A rapid detection device for aircraft engine turbine blades

Abstract

The present invention discloses a rapid detection device for aircraft engine turbine blades, and relates to the technical field of turbine blade detection. The device comprises a transmission disk for transmitting turbine blades, and a plurality of support rings for supporting turbine blades are distributed in an array on the upper end of the transmission disk, and a rolling member is provided on the upper end surface of the support ring for facilitating fine-tuning of the turbine blades. A detection component for detecting the turbine blades is provided on the transmission path of the transmission disk, and the detection component comprises a base, and a transmission groove matched with the transmission disk is provided on the base. The detection method here in the present application does not need to disassemble the blades for detection, and effectively ensures the processing efficiency. The detection here does not need immersion operation, and eliminates the problem of slow immersion process, and effectively ensures the detection effect. In addition, the flow-type detection method here is convenient for loading and unloading, and has high safety and strong practicality.

Description

Technical Field

[0001] The invention relates to the technical field of turbine blade detection, in particular to a rapid detection device for aircraft engine turbine blades. Background Art

[0002] After the high-pressure turbine blades of an aircraft engine have been running for a period of time, there will be dust accumulation in the internal cooling channels and air film holes. Blockage may cause the blades to break due to poor local heat dissipation. The existing blockage detection method is a water spray test method, that is, water is introduced from the airway inlet at the lower end of the tenon, and then observe whether there is water rushing out of the cooling channel and the air outlet on the air film hole, so as to judge whether there is a blockage, and finally clear the corresponding blocked parts. This method requires water injection, which is more complicated and easy to damage the blades. The existing patent announcement number CN112304625B discloses a detection device for engine turbine blades. The device immerses the blades in fluorescent liquid and then cooperates with the induction camera to take pictures to obtain the pore status. However, this method is extremely time-consuming during the infiltration process, and waste liquid removal operations are also required in the later stage, which increases the process. In addition, the device needs to position the turbine blades in a vertical tooling when performing the detection, and it also needs to be disassembled later. The operation is extremely complicated and there are safety hazards.

[0003] Based on this, a rapid detection device for aircraft engine turbine blades is now provided, which can eliminate the disadvantages of existing devices. Summary of the invention

[0004] The purpose of the present invention is to provide a rapid detection device for aircraft engine turbine blades to solve the problems in the background technology.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A rapid detection device for turbine blades of an aircraft engine comprises a transmission disk for transmitting turbine blades, a plurality of support rings for supporting turbine blades are arranged in an array on the upper end of the transmission disk, a rolling member is arranged on the upper end surface of the support ring for facilitating fine adjustment of the turbine blades, a detection component for detecting the turbine blades is arranged on the transmission path of the transmission disk, the detection component comprises a base, a transmission groove matched with the transmission disk is arranged on the base, a fixed frame is arranged above the base, a lifting seat is arranged below the fixed frame, a clamping mechanism for lifting the turbine blades for subsequent detection is arranged on the lifting seat, a rotating block is arranged in the middle position of the lifting seat, the upper end of the rotating block is connected to a rotating driving member for driving the rotating block to rotate so as to realize the rotation of the turbine blades, the right side of the lifting seat is connected to a lifting pushing member for driving the lifting seat to move up and down, and the base is also provided with a detection unit for covering the outer edge of the turbine blade to realize detection.

[0007] On the basis of the above technical solution, the present invention also provides the following optional technical solution:

[0008] In an optional solution: a high-pressure nozzle for performing dust removal operations on the surface of the turbine blade is provided on the other side of the fixing frame opposite to the detection unit.

[0009] In an optional solution: the detection unit includes a fan-shaped detection channel for wrapping the edge position of the turbine blade, the upper and lower inner walls of the fan-shaped detection channel are provided with a plurality of camera units for acquiring the surface image of the turbine blade, the lower end of the fan-shaped detection channel is connected to a pushing mechanism for pushing it to the left to wrap the turbine blade, and the detection unit also includes a blowing mechanism for blowing air to the air inlet of the corresponding blade on the turbine blade.

