CN220542771U - Detection device for aircraft turbine blade - Google Patents
Detection device for aircraft turbine blade Download PDFInfo
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- CN220542771U CN220542771U CN202322055938.0U CN202322055938U CN220542771U CN 220542771 U CN220542771 U CN 220542771U CN 202322055938 U CN202322055938 U CN 202322055938U CN 220542771 U CN220542771 U CN 220542771U
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- turbine blade
- bearing seat
- photographing camera
- aircraft turbine
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- 238000001514 detection method Methods 0.000 title claims abstract description 47
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- 230000005484 gravity Effects 0.000 claims abstract description 5
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- 238000007689 inspection Methods 0.000 claims description 5
- 239000004744 fabric Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
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Abstract
The utility model relates to the technical field of auxiliary detection of aircraft turbine blades, in particular to a detection device for aircraft turbine blades. Comprises a machine tool, a bearing seat and a photographing mechanism; the bearing seat is rotatably arranged in the machine tool and is used for fixing the turbine blade body of the aircraft; the photographing mechanism is arranged in the machine tool and is layered with the bearing seat in the gravity direction, the photographing mechanism comprises a filter disc switching and adjusting component and a photographing camera, and the filter disc switching and adjusting component is arranged between the photographing camera and the bearing seat; the filter disc switching adjusting assembly comprises at least two optical filters and a first rotary driving assembly. Specifically, the photographing camera photographs the turbine blade body of the airplane through the optical filter and calculates color detection data. The first rotary driving assembly can switch different optical filters so as to realize different detection requirements of the photographing camera on the turbine blade body of the airplane. The utility model can automatically switch the optical filter without manual replacement, and improves the detection efficiency.
Description
Technical Field
The utility model relates to the technical field of auxiliary detection of aircraft turbine blades, in particular to a detection device for aircraft turbine blades.
Background
The detection of the turbine blade of the airplane mainly adopts methods such as ultrasonic imaging, X-ray detection, magnetic powder detection and the like. In addition, to aid in blade inspection, colorimetric inspection is also used to analyze and compare changes in blade surface color to detect possible defects or damage.
The chromaticity detection device mainly comprises a photographing camera such as a CCD and an optical filter, and the photographing camera performs imaging photographing through the optical filter. However, the existing colorimetric detection device generally cannot automatically replace the filter, and a worker needs to manually replace the filter, so that the detection efficiency is low.
Disclosure of Invention
The technical problem to be solved by the embodiment of the utility model is to provide a detection device for an aircraft turbine blade, so as to solve the problem that the detection efficiency is low because a filter is required to be manually replaced in the chromaticity detection device in the prior art.
The detection device for the turbine blade of the airplane provided by the embodiment of the utility model comprises the following components:
a machine tool;
the bearing seat is rotatably arranged in the machine tool and is used for fixing the turbine blade body of the airplane;
the photographing mechanism is arranged in the machine tool, the photographing mechanism and the bearing seat are arranged in a layered manner in the gravity direction, the photographing mechanism comprises a filter disc switching and adjusting assembly and a photographing camera, the filter disc switching and adjusting assembly is arranged between the photographing camera and the bearing seat, and the photographing camera is used for carrying out detection on the turbine blade body of the airplane;
the filter switching and adjusting assembly comprises at least two optical filters and a first rotary driving assembly, wherein the first rotary driving assembly is connected with the at least two optical filters, and the first rotary driving assembly is used for driving each optical filter to move so that each optical filter is matched with the photographing camera respectively.
In some embodiments of the utility model, the filter switching adjustment assembly further comprises:
the mounting seat is rotatably arranged in the photographing mechanism, and one side of the mounting seat, which faces the camera, is provided with at least two mounting grooves; at least two mounting grooves are arranged at intervals by the rotation axis of the mounting seat, and each optical filter is respectively arranged in each mounting groove; the output end of the first rotary driving assembly is connected to the mounting seat, and the first rotary driving assembly is used for driving the mounting seat to rotate so that each optical filter corresponds to the position of the photographing camera.
In some embodiments of the utility model, the first rotary drive assembly comprises:
a driving wheel;
the synchronous belt is arranged on the driving wheel and the mounting seat;
the output end of the first rotary driving piece is connected with the driving wheel, and the first rotary driving piece is used for driving the driving wheel to rotate so that the synchronous belt drives the mounting seat to rotate relatively.
In some embodiments of the present utility model, the photographing mechanism includes a housing, the filter switching adjustment assembly and the photographing camera are both installed inside the housing, a through hole penetrating through the inner and outer surface walls of the housing is provided on a side of the housing facing the bearing seat, and an axis of the through hole coincides with a center line of the photographing camera.
