter. The air inlet is hot and stuffy in summer and cold in winter, which means that personnel cannot spend too long inspecting inside. In addition, the aircraft often needs to be inspected shortly after completing its mission and landing. The temperature inside the air inlet is too high for personnel to enter. Therefore, there is an urgent need for an aircraft engine blade moving device that can replace the manual movement of the engine's first-stage fan blades or low-pressure turbine blades, realize automatic movement of the blades, reduce manual labor, and improve the inspection efficiency of aircraft engine blades. Utility Model Content

[0005] The utility model aims to provide an aero-engine blade shifting device to solve the problems existing in the above-mentioned prior art.

[0006] To achieve the above-mentioned purpose, the utility model provides the following solution: the utility model provides an aircraft engine blade shifting device, including a main body, a shifting assembly is provided on one side of the main body, and the side of the main body away from the shifting assembly is detachably connected to a robot through a connecting piece, a locking assembly is provided between the shifting assembly and the connecting piece, and the locking assembly is provided on one side of the main body, and a clamping assembly is provided on the middle part of the outer wall of the side where the locking assembly is provided, and a guide assembly is provided on the bottom surface of one end of the main body away from the connecting piece; the locking assembly includes a support rod, one end of the support rod is fixedly connected to the side wall of one end of the main body close to the connecting piece, and a locking groove is left between the support rod and the main body.

[0007] Preferably, the shifting assembly comprises a first mechanical arm installed in the main body, and one end of the first mechanical arm extending out of the main body is rotatably connected to a first roller.

[0008] Preferably, the support rod is arranged in an L shape.

[0009] Preferably, one end of the support rod away from the body is rotatably connected to a second roller.

[0010] Preferably, the clamping assembly includes a positioning groove provided on the main body, one end of the second mechanical arm is installed in the positioning groove, and a positioning arm is installed at the other end of the second mechanical arm.

[0011] Preferably, the guide assembly includes a plurality of guide rollers, the guide rollers are arranged below the first mechanical arm, and the guide rollers are rotatably connected to the bottom surface of the body.

[0012] Preferably, a camera is fixedly connected to the main body.

[0013] The utility model discloses the following technical effects:

[0014] The utility model drives the main body to move in the air inlet duct by the robot, and when the support plate is inserted into the clamping groove, the support plate can be clamped in the clamping groove by the clamping component, so that the main body will not move forward and backward or left and right; then, the blades can be moved by the toggling component, and the blades can be automatically moved, which effectively reduces manual labor and improves the detection efficiency of aircraft engine blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 This is a schematic diagram of the top view structure of the utility model;

[0017] Figure 2 This is a side view of the structure of the utility model;

[0018] Figure 3 This is a schematic diagram of the structure of the utility model when the blades are moved on the curved support plate;

[0019] Figure 4 This is a schematic diagram of the structure of the utility model when it is used on an airfoil support plate to move blades;

[0020] Among them, 1. main body; 2. first roller; 3. positioning arm; 4. positioning groove; 5. guide roller; 11. connecting piece; 12. positioning groove; 21. first mechanical arm; 31. second mechanical arm; 41. support rod; 42. second roller. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0022] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0023] Embodiment 1

[0024] Reference Figure 1 - Figure 2 The utility model discloses an aircraft engine blade shifting device, comprising a main body 1, a shifting assembly is arranged on one side of the main body 1, a side of the main body 1 away from the shifting assembly is detachably connected to a robot through a connecting piece 11, a positioning assembly is arranged between the shifting assembly and the connecting piece 11, the positioning assembly is arranged on one side of the main body 1, a clamping assembly is arranged on the middle part of the outer wall of the side where the positioning assembly is arranged, and a guide assembly is arranged on the bottom surface of one end of the main body 1 away from the connecting piece 11; the positioning assembly comprises a support rod 41, one end of the support rod 41 is fixedly connected to the side wall of one end of the main body 1 close to the connecting piece 11, and a positioning groove 4 is left between the support rod 41 and the main body 1.