[0010] In an optional solution: the blowing mechanism includes a docking telescopic rod arranged on a lifting arm, the output end of the docking telescopic rod is provided with an air duct horizontally arranged, the left end of the air duct is provided with a docking nozzle for docking the blade air inlet end of the corresponding turbine blade, the air inlet end of the air duct is connected to a hair dryer through a hose, and the air inlet end of the hair dryer is connected to an atomization box.

[0011] In an optional scheme: the clamping mechanism includes an adjusting and fixing sleeve distributed in an array at the lower end of the lifting seat, each adjusting and fixing sleeve is slidably provided with a fixed side block with a rectangular cross-section, the outer end of the fixed side block is connected and fixed to the adjusting slide rod by an adjusting spring, the inner end of each fixed side block is provided with an arc surface, an adjusting motor is provided in the middle position of the rotating block, the output end of the adjusting motor is provided with an adjusting wheel which is pressed and contacted with the inner ends of multiple fixed side blocks, and a plurality of raised blocks for pushing the fixed side blocks to slide outward are distributed in an array on the outer side of the adjusting wheel, each fixed side block is provided with a vertically arranged clamping vertical rod at the lower end, the lower ends of the multiple clamping vertical rods constitute a clamping end that matches the center hole of the turbine blade, and each clamping vertical rod is provided with an anti-detachment hook at the lower end to prevent the turbine blade from falling off.

[0012] In an optional solution: the rotating drive member includes a transmission sleeve arranged in the middle position of the rotating block, a transmission rod is slidably provided on the upper end of the transmission sleeve, the upper end of the transmission rod is connected to a rotating motor for driving the rotation thereof, the rotating motor is arranged at the upper end of the fixed frame, and a limiting protrusion is provided on the outer side of the transmission rod for matching with the limiting groove on the inner wall of the transmission sleeve, and the setting of the limiting protrusion and the limiting groove allows the transmission sleeve and the transmission rod to only slide relative to each other.

[0013] In an optional solution: the lifting push member includes a lifting slider slidingly arranged on the right inner wall of the fixed frame, a lifting arm for connecting to a lifting seat is provided on the side of the lifting slider, the lifting slider is threadedly engaged on the lifting screw, the upper end of the lifting screw is rotatably connected to the bottom of the fixed frame, and the lower end of the lifting screw is connected to a lifting motor for driving it to rotate.

[0014] In an optional scheme: the pushing mechanism includes a vertical rod arranged at the lower end of the fan-shaped detection channel, the lower end of the vertical rod is connected to a horizontal slider, the horizontal slider is slidably arranged in a horizontal slide groove at the upper end of the base, the left side of the horizontal slider is connected and fixed to the inner wall of the horizontal slide groove by a reset spring, the upper end of the fan-shaped detection channel is provided with an inclined guide inclined rod, the upper end of the lifting arm is provided with a guide cross bar that is in sliding contact with the lower surface of the guide inclined rod, and the guide cross bar is rotatably arranged on the lifting arm.

[0015] In an optional solution: the rolling element includes spherical cavities distributed in an array on the upper end surface of the support ring, and a steel ball is arranged in each spherical cavity.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present application is designed to address the drawbacks of existing devices, and realizes the detection of turbine blades under flowing water, simplifies the difficulty of disassembly and assembly, improves the detection efficiency, and the adjustable clamping method here is suitable for the detection of turbine blades of different models. In addition, the present application cancels the existing immersion detection method and adopts the dry ice fog blowing method, which further simplifies the detection process, reduces the damage to the blades, and improves the efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural schematic diagram of the present invention.

[0019] Figure 2 It is a schematic diagram of the structure of the fixing frame and the transmission plate of the present invention.

[0020] Figure 3 It is a schematic diagram of the structure inside the fixed frame of the present invention.

[0021] Figure 4 It is a schematic diagram of the support ring structure in the present invention.