In some embodiments of the present utility model, the photographing device further includes a base, which is installed inside the machine tool, and the photographing mechanism is slidably disposed on the base, so that the photographing camera moves in a direction away from or close to the carrying seat.
In some embodiments of the present utility model, the camera further comprises a light source mechanism, wherein the light source mechanism is disposed between the bearing seat and the photographing mechanism, and the light source mechanism is used for illuminating the turbine blade body of the aircraft.
In some embodiments of the utility model, the light source mechanism comprises:
the supporting seat is slidably arranged on the base;
at least two light sources which are rotatably arranged on the supporting seat and arranged on two sides of the photographing camera.
In some embodiments of the utility model, further comprising a second rotary drive assembly comprising:
the rotary shaft is rotatably arranged in the machine tool, and one end, facing the photographing mechanism, of the rotary shaft is provided with the bearing seat;
the synchronous belt wheel set comprises two synchronous belt wheels which are arranged at intervals, wherein one synchronous belt wheel is sleeved at one end of the rotating shaft far away from the bearing seat; the two synchronous pulleys are connected through a belt;
and the output end of the second rotary driving piece is connected with the other synchronous pulley.
In some embodiments of the present utility model, the bearing seat includes a fixing portion and a limiting portion, the fixing portion is disposed at one end of the rotating shaft, the limiting portion is disposed at a side of the fixing portion facing the photographing camera, and the turbine blade body of the aircraft is sandwiched between the limiting portion and the fixing portion.
In some embodiments of the utility model, a black shade cloth is arranged inside the machine tool.
Compared with the prior art, the detection device for the aircraft turbine blade has the beneficial effects that: the utility model provides a detection device for an aircraft turbine blade, which comprises a machine tool, a bearing seat and a photographing mechanism, wherein the machine tool is used for carrying out the detection on the aircraft turbine blade; the bearing seat is rotatably arranged in the machine tool and is used for fixing the turbine blade body of the aircraft; the photographing mechanism is arranged in the machine tool and layered with the bearing seat in the gravity direction, and comprises a filter disc switching and adjusting assembly and a photographing camera, wherein the filter disc switching and adjusting assembly is arranged between the photographing camera and the bearing seat, and the photographing camera is used for carrying out the detection on the turbine blade body of the airplane; the filter disc switching and adjusting assembly comprises at least two optical filters and a first rotary driving assembly, wherein the first rotary driving assembly is connected with the at least two optical filters and is used for driving each optical filter to move so that each optical filter can be matched with a photographing camera respectively. Specifically, the photographing camera photographs the turbine blade body of the airplane through the optical filter and calculates color detection data. And the first rotary driving assembly can switch different optical filters so as to realize different detection requirements of the photographing camera on the turbine blade body of the airplane. Compared with the embodiment that the existing chromaticity detection device cannot automatically replace the filter, the utility model can automatically switch the filter without manual replacement, thereby improving the detection efficiency.
Drawings
The utility model will now be described in further detail with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic perspective view of a detection device according to an embodiment of the present utility model;
FIG. 2 is an enlarged schematic view of a portion of the position A of FIG. 1;
fig. 3 is a schematic perspective view of a second rotary driving assembly and a bearing seat in a pair detection device according to an embodiment of the present utility model;
fig. 4 is a schematic perspective view of a photographing mechanism according to an embodiment of the present utility model;
fig. 5 is a schematic perspective view of a portion of a photographing mechanism according to an embodiment of the present utility model.
The reference numerals in the drawings are as follows:
1000. detection device
10. A machine tool;
20. a bearing seat; 21. a fixing part; 22. a limit part;
30. a photographing mechanism; 31. a filter switching adjustment assembly; 311. a light filter; 312. a first rotary drive assembly; 3121. a driving wheel; 3122. a synchronous belt; 3123. a first rotary drive member; 313. a mounting base; 3131. a mounting groove; 32. a photographing camera; 33. a housing; 331. a through port;
40. a base;
50. a light source mechanism; 51. a support base; 52. a light source;
60. a second rotary drive assembly; 61. a rotating shaft; 62. a synchronous pulley; 63. a second rotary drive.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. Preferred embodiments of the present utility model will now be described in detail with reference to the accompanying drawings.
