In-situ eddy current flaw detection device and method for aircraft engine compressor disk

Abstract

The present invention discloses an in-situ eddy current flaw detection device and flaw detection method for an aircraft engine compressor disk. The flaw detection device includes an eddy current probe and a limiting step plate. The eddy current probe is retractably arranged on the limiting step plate. The bottom of the limiting step plate is vertically fixed with a limiting step, and the limiting step is provided with at least one sliding component. The present invention fixes and limits the eddy current probe through the matching structure of the probe rod and the limiting step plate, so that the eddy current probe is in a vertical state and can maintain a good fit with the disk surface of the compressor disk, ensuring that the flaw detection process will not be affected by human factors and produce a lifting effect, and the scanning area and scanning spacing are adjusted by retracting the probe rod, so that the flaw detection scanning area can cover the entire compressor disk; the present invention can effectively ensure the stability and reliability of the flaw detection structure, can reduce the number of repeated flaw detections, thereby effectively reducing the labor intensity of the staff, and can effectively shorten the delivery cycle of maintenance products.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engine maintenance, in particular to an in-situ eddy current flaw detection device for an aircraft engine compressor disk and an in-situ eddy current flaw detection method for an aircraft engine compressor disk. Background Art

[0002] During the maintenance process of aircraft engine high-pressure compressor discs, in-situ eddy current testing is required for the contours and spokes of the annular compressor disc in the in-situ assembly state. Currently, when conducting eddy current testing in the industry, the lift-off effect between the eddy current probe and the disc surface is suppressed by pressing the eddy current probe with fingers, and the scanning area and scanning spacing during the testing process are determined by marking the partitions. In the in-situ assembly state, the testing space is small, and the fit between the eddy current probe and the disc surface cannot be guaranteed. The change in eddy current impedance caused by the lift-off effect will interfere with defect judgment, and multiple repeated testing is required to ensure the testing results. At the same time, because the compressor disc is not visually accessible in the assembly state, there are quality risks of incomplete coverage of the inspection scanning area and excessive scanning spacing. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide an in-situ eddy current flaw detection device for an aircraft engine compressor disk, which can effectively improve the stability of the flaw detection process and the reliability of the flaw detection results.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is: an in-situ eddy current flaw detection device for an aircraft engine compressor disc, including an eddy current probe and a limit step plate. The eddy current probe is retractably arranged on the limit step plate, and the bottom of the limit step plate is vertically fixed with a limit step, and at least one sliding component is provided on the limit step.

[0005] Furthermore, a probe rod is connected to the eddy current probe, and a through hole that is gap-matched with the probe rod is provided on the limiting step plate.

[0006] Furthermore, the circumferential surface of the probe rod is provided with scale lines extending along the length direction of the probe rod.

[0007] Furthermore, a clamping portion is fixed to the end of the probe rod that is not connected to the eddy current probe, and a limiting groove matching the clamping portion is provided on the limiting step plate. The limiting groove is connected to the through hole on the limiting step plate and is perpendicular to each other.

[0008] Furthermore, a locking screw is also included, which is threadedly connected to the through hole set in the limiting step plate, and the end of the locking screw extends into the through hole and abuts against the circumference of the probe rod.

[0009] Furthermore, the sliding component is a ball bearing rotatably arranged on the limiting step.

[0010] Furthermore, there are two sliding components, which are symmetrically arranged on both sides of the eddy current probe.

[0011] The present invention also discloses a flaw detection method using the above-mentioned aircraft engine compressor disc in-situ eddy current flaw detection device, comprising the following steps:

[0012] Step 1: Coupling the limiting step of the in-situ eddy current flaw detection device of the aircraft engine compressor disk to the inner hole arc of the compressor disk;

[0013] Step 2: vertically attach the eddy current probe of the in-situ eddy current flaw detection device for the compressor disk of the aircraft engine to the disk surface of the compressor disk;

[0014] Step 3: Under the limiting action of the limiting step, the in-situ eddy current flaw detection device of the aircraft engine compressor disk is scanned along the inner hole arc of the compressor disk through the sliding component to complete the eddy current flaw detection of the radial area of ​​the compressor disk;

[0015] Step 4: Adjust the telescopic length of the eddy current probe to change the inspection scanning area and perform eddy current inspection in the corresponding area.

[0016] The beneficial effects of the present invention are as follows: the present invention fixes and limits the eddy current probe through the matching structure of the probe rod and the limiting step plate, so that the eddy current probe is in a stable vertical state and can maintain a good fit with the disk surface of the compressor disk, and moves stably against the inner hole arc surface of the compressor disk through the sliding component during the flaw detection process, ensuring that the flaw detection process will not be affected by human factors and produce a lifting effect, and the scanning area and the scanning spacing are adjusted by extending and retracting the probe rod, so that the flaw detection scanning area can cover the entire compressor disk; the present invention can effectively ensure the stability and reliability of the flaw detection structure, can reduce the number of repeated flaw detections, thereby effectively reducing the labor intensity of the staff, and can effectively shorten the delivery cycle of maintenance products. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A bottom view of the in-situ eddy current flaw detection device for an aircraft engine compressor disk according to the present invention;

[0018] Figure 2 It is a side view of the in-situ eddy current flaw detection device for an aircraft engine compressor disk according to the present invention.

