Aircraft engine blade tip wear depth detection device

Abstract

The application discloses an aero-engine blade tip wear depth detection device, which comprises a detection needle group, a locking sleeve and a comparison piece. The detection needle group comprises a mounting shell, mounting holes arranged on the mounting shell and probes arranged in the mounting holes. The mounting holes are arranged in multiple, and the mounting holes are arranged along the length direction of the mounting shell. The probes and the mounting holes are arranged one by one. The detection ends of the multiple probes are arranged opposite to the wear ends of the parts to be repaired. The mounting shell is used for moving towards the direction close to the parts to be repaired to apply a preset axial force to the multiple probes, so that the multiple probes are inserted into the wear grooves of the wear ends of the parts to be repaired. The locking sleeve is used for applying a radial pressure to the probes after the detection of the detection needle group is completed to prevent the probes from sliding relative to the mounting shell. The comparison piece is used for comparing the extension length of the detection ends of the probes relative to the mounting shell after the detection of the detection needle group is completed to judge the processing mode of the parts to be repaired.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine fault inspection, in particular, to an aero-engine blade tip wear depth detection device. BACKGROUND

[0002] In the field of aero-engines, in order to ensure the working efficiency of the rotor of the aero-engine, a certain amount of scraping is allowed between the aero-engine blade tip and the sealing grate matched therewith. Therefore, when the fault inspection is carried out during the repair of the aero-engine, it is found that there is a wear groove on the aero-engine blade tip, and it is necessary to detect the wear depth of the wear groove on the aero-engine blade tip, and then to judge which type of fault the aero-engine blade tip belongs to according to the wear depth, so as to select a corresponding mode to process the aero-engine blade tip according to the fault type. At present, the aero-engine blade tip wear depth detection mainly adopts visual inspection, probe, sample paste and optical measurement methods, but the detection results of the first two detection methods have more subjective components and are difficult to quantify, and the accuracy is low, and the detection cost of the last detection method is high and the efficiency is low. Therefore, the above methods do not meet the repair requirements of large quantities and high efficiency of the aero-engine blade tip. SUMMARY

[0003] The present application provides an aero-engine blade tip wear depth detection device to solve the technical problems of low accuracy, high cost and low efficiency of the existing aero-engine blade tip wear depth detection method.

[0004] According to one aspect of the present application, an aero-engine blade tip wear depth detection device is provided, which comprises a detection needle group, a locking sleeve and a comparison piece. The detection needle group comprises a mounting shell, a mounting hole arranged on the mounting shell, and a probe arranged in the mounting hole for sliding relative to the mounting shell under a preset axial force. The mounting hole is provided with a plurality of mounting holes, and the mounting holes are arranged at intervals along the length direction of the mounting shell. The probe and the mounting hole are arranged one by one. The detection ends of the plurality of probes are arranged opposite to the wear end of the repaired part. The mounting shell is used to move towards the direction close to the repaired part to apply a preset axial force to the plurality of probes, so as to make the plurality of probes extend into the wear groove of the wear end of the repaired part. The locking sleeve is used to apply a radial pressure to the probe after the detection of the detection needle group is completed to prevent the probe from sliding relative to the mounting shell. The comparison piece is used to compare the extension length of the detection end of the probe relative to the mounting shell after the detection of the detection needle group is completed to judge the processing mode of the repaired part.

[0005] As a further improvement of the above technical solution:

[0006] Further, the comparison piece is a stepped shaft, the stepped shaft is sequentially arranged with a plurality of stepped steps in the axial direction, the radial height of the plurality of stepped steps gradually increases or gradually decreases along the axial direction, and a stepped difference for comparing the protruding length of the detection end of the probe relative to the mounting shell is formed between the adjacent two stepped steps.

[0007] Further, the stepped shaft sequentially includes, from outside to inside in the radial direction, a first stepped difference for judging whether the repair of the to-be-repaired part is repaired by adopting a repair process, a second stepped difference for judging whether the repair of the to-be-repaired part is repaired by adopting a spraying process, and a third stepped difference for judging whether the to-be-repaired part is scrapped.

[0008] Further, the first stepped difference is 0.3mm, the second stepped difference is 0.6mm, and the third stepped difference is 0.9mm.