[0022] Notes on the accompanying drawings: fixed frame 11, lifting arm 12, guiding diagonal rod 13, guiding cross rod 14, lifting slider 15, lifting screw 16, fan-shaped detection channel 17, lifting motor 18, horizontal slider 19, base 20, reset spring 21, steel ball 22, anti-unhooking hook 23, adjusting wheel 24, support ring 25, transmission disk 26, clamping vertical rod 27, turbine blade 28, adjusting fixed sleeve 29, high-pressure nozzle 30, fixed side block 31, adjusting slide rod 32, lifting seat 33, transmission sleeve 34, rotating motor 35, transmission rod 36, adjusting motor 37, docking nozzle 38, docking telescopic rod 39. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0024] In one embodiment, Figure 1-Figure 4As shown, a rapid detection device for turbine blades of an aircraft engine comprises a transmission disc 26 for transmitting turbine blades 28, a plurality of support rings 25 for supporting turbine blades 28 are arranged in an array on the upper end of the transmission disc 26, a rolling member for facilitating fine adjustment of the turbine blades 28 is arranged on the upper end surface of the support ring 25, a detection component for detecting the turbine blades 28 is arranged on the transmission path of the transmission disc 26, the detection component comprises a base 20, a transmission groove for matching with the transmission disc 26 is arranged on the base 20, a fixed frame 11 is arranged above the base 20, a lifting seat 33 is arranged below the fixed frame 11, a clamping mechanism for lifting the turbine blades 28 for subsequent detection is arranged on the lifting seat 33, a rotating block is arranged in the middle position of the lifting seat 33, the upper end of the rotating block is connected to a rotating driving member for driving the rotating block to rotate so as to realize the rotation of the turbine blades 28, a lifting pusher for driving the lifting seat 33 to move up and down is connected to the right side, and a detection unit for covering the outer edge of the turbine blades 28 for detection is also arranged on the base 20;

[0025] A high-pressure nozzle 30 for performing dust removal operation on the surface of the turbine blade 28 is provided on the other side of the fixed frame 11 opposite to the detection unit. The dust on the surface of the turbine blade 28 is blown away by the high-pressure airflow to avoid interference with the subsequent detection.

[0026] The detection unit includes a fan-shaped detection channel 17 for wrapping the edge position of the turbine blade 28. The upper and lower inner walls of the fan-shaped detection channel 17 are provided with a plurality of camera units for obtaining the surface image of the turbine blade 28. The lower end of the fan-shaped detection channel 17 is connected to a pushing mechanism for pushing the turbine blade 28 wrapped therein to the left. The pushing mechanism ensures that the lifting and lowering of the turbine blade 28 will not be interfered with. The detection unit also includes a blowing mechanism for blowing air to the air inlet of the corresponding blade on the turbine blade 28, so that colored gas can be blown into the blade channel through the blowing mechanism, so that the camera can clearly obtain the air ventilation condition of the pores on the surface of the corresponding blade. This detection method greatly simplifies the detection equipment;

[0027] The colored gas here is produced by dry ice vaporization, so the gas produced will not have any impact on the environment and it also helps to mark the gas;

[0028] The blowing mechanism includes a docking telescopic rod 39 arranged on the lifting arm 12, the output end of the docking telescopic rod 39 is provided with a horizontally arranged air guide pipe, the left end of the air guide pipe is provided with a docking nozzle 38 for docking the blade air inlet end of the corresponding turbine blade 28, the air inlet end of the air guide pipe is connected to the hair dryer through a hose, the air inlet end of the hair dryer is connected to the atomization box, and dry ice is used to generate water mist in the atomization box to facilitate the subsequent camera detection;