An embodiment of the present utility model provides a detection device 1000 for an aircraft turbine blade, as shown in fig. 1 to 5, which includes a machine tool 10, a bearing seat 20, and a photographing mechanism 30; the bearing seat 20 is rotatably arranged in the machine tool 10, and the bearing seat 20 is used for fixing the turbine blade body of the airplane; the photographing mechanism 30 is arranged in the machine tool 10, the photographing mechanism 30 and the bearing seat 20 are arranged in a layered manner in the gravity direction, the photographing mechanism 30 comprises a filter disc switching and adjusting assembly 31 and a photographing camera 32, the filter disc switching and adjusting assembly 31 is arranged between the photographing camera 32 and the bearing seat 20, and the photographing camera 32 is used for carrying out the detection on the turbine blade body of the airplane; the filter switching adjustment assembly 31 includes at least two optical filters 311 and a first rotation driving assembly 312, the first rotation driving assembly 312 is connected to the at least two optical filters 311, and the first rotation driving assembly 312 is used for driving each optical filter 311 to move so that each optical filter 311 is respectively matched with the photographing camera 32.
Through the above scheme, the photographing camera 32 photographs the turbine blade body of the aircraft through the optical filter 311 and calculates the color detection data, so as to analyze and compare the changes of the surface colors of the blade, so as to detect possible defects or damages. In addition, the first rotary driving assembly 312 can switch different optical filters 311 to realize different detection requirements of the camera 32 on the turbine blade body of the aircraft. Compared with the embodiment of the conventional colorimetric detection device 1000, which cannot automatically replace the filter, the present utility model can automatically switch the filter 311 without manual replacement, thereby improving the detection efficiency.
Referring to fig. 5, in the solution of the present utility model, the filter switching adjustment assembly 31 further includes a mounting base 313, the mounting base 313 is rotatably disposed in the photographing mechanism 30, and at least two mounting grooves 3131 are disposed on a side of the mounting base 313 facing the camera; at least two mounting grooves 3131 are spaced apart from the rotation axis 61 of the mounting base 313, and each of the optical filters 311 is respectively mounted in each of the mounting grooves 3131. The output end of the first rotary driving assembly 312 is connected to the mounting base 313, and the first rotary driving assembly 312 is used for driving the mounting base 313 to rotate, so that each optical filter 311 corresponds to the position of the photographing camera 32. Specifically, the first rotary driving assembly 312 drives the mounting base 313 to rotate, the mounting base 313 rotates and simultaneously realizes different angle conversion of each optical filter 311, when one of the optical filters 311 rotates to a preset angle, the optical filter 311 just completes pairing with the photographing camera 32, the photographing camera 32 photographs the turbine blade body of the aircraft, and then the cyclic action is repeated, and the pairing is performed by switching between the different optical filters 311. So set up, each light filter 311 is all restricted to be installed in mounting groove 3131, and after light filter 311 is installed in mounting groove 3131, light filter 311 just is in the preset position, and light filter 311 has just been aimed at with camera 32 of shooing in mount pad 313 rotation light filter 311 to can fix a position the installation fast, convenient operation avoids assembly error to influence the effect of shooing, has improved the reliability of device.
Referring to fig. 5, in a more specific embodiment, the first rotary drive assembly 312 includes a drive wheel 3121, a timing belt 3122, and a first rotary drive piece 3123; the synchronous belt 3122 is installed on the driving wheel 3121 and the installation seat 313; the output end of the first rotation driving member 3123 is connected to the driving wheel 3121, and the first rotation driving member 3123 is configured to drive the driving wheel 3121 to rotate, so that the synchronous belt 3122 drives the mounting seat 313 to rotate relatively. Specifically, the first rotation driving member 3123 drives the driving wheel 3121 to rotate, and the driving wheel 3121 drives the mounting seat 313 to rotate through the timing belt 3122, so as to drive each optical filter 311 to move into a preset position. The outer diameter of the mounting seat 313 is larger than the outer diameter of the driving wheel 3121, so that the input of high speed and low torque is converted into the output of low speed and high torque, and the stability in operation is maintained.
Referring to fig. 1, 2 and 4, the camera is susceptible to ambient light during chromaticity detection, which results in inaccurate detection results, so as to solve this technical problem. In an embodiment, the photographing mechanism 30 includes a housing 33, the filter switching adjustment assembly 31 and the photographing camera 32 are both disposed inside the housing 33, a through hole 331 penetrating through the inner and outer surfaces of the housing 33 is disposed on a side of the housing 33 facing the bearing seat 20, and an axis of the through hole 331 coincides with a center line of the photographing camera 32. So arranged, on the one hand, the photographing camera 32 is effectively isolated from the ambient light, and the detection accuracy is improved; on the other hand, the filter switching adjusting assembly 31 and the camera 32 are both mounted inside the housing 33, and during maintenance, a worker can detach the housing 33 alone, so that the maintenance is facilitated.
