CN210293151U - Aeroengine single-blade detection device - Google Patents
Aeroengine single-blade detection device Download PDFInfo
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- CN210293151U CN210293151U CN201921357504.3U CN201921357504U CN210293151U CN 210293151 U CN210293151 U CN 210293151U CN 201921357504 U CN201921357504 U CN 201921357504U CN 210293151 U CN210293151 U CN 210293151U
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Abstract
The utility model relates to an aeroengine single-blade detection device, which belongs to a detection device, and comprises a detection device and a clamping device for fixing a single blade, wherein the detection device is internally provided with a single-blade detection program and a displacement program for identifying relative distance in advance, and the clamping device is provided with a base and a pressing plate for respectively fixing a lower assembly extension section and an upper assembly extension section of the single blade so as to simulate the assembly clamping of the single blade in practical application, thereby effectively fixing the single blade of the engine and simultaneously preventing the blade from being damaged; in addition, single blades can be detected in batches by using a standard program of the detection device, and the detection efficiency of the blades is greatly improved.
Description
Technical Field
The utility model relates to a detection device, in particular to aeroengine single blade detection device.
Background
The aeroengine blade has complex profile and large size span, and the energy conversion efficiency of the aeroengine blade is directly influenced by the quality of the profile, so that the detection of the blade is very important.
In general, the blade is fixed by a general jig and then detected by a three-coordinate method. However, the number of the blade available for fixing is very small, the rapid chuck occupies too many blade positions, which can affect the three-coordinate detection and even shield the detection part; if the universal fixture is used for fixing the blade on the single side, the other end of the blade is completely suspended or vertically placed, so that the clamping is not firm, particularly, under the condition that the single blade is very thin, the blade is easy to deform and damage parts due to the gravity influence and the force measurement influence of a three-coordinate measuring pin, and the assembly mode of the single blade is not met.
SUMMERY OF THE UTILITY MODEL
In order to overcome prior art's defect, the utility model provides an aeroengine single blade detection device, through setting up clamping device and detection device, clamping device passes through base and pressure strip and fixes the last assembly extension of single blade respectively and assembles the extension down, simulates the assembly methods of blade, simultaneously with clamping device's distribution data input detection device, the operation procedure detects in batches, has improved detection efficiency.
The technical scheme for realizing the purpose is as follows:
the utility model provides an aeroengine single-blade detection device, which comprises a working platform, wherein a plurality of clamping devices are uniformly arranged on the working platform, each clamping device is provided with a base connected with the working platform, and the upper surface of the base is provided with a positioning hole and a first groove;
a guide rod is arranged in the positioning hole, a pressing knob is screwed at the top end of the guide rod, a pressing device and a first elastic device are sleeved on the guide rod, the pressing device is positioned below the pressing knob, and the first elastic device is positioned between the pressing device and the base;
the first groove is connected with a lower assembly extension section of a single blade, the single blade is provided with an upper assembly extension section opposite to the lower assembly extension section, the upper assembly extension section is matched with the second groove, and the pressing plate is provided with a plurality of detection holes and observation holes communicated with the second groove;
the device also comprises a detection device, and the distance between the detection device and the clamping device is the distance recorded in the detection device in advance.
Further, clamping device's below is equipped with a mounting panel, the mounting panel can dismantle connect in work platform, the clamping device who is convenient for change different specifications through the mounting panel comes the different single blade of adaptation.
Furthermore, the guide rod is in interference fit with the positioning hole, so that the guide rod and the base are prevented from generating relative displacement when the pressing knob is rotated.
Furthermore, the guide rod is a cylinder, and the part of the guide rod, which is positioned in the positioning hole, is in an irregular shape, so that the guide rod and the base are ensured to be tightly matched and connected without relative rotation displacement.
Further, the pressing device and the pressing plate are integrally formed.
Furthermore, the guide rod is further sleeved with a second elastic device, the elastic force of the second elastic device is larger than that of the first elastic device, and the second elastic device is located between the pressing knob and the pressing device to protect the pressing knob and the pressing device, prevent long-time hard contact of the pressing knob and the pressing device and prolong the service life of the pressing knob and the pressing device.
Further, the detection device is a three-coordinate measuring instrument.
Has the advantages that: compared with the prior art, the utility model is different in that the utility model provides an aeroengine single-blade detection device, including detection device and the clamping device of the single-blade of solid fixed, the detection device is equipped with the detection procedure of single-blade and discerns the displacement procedure of relative distance in advance, the clamping device is equipped with base and pressure strip and fixes the lower assembly extension section and the upper assembly extension section of single-blade respectively, come the assembly clamping of simulation single-blade in the practical application, not only can effectively fix the single-blade of engine, be difficult for damaging the blade simultaneously; in addition, single blades can be detected in batches by using a standard program of the detection device, so that the detection efficiency of the blades is greatly improved, and the detection accuracy of the blades is improved.
Drawings
FIG. 1 is a schematic structural diagram of a single-blade detection device of an aircraft engine.
Fig. 2 is a schematic structural view of the middle clamping device of the present invention.
The device comprises a working platform 1, a mounting plate 11, a clamping device 2, a base 21, a first groove 22, a guide rod 23, a pressing knob 3, a pressing device 4, a pressing plate 41, a second groove 42, a detection hole 43, an observation hole 44, a first elastic device 5, a single blade 6, an assembly extension section 61-lower and an assembly extension section 62-upper.
Detailed Description
The invention will be further explained with reference to the drawings and the specific embodiments.