[0029] The clamping mechanism includes an adjustment fixing sleeve 29 distributed in an array at the lower end of the lifting seat 33, each adjustment fixing sleeve 29 is slidably provided with a fixed side block 31 with a rectangular cross-section, the outer end of the fixed side block 31 is connected and fixed to the adjustment slide rod 32 through an adjustment spring, and the inner end of each fixed side block 31 is provided with an arc surface, an adjustment motor 37 is provided in the middle position of the rotating block, and an adjustment wheel 24 is provided at the output end of the adjustment motor 37 to be pressed and contacted with the inner ends of multiple fixed side blocks 31, and a plurality of raised blocks for pushing the fixed side blocks 31 to slide outward are distributed in an array on the outer side of the adjustment wheel 24, and a vertically arranged clamping vertical rod 27 is provided at the lower end of each fixed side block 31, and multiple The lower end of the clamping vertical rod 27 constitutes a clamping end that matches the center hole of the turbine blade 28. The lower end of each clamping vertical rod 27 is provided with an anti-drop hook 23 to prevent the turbine blade 28 from falling off. Under the action of the adjustment spring, multiple fixed side blocks 31 converge to the middle. At this time, the distance between the lower ends of the clamping vertical rod 27 is the smallest. After extending into the center hole of the turbine blade 28, the adjusting motor 37 drives the adjusting wheel 24 to rotate. The raised block on the outer side of the adjusting wheel 24 will generate a force on the fixed side block 31, so that the fixed side block 31 slides outward along the adjustment fixing sleeve 29. In this way, the clamping vertical rod 27 at the lower end of the fixed side block 31 will also expand outward, thereby achieving clamping and fixing of the center hole of the turbine blade 28;

[0030] The rotary drive member includes a transmission sleeve 34 arranged at the middle position of the rotating block, a transmission rod 36 is slidably provided on the upper end of the transmission sleeve 34, the upper end of the transmission rod 36 is connected to a rotating motor 35 for driving the transmission sleeve 34 to rotate, and the rotating motor 35 is arranged on the upper end of the fixed frame 11. A limiting protrusion is provided on the outer side of the transmission rod 36 to match the limiting groove on the inner wall of the transmission sleeve 34. The setting of the limiting protrusion and the limiting groove allows the transmission sleeve 34 and the transmission rod 36 to only slide relative to each other, and cannot rotate relative to each other. Such a retractable transmission mode allows the power to be transmitted all the time regardless of whether the lifting seat 33 is raised or lowered;

[0031] The lifting pusher includes a lifting slider 15 slidably arranged on the right inner wall of the fixed frame 11, and a lifting arm 12 for connecting the lifting seat 33 is provided on the side of the lifting slider 15. The lifting slider 15 is threadedly engaged with the lifting screw 16. The upper end of the lifting screw 16 is rotatably connected to the bottom of the fixed frame 11, and the lower end of the lifting screw 16 is connected to a lifting motor 18 for driving the lifting screw 16 to rotate. In this way, the lifting slider 15 and the lifting screw 16 can be driven by the lifting motor 18 to rotate relative to each other. Under the action of the thread, the lifting slider 15 slides up and down along the inner wall of the fixed frame 11, thereby providing power for lifting and lowering the detection position;

[0032] The pushing mechanism includes a vertical rod arranged at the lower end of the fan-shaped detection channel 17, the lower end of the vertical rod is connected to a horizontal slider 19, the horizontal slider 19 is slidably arranged in a horizontal slide groove at the upper end of a base 20, the left side of the horizontal slider 19 is connected and fixed to the inner wall of the horizontal slide groove by a return spring 21, the upper end of the fan-shaped detection channel 17 is provided with an inclined guide inclined rod 13, the upper end of the lifting arm 12 is provided with a guide cross bar 14 that is in sliding contact with the lower surface of the guide inclined rod 13, the guide cross bar 14 is rotatably arranged on the lifting arm 12, when the lifting arm 12 moves upward with the turbine blade 28, the guide cross bar 14 will generate a driving force on the inclined surface of the guide inclined rod 13, so that the fan-shaped detection channel 17 moves to the left, so as to wrap the side part of the turbine blade 28 after rising, so as to facilitate subsequent detection;