[0009] Further, the locking sleeve includes a first locking rod, a second locking rod and an elastic piece, the free end of the first locking rod and the free end of the second locking rod are hinged and cross arranged, the locking end of the first locking rod is arranged with a first locking part, the locking end of the second locking rod is arranged with a second locking part, and the two ends of the elastic piece are connected with the first locking rod and the second locking rod respectively and used to drive the first locking part and the second locking part to approach each other to press against the mounting shell and thus exert radial pressure on the probe.

[0010] Further, the end surface of the mounting shell towards the to-be-repaired part is horizontally arranged.

[0011] Further, the number of probes is 13-17.

[0012] Further, the diameter of the probe is 0.8mm-1mm.

[0013] Further, the needle tip cone angle of the probe is 13°-15°.

[0014] Further, the detection needle group further includes an elastic layer arranged on the inner wall of the mounting hole and used to exert radial pressure on the probe.

[0015] The present application has the following beneficial effects:

[0016] The aero-engine blade tip wear depth detection device of the application, the repaired parts are placed horizontally or vertically, a plurality of probes are installed in the corresponding mounting holes of the mounting shell, a predetermined axial force is applied to the probes, the detection ends of the plurality of probes are extended out of the mounting shell and are in the same horizontal plane, then the detection ends of the plurality of probes are attached to the worn ends of the repaired parts, an acting force is applied to the mounting shell to make the mounting shell move towards the repaired parts, and then the plurality of probes are extended into the wear grooves of the worn ends of the repaired parts under the predetermined axial force, so that the wear grooves are fully covered, the detection efficiency is improved, after the mounting shell is attached to the worn ends of the repaired parts, the depth detection of the wear grooves is completed, the radial pressure is applied to the probes by the locking sleeve to prevent the probes from sliding relative to the mounting shell, the position of the probes is prevented from changing, the accuracy of the detection result is improved, the probe with the longest extension length of the detection end relative to the mounting shell is reserved, and the detection ends of the other probes are withdrawn into the mounting shell, finally, the detection end of the probe is compared with the comparison piece to quickly determine which length range the extension length of the detection end of the probe relative to the mounting shell is in, and then the wear depth of the wear groove on the repaired part is quickly determined to be in which depth interval, so that the corresponding processing mode can be quickly selected to process the repaired part, the detection needle group, the locking sleeve and the comparison piece are cooperated with each other to quickly detect which depth interval the maximum wear depth of the wear groove on the repaired part is in, so that the most appropriate processing mode of the repaired part can be quickly determined according to the depth interval, the accuracy of the detection result is high, the detection cost is low, and the detection efficiency is high, which meets the requirements of large batch and high efficiency repair of aero-engine blade tips, has strong practicality, and is suitable for wide promotion and application.

[0017] In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. The present application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate the preferred embodiments of the application, and assist in the explanation of the application. In the drawings, the same reference numbers represent the same elements throughout the several views of the drawings:

[0019] Figure 1 is a structure schematic view of a detection needle group in an aero-engine blade tip wear depth detection device of a preferred embodiment of the application;

[0020] Figure 2 is a partial structure schematic view of an aero-engine blade tip wear depth detection device of a preferred embodiment of the application;

[0021] Figure 3Figure 3 is a structure schematic diagram of a comparison piece in an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application;

[0022] Figure 4 Figure 4 is a structure schematic diagram of a detection needle group during detection in an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application.

[0023] Legend:

[0024] 100, detection needle group; 110, mounting shell; 120, probe; 200, locking sleeve; 210, first locking rod; 211, first locking part; 220, second locking rod; 221, second locking part; 230, elastic piece; 300, comparison piece; 310, stepped step. DETAILED DESCRIPTION

[0025] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following.

[0026] Figure 1 Figure 3 is a structure schematic diagram of a comparison piece in an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application; Figure 2 Figure 2 is a partial structure schematic diagram of an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application; Figure 3 Figure 3 is a structure schematic diagram of a comparison piece in an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application; Figure 4 Figure 4 is a structure schematic diagram of a detection needle group during detection in an aero-engine blade tip wear depth detection device according to a preferred embodiment of the present application.