Referring to fig. 1, in an embodiment, the detecting device 1000 further includes a base 40, the base 40 is installed inside the machine tool 10, and the photographing mechanism 30 is slidably disposed on the base 40, so as to move the photographing camera 32 in a direction away from or close to the carrying seat 20. So arranged, the photographing mechanism 30 can adjust the relative distance with the bearing seat 20, namely, adjust the photographing height; and the accuracy of detection is improved. Specifically, the base 40 is provided with a plurality of threaded holes, a connecting seat is arranged on one side of the shell 33 facing the base 40, a groove hole is arranged on the connecting seat, and a screw is inserted into the groove hole and the threaded holes. Through the design, the connecting seat can be moved along the length direction of the groove-shaped hole by tightening the screw, namely, the relative distance between the photographing mechanism 30 and the bearing seat 20 is adjusted, and the screw is installed and disassembled quickly and conveniently, so that the adjustment is convenient.
Referring to fig. 1, 2 and 4, in an embodiment, the detection device 1000 further includes a light source 52 mechanism 50, the light source 52 mechanism 50 is disposed between the bearing seat 20 and the photographing mechanism 30, and the light source 52 mechanism 50 is used for illuminating the turbine blade body of the aircraft. So configured, sufficient illumination may be provided to ensure that the photo camera 32 is able to properly perceive and record the details and color of the photographed aircraft turbine blade body. The problem that the photo is too dark or fuzzy under the condition of insufficient light is avoided, so that the image is bright and clear.
Referring to fig. 4, in a specific embodiment, the light source 52 mechanism 50 includes a support base 51 and at least two light sources 52; the supporting seat 51 is slidably disposed on the base 40; at least two light sources 52 are rotatably disposed on the support base 51 and disposed on two sides of the camera 32. Specifically, the support base 51 moves on the base 40 relative to the photographing mechanism 30 to ensure that the aircraft turbine blade body is illuminated at the desired location. In addition, the light source 52 is angularly adjusted relative to the aircraft turbine blade body to mitigate shadows and balance light in the scene so that the brightness of the overall image is more uniform.
Referring to fig. 3, in an embodiment of the present utility model, the detecting device 1000 further includes a second rotary driving assembly 60 including a rotating shaft 61, a synchronous pulley 62 set, and a second rotary driving member 63, wherein the rotating shaft 61 of the second rotary driving member 63 is rotatably disposed inside the machine tool 10, and one end of the rotating shaft 61 facing the photographing mechanism 30 is provided with a bearing seat 20; the synchronous pulley 62 group comprises two synchronous pulleys 62 which are arranged at intervals, wherein one synchronous pulley 62 is sleeved at one end of the rotating shaft 61 far away from the bearing seat 20; the two synchronous pulleys 62 are connected by a belt; the output end of the second rotary drive 63 is connected to the other synchronous pulley 62. Specifically, the second rotary driving member 63 drives one of the synchronous pulleys 62 to rotate, and then the other synchronous pulley 62 is brought to rotate in cooperation, the synchronous pulley 62 is connected with the rotating shaft 61 by a key, and the rotating shaft 61 follows rotation to then drive the turbine blade body of the airplane on the bearing seat 20 to rotate. So set up to be suitable for the shooting of the different angles of putting of aircraft turbine blade body, guarantee the degree of accuracy of effect of shooing.
The first rotation driving member 3123 and the second rotation driving member 63 in the above embodiments may be servo motors, but may be DD motors or other rotation driving units, which are not limited thereto.
Referring to fig. 3, in some embodiments of the present utility model, the bearing seat 20 includes a fixing portion 21 and a limiting portion 22, the fixing portion 21 is disposed at one end of the rotating shaft 61, the limiting portion 22 is disposed at a side of the fixing portion 21 facing the camera 32, and the turbine blade body of the aircraft is sandwiched between the limiting portion 22 and the fixing portion 21. Specifically, the fixing portion 21 and the limiting portion 22 are detachably connected, the fixing portion 21 is in shaft installation, a first external thread is arranged on the outer peripheral surface of the fixing portion 21, the limiting portion 22 is provided with a mounting hole, a first internal thread is arranged in the mounting hole, and the first internal thread is in threaded connection with the first external thread. So set up, threaded connection has the auto-lock nature, and easily dismantles and maintains, can restrict aircraft turbine blade body displacement, and the aircraft turbine blade body does not rock when guaranteeing to detect, influences the testing result.
In some embodiments of the present utility model, a black shade cloth (not shown) is provided inside machine tool 10. The arrangement further prevents various external factors from affecting the photographing effect, and ensures the accuracy of the photographing effect.