[0025] The connecting member 11 can install the body 1 on the robot in a horizontally suspended manner through the pin shaft, that is, the robot lifts the body 1 to move, and the body 1 can be rotated upward along the pin shaft through the pin shaft.

[0026] The utility model drives the main body 1 to move in the air inlet duct through the robot. When the support plate is inserted into the clamping groove 4, the support plate can be clamped in the clamping groove 4 through the clamping component, so that the main body 1 will not move forward and backward or left and right. Then, the blades can be moved through the toggling component, and the blades can be automatically moved, which effectively reduces manual labor and improves the detection efficiency of aircraft engine blades.

[0027] According to a further optimized solution, the toggle assembly includes a first mechanical arm 21 installed in the main body 1 , and one end of the first mechanical arm 21 extending outside the main body 1 is rotatably connected to the first roller 2 .

[0028] The first mechanical arm 21 can drive the first roller 2 to be between the two blades, and the first mechanical arm 21 can drive the first roller 2 to move in a trajectory similar to an ellipse, so that the first roller 2 can move the blades, and the first roller 2 can enter between the two blades. When the first roller 2 contacts the blades, the rolling of the first roller 2 on the blades can move the blades, and the rotation of the blades is realized through the reciprocating cycle of the first roller 2.

[0029] In order to prevent the first roller 2 from scratching the blades, the first roller 2 is made of engineering plastics with lower hardness than the blades, such as POM or PTFE.

[0030] In a further optimized solution, the support rod 41 is arranged in an L shape, so that the support plate can be effectively inserted into the clamping groove 4.

[0031] In a further optimized solution, the end of the support rod 41 away from the body 1 is rotatably connected to a second roller 42. Through the guidance of the second roller 42, the support plate will not collide with the support rod 41, and the support plate can be stably placed in the clamping groove 4.

[0032] According to a further optimized solution, the clamping assembly includes a positioning groove 12 provided on the main body 1 , one end of the second mechanical arm 31 is installed in the positioning groove 12 , and the positioning arm 3 is installed at the other end of the second mechanical arm 31 .

[0033] The second mechanical arm 31 drives the positioning arm 3 to move, so that the positioning arm 3 can abut against the support plate, limit the support plate, and prevent the support plate from moving in the clamping groove 4.

[0034] In a further optimized solution, the guide assembly includes a plurality of guide rollers 5, which are arranged below the first mechanical arm 21 and are rotatably connected to the bottom surface of the body 1. When encountering a slope in the air intake duct, the guide rollers 5 first contact the ground. At this time, the body 1 is lifted and rotated through the pin shaft, so that the body 1 can be adaptively raised and adjusted to avoid the front end of the body 1 colliding with the slope. The guide rollers 5 can stably drive the body 1 to move inside the air intake duct, effectively improving the obstacle-crossing ability of the body 1.

[0035] To further optimize the solution, a camera is fixedly connected to the body 1. The position of the body 1 can be checked through the camera, and the position of the body 1 can be adjusted in real time by the robot, so that the support plate can be accurately inserted into the positioning slot 4.

[0036] Working process: The utility model installs the main body 1 at the front end of the detection robot; when performing the inspection task, the robot drives the main body 1 to move and places the main body 1 between the two lowest support plates at the front end of the engine, one of the support plates is inserted into the positioning groove 4, and the main body 1 is limited in the left and right directions, and the second roller 42 can assist in guiding the support plate to be inserted into the positioning groove 4; when the first mechanical arm 21 drives the first roller 2 to move the blade, a reaction force will be generated on the main body 1, and the positioning groove 4 can better limit the left and right movement of the device; after the support plate is inserted into the positioning groove 4 and is in place, that is, the main body 1 cannot continue to move toward the engine, at this time, the positioning arm 3 in the positioning groove 12 on one side of the main body 1 will extend out of the positioning groove 12 through the drive of the second mechanical arm 31, and the support plate is clamped by the positioning arm 3, so that the main body 1 cannot move in the front and rear directions, thereby realizing that the main body 1 is firmly fixed next to the support plate; the detection work of moving the blade can be carried out.