[0027] As Figures 1-4The aero-engine blade tip wear depth detection device of the embodiment shown comprises a detection needle group 100, a locking sleeve 200 and a comparison piece 300. The detection needle group 100 comprises a mounting shell 110, mounting holes arranged on the mounting shell 110 and probes 120 arranged in the mounting holes for sliding relative to the mounting shell 110 under a preset axial force. The mounting holes are arranged in a length direction of the mounting shell 110 at intervals. The probes 120 and the mounting holes are arranged one by one. The detection ends of the plurality of probes 120 are arranged opposite the worn end of the part to be repaired. The mounting shell 110 is used to move towards the part to be repaired to apply the preset axial force to the plurality of probes 120, so that the plurality of probes 120 extend into the wear grooves of the worn end of the part to be repaired. The locking sleeve 200 is used to apply radial pressure to the probes 120 after the detection of the detection needle group 100 is completed to prevent the probes 120 from sliding relative to the mounting shell 110. The comparison piece 300 is used to compare the extension length of the detection end of the probe 120 relative to the mounting shell 110 after the detection of the detection needle group 100 is completed to determine the processing mode of the part to be repaired.Specifically, the aero-engine blade tip wear depth detection device of the present application, the repaired parts are placed horizontally or vertically, a plurality of probes 120 are installed in the corresponding mounting holes of the mounting shell 110, a predetermined axial force is applied to the probes 120, so that the detection ends of the plurality of probes 120 extend out of the mounting shell 110 and are in the same horizontal plane, then the detection ends of the plurality of probes 120 are attached to the worn ends of the repaired parts, an acting force is applied to the mounting shell 110, so that the mounting shell 110 moves towards the repaired parts, and then the plurality of probes 120 are respectively inserted into the wear grooves of the worn ends of the repaired parts, so as to realize comprehensive coverage of the wear grooves, improve the detection efficiency, after the mounting shell 110 is attached to the worn ends of the repaired parts, the depth detection of the wear grooves is completed, the radial pressure is applied to the probes 120 by the locking sleeve 200 to prevent the probes 120 from sliding relative to the mounting shell 110, so as to avoid the position of the probes 120 from changing, improve the accuracy of the detection results, the probe 120 with the longest extension length of the detection end relative to the mounting shell 110 is reserved, and the detection ends of the other probes 120 are withdrawn into the mounting shell 110, finally, the detection end of the probe 120 is compared with the comparison piece 300, so as to quickly judge which length range the extension length of the detection end of the probe 120 relative to the mounting shell 110 is in, and then the wear depth of the wear groove on the repaired part is quickly obtained, so that the corresponding processing mode can be quickly selected to process the repaired part, the detection needle group 100, the locking sleeve 200 and the comparison piece 300 are cooperated with each other to quickly detect which depth range the maximum wear depth of the wear groove on the repaired part is in, so that the most appropriate processing mode of the repaired part can be quickly judged according to the depth range, the accuracy of the detection result is high, the detection cost is low, and the detection efficiency is high, which meets the requirements of large batch and high efficiency repair of aero-engine blade tips, has strong practicality, and is suitable for wide promotion and application. It should be understood that the axial length of the probe 120 is greater than the axial length of the mounting hole, so as to adjust the extension length of the detection end of the probe 120 relative to the mounting shell 110. It should be understood that even if the probe 120 is subjected to the radial pressure applied by the locking sleeve 200, the axial force can still be applied to overcome the friction force generated by the radial pressure, and then the detection end of the probe 120 is withdrawn into the mounting shell 110. It should be understood that the worn end surface of the large blade tip is a circular arc surface, so a plurality of detection needle groups 100 can be arranged to detect synchronously, so as to improve the detection efficiency and accuracy.

[0028] As Figure 3As shown, in the embodiment, the comparison piece 300 is a stepped shaft, and the stepped shaft is sequentially arranged with a plurality of stepped steps 310 along the axial direction, the radial height of the plurality of stepped steps 310 gradually increases or gradually decreases along the axial direction, and a stepped difference for comparing the extension length of the detection end of the probe 120 relative to the mounting shell 110 is formed between the adjacent two stepped steps 310. Specifically, a plurality of stepped differences are formed by the plurality of stepped steps 310, and the stepped differences can be adaptively selected according to requirements, so as to compare the extension length of the detection end of the probe 120 relative to the mounting shell 110 through the stepped differences, to indirectly and quickly obtain the wear depth of the wear groove on the repaired part, facilitate the quick judgment of the best processing mode of the repaired part, greatly improve the efficiency, and be suitable for the detection and judgment of a large number of repaired parts.