[0033] The rolling element includes a spherical cavity arrayed on the upper end surface of the support ring 25, and each spherical cavity is equipped with a steel ball 22, so that when the multiple steel balls 22 contact the turbine blades 28, rolling friction is achieved, so that the position of the turbine blades 28 can be fine-tuned, which is convenient for later fine-tuning and reduces wear between components;

[0034] The above embodiment discloses a rapid detection device for aircraft engine turbine blades, wherein, during actual detection, the mortise and tenon air inlet of each blade on the turbine blade 28 is first guided to the upper surface of the center ring of the turbine blade 28 through a pipeline to facilitate subsequent docking and blowing, and then the turbine blade 28 to be detected is placed on the support ring 25 on the transmission disk 26. As the transmission disk 26 rotates, the turbine blades 28 thereon will continuously pass through the fixed frame 11. When the turbine blade 28 is located inside the fixed frame 11, the lifting seat 33 is driven down by the lifting pusher, and then the center hole of the turbine blade 28 is clamped by the clamping mechanism. The turbine blade 28 is clamped and fixed, and then the lifting and pushing member drives the turbine blade 28 to rise to the target height. While the turbine blade 28 rises, the fan-shaped detection channel 17 moves close to the turbine blade 28, thereby wrapping the outer side of the turbine blade 28, and driving the turbine blade 28 to rotate through the rotating driving member, thereby providing power for the outer blades of the turbine blade 28 to be detected in turn. When a blade rotates to the detection position, the rotating driving member stops rotating, and at this time, air is blown into the inside of the blade through the blowing mechanism, so that the camera unit can clearly display the overflow of the airflow, thereby judging whether the air hole of the blade is blocked, and then completing the detection of the blade;

[0035] The detection method in the present application does not require the blades to be disassembled for detection, which effectively ensures processing efficiency. The detection here does not require immersion operation, eliminating the problem of slow immersion process, effectively ensuring the detection effect. The flow-type detection method here is also convenient for loading and unloading, highly safe, and highly practical.

[0036] The above is only a specific embodiment of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A rapid detection device for turbine blades of an aircraft engine, comprising a transmission disc (26) for transmitting turbine blades (28), a plurality of support rings (25) for supporting turbine blades (28) are arranged in an array on the upper end of the transmission disc (26), a rolling element for facilitating fine adjustment of the turbine blades (28) is arranged on the upper end surface of the support ring (25), and a detection component for detecting the turbine blades (28) is arranged on the transmission path of the transmission disc (26); characterized in that: The detection component comprises a base (20), a transmission groove matched with a transmission disk (26) is provided on the base (20), a fixed frame (11) is arranged above the base (20), a lifting seat (33) is arranged below the fixed frame (11), a clamping mechanism for lifting the turbine blade (28) for subsequent detection is arranged on the lifting seat (33), a rotating block is arranged in the middle of the lifting seat (33), the upper end of the rotating block is connected to a rotating driving member for driving the rotating block to rotate so as to realize the rotation of the turbine blade (28), the right side of the lifting seat (33) is connected to a lifting pushing member for driving the lifting seat (33) to move up and down, and the base (20) is also provided with a detection unit for covering the outer edge of the turbine blade (28) to realize detection; The clamping mechanism comprises an array of adjustment fixing sleeves (29) distributed at the lower end of the lifting seat (33), each adjustment fixing sleeve (29) is slidably provided with a fixed side block (31) with a rectangular cross section, the outer end of the fixed side block (31) is connected and fixed to the adjustment slide rod (32) through an adjustment spring, the inner end of each fixed side block (31) is provided with an arc surface, an adjustment motor (37) is provided at the middle position of the rotating block, and the output end of the adjustment motor (37) is provided with a plurality of fixed side blocks The inner end of the adjusting wheel (24) is pressed against the inner end of the adjusting wheel (24), and a plurality of protrusions are arranged in an array on the outer side of the adjusting wheel (24) for pushing the fixed side block (31) to slide outward. A vertically arranged clamping vertical rod (27) is provided at the lower end of each fixed side block (31). The lower ends of the plurality of clamping vertical rods (27) form clamping ends that match the central holes of the turbine blades (28). The lower end of each clamping vertical rod (27) is provided with an anti-drop hook (23) for preventing the turbine blades (28) from falling off.