Referring to fig. 1 and 2, the utility model provides an aeroengine single-blade detection device, which comprises a working platform 1, six clamping devices 2 are uniformly arranged on the working platform 1, the clamping devices 2 are provided with a base 21 connected to the working platform 1, and the upper surface of the base 21 is provided with a positioning hole and a first groove 22;
a guide rod 23 is arranged in the positioning hole, a pressing knob 3 is screwed at the top end of the guide rod 23, a pressing device 4 and a first elastic device 5 are sleeved on the guide rod 23, the pressing device 4 is positioned below the pressing knob 3, the first elastic device 5 is positioned between the pressing device 4 and the base 21, the pressing device 4 is provided with a pressing plate 41, and the pressing plate 41 is provided with a second groove 42 opposite to the first groove 22;
the first groove 22 is connected with a lower assembly extension section 61 of the single blade 6, the depth and the shape of the first groove 22 are consistent with those of the lower assembly extension section 61 of the single blade 6, the single blade 6 is provided with an upper assembly extension section 62 opposite to the lower assembly extension section 61, the upper assembly extension section 62 is matched with the second groove 42, and the pressing plate 41 is provided with a detection hole 43 and two observation holes 44 communicated with the second groove 42 and respectively used for detecting the installation positions of the single blade 6 and observing the single blade 6;
still including a detection device, detection device with distance between clamping device 2 does the distance that records in advance in the detection device, detection device carries out the detection of blade surface according to the distance that records in advance to single blade 6 on clamping device 2 automatically, detects and carries out next procedure after finishing, continues to carry out the blade surface detection of next single blade 6, finishes six clamping device 2 whole detection until, accomplishes an operation promptly, can effectively realize batched automated inspection.
Preferably, a mounting plate 11 is arranged below the clamping device 2, the mounting plate 11 is detachably connected to the working platform 1, and the clamping devices 2 with different specifications can be replaced conveniently through the mounting plate 11 to adapt to different single blades 6.
Preferably, the guide rod 23 is in interference fit with the positioning hole to prevent the guide rod 23 from being displaced relative to the base 21 when the pressing knob 3 is rotated.
Preferably, the guide rod 23 is a cylinder, and the portion of the guide rod 23 located in the positioning hole is irregular, so as to ensure the tight fit connection between the guide rod 23 and the base 21 without relative rotational displacement.
Preferably, the pressing device 4 and the pressing plate 41 are integrally formed, so that the device is simplified, and the structural stability is improved.
Preferably, the guide rod 23 is further sleeved with a second elastic device, the elastic force of the second elastic device is greater than that of the first elastic device, and the second elastic device is located between the pressing knob 3 and the pressing device 4 and is used for protecting the pressing knob 3 and the pressing device 4, preventing long-time hard contact of the pressing knob 3 and the pressing device 4 and reducing the service life of the pressing knob.
Preferably, the detection device is a three-coordinate measuring machine.
It should be noted that the terms "first and second" in the present invention are used for descriptive purposes only, do not denote any order, are not to be construed as indicating or implying any relative importance, and are to be interpreted as names.
The above embodiments are merely preferred embodiments of the present disclosure, which are not intended to limit the present disclosure, and any modifications, equivalents, improvements and the like, which are within the spirit and principle of the present disclosure, should be included in the scope of the present disclosure.
Claims (7)
1. The single-blade detection device for the aircraft engine is characterized by comprising a working platform, wherein a plurality of clamping devices are uniformly arranged on the working platform, each clamping device is provided with a base connected to the working platform, and the upper surface of each base is provided with a positioning hole and a first groove;
a guide rod is arranged in the positioning hole, a pressing knob is screwed at the top end of the guide rod, a pressing device and a first elastic device are sleeved on the guide rod, the pressing device is positioned below the pressing knob, and the first elastic device is positioned between the pressing device and the base;
the first groove is connected with a lower assembly extension section of a single blade, the single blade is provided with an upper assembly extension section opposite to the lower assembly extension section, the upper assembly extension section is matched with the second groove, and the pressing plate is provided with a plurality of detection holes and observation holes communicated with the second groove;
the device also comprises a detection device, and the distance between the detection device and the clamping device is the distance recorded in the detection device in advance.
2. The aircraft engine single blade detection device of claim 1, wherein:
the clamping device is characterized in that a mounting plate is arranged below the clamping device, and the mounting plate is detachably connected to the working platform.
3. The aircraft engine single blade detection device of claim 1, wherein:
the guide rod is in interference fit with the positioning hole.
4. The aircraft engine single blade detection device of claim 1, wherein:
the guide rod is a cylinder, and the part of the guide rod, which is positioned in the positioning hole, is in an irregular shape.
5. The aircraft engine single blade detection device of claim 1, wherein:
the pressing device and the pressing plate are integrally formed.
6. The aircraft engine single blade detection device of claim 1, wherein:
the guide rod is further sleeved with a second elastic device, the elastic force of the second elastic device is larger than that of the first elastic device, and the second elastic device is located between the pressing knob and the pressing device.
7. The aircraft engine single blade detection device of claim 1, wherein:
the detection device is a three-coordinate measuring instrument.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921357504.3U CN210293151U (en) | 2019-08-21 | 2019-08-21 | Aeroengine single-blade detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921357504.3U CN210293151U (en) | 2019-08-21 | 2019-08-21 | Aeroengine single-blade detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210293151U true CN210293151U (en) | 2020-04-10 |
Family
ID=70063277
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921357504.3U Active CN210293151U (en) | 2019-08-21 | 2019-08-21 | Aeroengine single-blade detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210293151U (en) |
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2019
- 2019-08-21 CN CN201921357504.3U patent/CN210293151U/en active Active
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