[0029] As shown in the figure, Figure 3 In the embodiment, the stepped shaft sequentially includes, from the outside to the inside along the radial direction, a first stepped difference for judging whether to repair the repaired part by using a repair process, a second stepped difference for judging whether to repair the repaired part by using a spraying process, and a third stepped difference for judging whether the repaired part is scrapped. Specifically, when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within the first stepped difference, the repaired part is repaired by using the repair process, when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within the second stepped difference, the repaired part is repaired by using the spraying process, and when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within the third stepped difference, the repaired part is scrapped and no longer repaired.

[0030] As shown in the figure, Figure 3 In the embodiment, the first stepped difference is 0.3mm, the second stepped difference is 0.6mm, and the third stepped difference is 0.9mm. Specifically, in an embodiment, when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within 0mm-0.3mm, the repaired part is repaired by using the repair process, when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within 0.3mm-0.6mm, the repaired part is repaired by using the spraying process, and when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is within 0.6mm-0.9mm, the repaired part is scrapped and no longer repaired. It should be understood that if the scrapped treatment of the repaired part is the final processing means, that is, when the extension length of the detection end of the probe 120 relative to the mounting shell 110 is greater than 0.9mm, the repaired part is still scrapped.

[0031] As shown in the figure, Figure 2As shown, in the embodiment, the locking sleeve 200 comprises a first locking rod 210, a second locking rod 220 and an elastic member 230, the free ends of the first locking rod 210 and the second locking rod 220 are hinged and cross arranged, the locking end of the first locking rod 210 is arranged with a first locking part 211, the locking end of the second locking rod 220 is arranged with a second locking part 221, and the two ends of the elastic member 230 are connected with the first locking rod 210 and the second locking rod 220 respectively and used to drive the first locking part 211 and the second locking part 221 to approach each other to press against the mounting shell 110 and thus exert radial pressure on the probe 120. Specifically, since the free ends of the first locking rod 210 and the second locking rod 220 are hinged and cross arranged, that is, when the free ends of the first locking rod 210 and the second locking rod 220 are away from or approach each other, the locking ends of the first locking rod 210 and the second locking rod 220 are synchronously away from or approach each other, first, the free ends of the first locking rod 210 and the second locking rod 220 are away from each other, so that the locking ends of the first locking rod 210 and the second locking rod 220 are away from each other against the elastic force of the elastic member 230, and thus the first locking part 211 and the second locking part 221 are arranged at opposite ends of the mounting shell 110, so that after the force is cancelled, the elastic member 230 drives the first locking part 211 and the second locking part 221 to approach each other to press against the mounting shell 110 and thus exert radial pressure on the probe 120. Optionally, the elastic member 230 is a tension spring.

[0032] As shown in Figure 1 and Figure 4 As shown, in the embodiment, the mounting shell 110 is horizontally arranged towards the end face of the repaired part. Specifically, by horizontally arranging the mounting shell 110 towards the end face of the repaired part, during the detection of the needle group 100, the end face of the mounting shell 110 towards the repaired part is as much as possible to fit the worn end of the repaired part, and thus the accuracy of the detection result is indirectly improved.

[0033] In the embodiment, the number of probes 120 is 13-17. Specifically, when the number of probes 120 is between 13 and 17, the worn end of the repaired part can be fully covered, the detection efficiency is improved, and the number of probes 120 is appropriate, facilitating movement and simple detection operation; when the number of probes 120 is less than 13, the worn end of the repaired part cannot be fully covered, and multiple detections are required, resulting in low detection efficiency; when the number of probes 120 is more than 17, the number of probes 120 is too large, and the detection operation is complicated.

[0034] In the embodiment, the diameter of the probe 120 is 0.8-1 mm. Specifically, when the diameter of the probe 120 is between 0.8 mm and 1 mm, the probe 120 is low in processing difficulty, the number of the probes 120 arranged on the mounting shell 110 is appropriate, and the probe 120 is easy to extend into the wear groove of the repaired part, and the detection efficiency is high; when the diameter of the probe 120 is less than 0.8 mm, the probe 120 is high in processing difficulty; and when the diameter of the probe 120 is greater than 1 mm, the number of the probes 120 arranged on the mounting shell 110 is small, and the probe 120 can not extend into the wear groove of the repaired part, affecting the accuracy of the detection result.