2. The rapid detection device for aircraft engine turbine blades according to claim 1, characterized in that: A high-pressure nozzle (30) for performing dust removal operations on the blade surface of the turbine blade (28) is provided on the other side of the fixing frame (11) opposite to the detection unit.

3. The rapid detection device for aircraft engine turbine blades according to claim 1, characterized in that: The detection unit comprises a fan-shaped detection channel (17) for wrapping the edge position of a turbine blade (28); the upper and lower inner walls of the fan-shaped detection channel (17) are provided with a plurality of camera units for acquiring images of the surface of the turbine blade (28); the lower end of the fan-shaped detection channel (17) is connected to a pushing mechanism for pushing the wrapped turbine blade (28) to the left; and the detection unit further comprises an air blowing mechanism for blowing air to an air inlet of a corresponding blade on the turbine blade (28).

4. The rapid detection device for aircraft engine turbine blades according to claim 3, characterized in that: The air blowing mechanism comprises a docking telescopic rod (39) arranged on a lifting arm (12); a horizontally arranged air guide pipe is provided at the output end of the docking telescopic rod (39); a docking nozzle (38) for docking the blade air inlet end of a corresponding turbine blade (28) is provided at the left end of the air guide pipe; the air inlet end of the air guide pipe is connected to a hair dryer through a hose; and the air inlet end of the hair dryer is connected to an atomizing box.

5. The rapid detection device for aircraft engine turbine blades according to claim 1, characterized in that: The rotary drive member comprises a transmission sleeve (34) arranged at the middle position of the rotating block, a transmission rod (36) is slidably provided at the upper end of the transmission sleeve (34), the upper end of the transmission rod (36) is connected to a rotating motor (35) for driving the transmission rod to rotate, the rotating motor (35) is arranged at the upper end of the fixed frame (11), and a limiting protrusion is provided on the outer side of the transmission rod (36) to match with a limiting groove on the inner wall of the transmission sleeve (34), and the setting of the limiting protrusion and the limiting groove allows the transmission sleeve (34) and the transmission rod (36) to slide only relative to each other.

6. The rapid detection device for aircraft engine turbine blades according to claim 3, characterized in that: The lifting pusher comprises a lifting slider (15) slidably arranged on the right inner wall of the fixed frame (11); a lifting arm (12) for connecting to a lifting seat (33) is arranged on the side of the lifting slider (15); the lifting slider (15) is threadedly engaged with a lifting screw (16); the upper end of the lifting screw (16) is rotatably connected to the inner bottom of the fixed frame (11); and the lower end of the lifting screw (16) is connected to a lifting motor (18) for driving the lifting screw (16) to rotate.

7. The rapid detection device for aircraft engine turbine blades according to claim 6, characterized in that: The pushing mechanism comprises a vertical rod arranged at the lower end of the fan-shaped detection channel (17), the lower end of the vertical rod is connected to a horizontal slider (19), the horizontal slider (19) is slidably arranged in a horizontal slide groove at the upper end of a base (20), the left side of the horizontal slider (19) is connected and fixed to the inner wall of the horizontal slide groove through a return spring (21), an inclined guide inclined rod (13) is arranged at the upper end of the fan-shaped detection channel (17), a guide cross rod (14) which is in sliding contact with the lower surface of the guide inclined rod (13) is arranged at the upper end of the lifting arm (12), and the guide cross rod (14) is rotatably arranged on the lifting arm (12).

8. The rapid detection device for aircraft engine turbine blades according to claim 1, characterized in that: The rolling element comprises spherical cavities distributed in an array on the upper end surface of a support ring (25), and a steel ball (22) is matched in each spherical cavity.

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