It should be understood that the foregoing embodiments are merely illustrative of the technical solutions of the present utility model, and not limiting thereof, and that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art; all such modifications and substitutions are intended to be included within the scope of this disclosure as defined in the following claims.
Claims (10)
1. A detection device for an aircraft turbine blade, comprising:
a machine tool;
the bearing seat is rotatably arranged in the machine tool and is used for fixing the turbine blade body of the airplane;
the photographing mechanism is arranged in the machine tool, the photographing mechanism and the bearing seat are arranged in a layered manner in the gravity direction, the photographing mechanism comprises a filter disc switching and adjusting assembly and a photographing camera, the filter disc switching and adjusting assembly is arranged between the photographing camera and the bearing seat, and the photographing camera is used for carrying out detection on the turbine blade body of the airplane;
the filter switching and adjusting assembly comprises at least two optical filters and a first rotary driving assembly, wherein the first rotary driving assembly is connected with the at least two optical filters, and the first rotary driving assembly is used for driving each optical filter to move so that each optical filter is matched with the photographing camera respectively.
2. The detection device for aircraft turbine blades of claim 1, wherein the filter switching adjustment assembly further comprises:
the mounting seat is rotatably arranged in the photographing mechanism, and one side of the mounting seat, which faces the camera, is provided with at least two mounting grooves; at least two mounting grooves are arranged at intervals by the rotation axis of the mounting seat, and each optical filter is respectively arranged in each mounting groove; the output end of the first rotary driving assembly is connected to the mounting seat, and the first rotary driving assembly is used for driving the mounting seat to rotate so that each optical filter corresponds to the position of the photographing camera.
3. The detection apparatus for aircraft turbine blades as claimed in claim 2, wherein the first rotary drive assembly comprises:
a driving wheel;
the synchronous belt is arranged on the driving wheel and the mounting seat;
the output end of the first rotary driving piece is connected with the driving wheel, and the first rotary driving piece is used for driving the driving wheel to rotate so that the synchronous belt drives the mounting seat to rotate relatively.
4. A detection device for an aircraft turbine blade according to any one of claims 1 to 3, wherein the photographing mechanism comprises a housing, the filter switching adjustment assembly and the photographing camera are both arranged inside the housing, a through hole penetrating through the inner and outer surface walls of the housing is formed in one side of the housing, which faces the bearing seat, and the axis of the through hole coincides with the central line of the photographing camera.
5. The apparatus of claim 4, further comprising a base mounted inside the machine tool, the photographing mechanism being slidably disposed on the base to move the photographing camera in a direction away from or toward the carrier.
6. The inspection device for an aircraft turbine blade of claim 5, further comprising a light source mechanism disposed between the carrier and the photographing mechanism, the light source mechanism configured to illuminate the aircraft turbine blade body.
7. The inspection apparatus for aircraft turbine blades as set forth in claim 6, wherein said light source mechanism comprises:
the supporting seat is slidably arranged on the base;
at least two light sources which are rotatably arranged on the supporting seat and arranged on two sides of the photographing camera.
8. The inspection apparatus for aircraft turbine blades as in claim 4, further comprising a second rotary drive assembly comprising:
the rotary shaft is rotatably arranged in the machine tool, and one end, facing the photographing mechanism, of the rotary shaft is provided with the bearing seat;
the synchronous belt wheel set comprises two synchronous belt wheels which are arranged at intervals, wherein one synchronous belt wheel is sleeved at one end of the rotating shaft far away from the bearing seat; the two synchronous pulleys are connected through a belt;
and the output end of the second rotary driving piece is connected with the other synchronous pulley.
9. The detecting device for an aircraft turbine blade according to claim 8, wherein the bearing seat comprises a fixing portion and a limiting portion, the fixing portion is mounted at one end of the rotating shaft, the limiting portion is disposed at a side of the fixing portion facing the photographing camera, and the aircraft turbine blade body is sandwiched between the limiting portion and the fixing portion.
10. The detecting device for aircraft turbine blades as claimed in claim 4, wherein the machine tool is internally provided with black shading cloth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322055938.0U CN220542771U (en) | 2023-08-02 | 2023-08-02 | Detection device for aircraft turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322055938.0U CN220542771U (en) | 2023-08-02 | 2023-08-02 | Detection device for aircraft turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220542771U true CN220542771U (en) | 2024-02-27 |
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ID=89976909
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322055938.0U Active CN220542771U (en) | 2023-08-02 | 2023-08-02 | Detection device for aircraft turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220542771U (en) |
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2023
- 2023-08-02 CN CN202322055938.0U patent/CN220542771U/en active Active
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