[0035] In the embodiment, the needle tip angle of the probe 120 is 13-15°. It should be understood that the needle part of the probe 120 is the detection end of the probe 120. Specifically, when the needle tip angle of the probe 120 is between 13° and 15°, the probe 120 is low in processing difficulty, and is easy to extend into the wear groove of the repaired part; when the needle tip angle of the probe 120 is less than 13°, the probe 120 is high in processing difficulty, and is low in strength, and is easy to be bent in the pressure process, affecting the accuracy of the detection result; and when the needle tip angle of the probe 120 is greater than 15°, the probe 120 is not easy to extend into the bottom of the wear groove of the repaired part, affecting the accuracy of the detection result.

[0036] In the embodiment, the detection needle group 100 further comprises an elastic layer arranged on the inner wall of the mounting hole and used for applying radial pressure to the probe 120. Specifically, the elastic layer applies radial pressure to the probe 120, so that the probe 120 is fixed in the mounting hole when not subjected to external force, and when the mounting shell 110 is subjected to external force, the elastic layer applies reverse force to the probe 120, and then drives the probe 120 to extend into the wear groove of the repaired part to detect the wear depth.

[0037] The above merely describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft engine blade tip wear depth detection device, characterized by, The device comprises a detection needle group (100), a locking sleeve (200) and a comparison piece (300). The detection needle group (100) comprises a mounting shell (110), mounting holes arranged on the mounting shell (110), and probes (120) arranged in the mounting holes and used to slide relative to the mounting shell (110) under a preset axial force. The mounting holes are arranged in a length direction of the mounting shell (110) and are spaced apart. The probes (120) are arranged one by one in the mounting holes. The detection ends of the probes (120) are arranged opposite to a worn end of a repaired part. The mounting shell (110) is used to move towards the repaired part to apply the preset axial force to the probes (120) so that the probes (120) extend into a wear groove of the worn end of the repaired part. The locking sleeve (200) is used to apply a radial pressure to the probes (120) after the detection of the detection needle group (100) is completed to prevent the probes (120) from sliding relative to the mounting shell (110). The comparison piece (300) is used to compare the extension length of the detection ends of the probes (120) relative to the mounting shell (110) to determine a treatment method of the repaired part after the detection of the detection needle group (100) is completed. The comparison piece (300) is a stepped shaft. The stepped shaft comprises a plurality of stepped stages (310) arranged in an axial direction. The radial heights of the stepped stages (310) gradually increase or decrease in the axial direction. A stepped difference is formed between adjacent two stepped stages (310) to compare the extension length of the detection ends of the probes (120) relative to the mounting shell (110). The stepped shaft comprises, from outside to inside in a radial direction, a first stepped difference used to determine whether a repaired part is repaired by a repair process, a second stepped difference used to determine whether the repaired part is repaired by a spraying process, and a third stepped difference used to determine whether the repaired part is scrapped. The locking sleeve (200) comprises a first locking rod (210), a second locking rod (220), and an elastic member (230). The free ends of the first locking rod (210) and the second locking rod (220) are hinged and cross arranged. The first locking rod (210) is provided with a first locking portion (211) on the locking end. The second locking rod (220) is provided with a second locking portion (221) on the locking end. The two ends of the elastic member (230) are connected with the first locking rod (210) and the second locking rod (220) respectively and used to drive the first locking portion (211) and the second locking portion (221) to approach each other to press against the mounting shell (110) to apply a radial pressure to the probes (120).

2. The aeroengine blade tip wear depth detection apparatus of claim 1, wherein, The first stepped difference is 0.3 mm, the second stepped difference is 0.6 mm, and the third stepped difference is 0.9 mm.

3. The aeroengine blade tip wear depth detection apparatus of any of claims 1-2, wherein, The end surface of the mounting shell (110) towards the repaired part is horizontally arranged.

4. The aeroengine blade tip wear depth detection apparatus of any of claims 1-2, wherein, The number of the probes (120) is 13-17.

5. The aeroengine blade tip wear depth detection apparatus of any one of claims 1-2, wherein, The diameter of the probes (120) is 0.8-1 mm.

6. The aeroengine blade tip wear depth detection apparatus of any one of claims 1-2, wherein, The needle tip cone angle of the probes (120) is 13-15°.

7. The aeroengine blade tip wear depth detection apparatus of any of claims 1-2, wherein, The detection needle group (100) further comprises an elastic layer arranged on the inner wall of the mounting hole for applying radial pressure to the probe (120).

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