[0037] For an engine in which no support plate is installed on the front end surface of the engine and the resistance to blade rotation is relatively small, since there is no support plate for auxiliary fixation, the friction between the robot itself and the ground allows the first robot arm 21 to stably drive the first roller 2 to move the blades without causing the main body 1 to move left and right or forward and backward.

[0038] Embodiment 2

[0039] Reference Figure 3 The difference between this embodiment and the first embodiment is that this embodiment is used to clamp the curved support plate, and the positioning arm 3 adopts a flat plate. When the flat plate abuts against the curved support plate, the flat plate is hinged to the second mechanical arm 31, so that the flat plate can effectively fit the surface of the curved support plate, and the flat plate is driven to move by the second mechanical arm 31, so that the flat plate can clamp the curved support plate in the clamping groove 4, and then the first mechanical arm 21 can drive the first roller 2 to move the blade.

[0040] Embodiment 3

[0041] Reference Figure 4 The difference between this embodiment and the first embodiment is that this embodiment is used to clamp the airfoil support plate, and the positioning arm 3 adopts a positioning block. A limiting groove is provided at one end of the positioning block away from the second mechanical arm 31, and the limiting groove is adapted to the end of the airfoil support plate. After the airfoil support plate extends into the clamping groove 4, the second mechanical arm 31 drives the positioning block to rotate so that the positioning block extends out of the positioning groove 12. When the limiting groove abuts against the end of the airfoil support plate, the positioning block can clamp the airfoil support plate in the clamping groove 4, and then the first mechanical arm 21 can drive the first roller 2 to move the blade.

[0042] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0043] The embodiments described above are only descriptions of the preferred methods of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the protection scope determined by the claims of the present invention.

Claims

1. An aero-engine blade shifting device, characterized in that: The robot comprises a body (1), a toggle assembly is arranged on one side of the body (1), a side of the body (1) away from the toggle assembly is detachably connected to a robot via a connecting piece (11), a positioning assembly is arranged between the toggle assembly and the connecting piece (11), the positioning assembly is arranged on one side of the body (1), a clamping assembly is arranged in the middle of an outer wall of the side where the positioning assembly is arranged, and a guide assembly is arranged on the bottom surface of one end of the body (1) away from the connecting piece (11); The locking assembly comprises a support rod (41), one end of the support rod (41) is fixedly connected to a side wall of the body (1) close to the connecting piece (11), and a locking groove (4) is left between the support rod (41) and the body (1).

2. The aeroengine blade shifting device according to claim 1, characterized in that: The shifting assembly comprises a first mechanical arm (21) installed in the body (1); one end of the first mechanical arm (21) extending outside the body (1) is rotatably connected to a first roller (2).

3. The aeroengine blade shifting device according to claim 1, characterized in that: The support rod (41) is arranged in an L shape.

4. The aeroengine blade shifting device according to claim 1, characterized in that: One end of the support rod (41) away from the body (1) is rotatably connected to a second roller (42).

5. The aero-engine blade shifting device according to claim 1, characterized in that: The clamping assembly comprises a positioning groove (12) provided on the body (1), one end of a second mechanical arm (31) being installed in the positioning groove (12), and a positioning arm (3) being installed at the other end of the second mechanical arm (31).

6. The aeroengine blade shifting device according to claim 2, characterized in that: The guide assembly comprises a plurality of guide rollers (5), wherein the guide rollers (5) are arranged below the first mechanical arm (21), and the guide rollers (5) are rotatably connected to the bottom surface of the body (1).

7. The aircraft engine blade shifting device according to claim 1, characterized in that: A camera is fixedly connected to the body (1).

Images