[0019] Markings in the figure are: 100-eddy current probe, 200-limiting step plate, 210-limiting step, 220-sliding part, 230-limiting groove, 300-probe rod, 400-clamping part, 500-locking screw. DETAILED DESCRIPTION

[0020] To facilitate understanding of the present invention, the present invention will be further described below with reference to the accompanying drawings.

[0021] like Figure 1 and Figure 2 As shown, the in-situ eddy current flaw detection device for an aircraft engine compressor disk disclosed in the present invention improves the conventional eddy current probe 100 in the prior art. A limiting step plate 200 is added to the eddy current probe 100 for installation of the eddy current probe 100. A limiting step 210 fixed to the bottom of the limiting step plate 200 is used to limit the entire flaw detection device to ensure the stability of the eddy current probe 100 during the flaw detection process, thereby ensuring the reliability of the flaw detection structure. In addition, the eddy current probe 100 is configured as a retractable structure in the present invention, so that the eddy current probe 100 can be retracted and set on the limiting step plate 200. The range of the scanning area and the size of the scanning interval of the eddy current probe 100 can be adjusted by retracting the eddy current probe 100, so that the scanning area of ​​the flaw detection process using the in-situ eddy current flaw detection device for an aircraft engine compressor disk disclosed in the present invention can cover the entire compressor disk.

[0022] In addition, since the inner hole wall surface of the compressor disk to be inspected is a curved surface, the inspection device must be able to closely fit the inner hole curved surface of the compressor disk during the inspection to ensure the reliability of the inspection results. Therefore, in the present invention, a sliding component 220 is also installed on the limiting step 210 of the limiting step plate 200. The sliding component 220 firstly converts the friction between the aircraft engine compressor disk in-situ eddy current inspection device disclosed in the present invention and the compressor disk into sliding friction, reducing the friction between the two, thereby preventing the eddy current probe 100 from jumping during the rotational scanning process; secondly, the sliding component 220 can move along the inner hole curved surface of the compressor disk, ensuring the consistency of the scanning radius during the inspection process; and finally, the sliding component 220 can quickly couple the limiting step 210 to the inner control circular arc surface of the compressor disk, thereby realizing rapid positioning of the inspection device. In this embodiment, The sliding component 220 adopts a ball bearing rotatably arranged on the limiting step 210; further, there are two sliding components 220, and the two sliding components 220 are symmetrically arranged on both sides of the eddy current probe 100 to ensure the balance of the flaw detection device when moving along the inner hole arc surface of the compressor disk.

[0023] In the present invention, the installation of the eddy current probe 100 on the limiting step plate 200 is achieved by the probe rod 300. Figure 1 and Figure 2As shown, the eddy current probe 100 is mounted on one end of the probe rod 300. A through hole is provided on the limiting step plate 200, extending horizontally through the limiting step plate 200. The probe rod 300 passes through the through hole, with a clearance fit between the probe rod 300 and the through hole. Providing a through hole on the limiting step plate 200 that mates with the probe rod 300 not only enables the installation of the eddy current probe 100, but also allows the probe rod 300 to be radially limited by the through hole, thereby limiting the eddy current probe 100 and ensuring that the eddy current probe 100 remains vertical during the scanning process.

[0024] Furthermore, in order to enable the staff to monitor the range and scanning interval of the scanning area during the flaw detection process in real time, and also to help the staff accurately adjust the telescopic length of the eddy current probe 100, the present invention provides scale lines on the probe rod 300. The scale lines are set on the circumference of the probe rod 300 and extend along the length direction of the probe rod 300.

[0025] In order to ensure the verticality and stability of the eddy current probe 100 during the scanning process, the present invention adds a clamping portion 400 to the probe rod 300. Figure 1 and Figure 2 As shown, the clamping part 400 is fixed at the end of the probe rod 300 that is not connected to the eddy current probe 100. At the same time, a limiting groove 230 that matches the clamping part 400 is provided on the limiting step plate 200. The groove type of the limiting groove 230 matches the shape of the clamping part 400 so that the clamping part 400 can be embedded in the limiting groove 230. In this embodiment, the clamping part 400 adopts a rectangular structure, so the limiting groove 230 is also set to a corresponding rectangular groove; the limiting groove 230 is connected to the through hole on the limiting step plate 200 and the two are perpendicular to each other. Then, through the limiting effect of the limiting groove 230 on the clamping part 400, the clamping part 400 can only move horizontally in the extension direction of the through hole, thereby ensuring that the probe rod 300 fixedly connected to the clamping part 400 always remains vertical, thereby ensuring that the eddy current probe 100 is always in a vertical state during the scanning process.

[0026] As described above, the eddy current probe 100 in the present invention can be telescopically arranged on the limiting step plate 200, which is specifically achieved by making the through hole on the limiting step plate 200 have a radial limiting effect on the eddy current probe 100. Since there is a clearance fit between the through hole on the limiting step plate 200 and the probe rod 300, the probe rod 300 can only move axially along the through hole and cannot move radially. By moving the probe rod 300 axially along the through hole, the relative translation between the probe rod 300 and the through hole can be achieved, thereby realizing the telescopic movement of the eddy current probe 100, and ultimately achieving the effect of changing the scanning area range and the scanning gap during the flaw detection process. After the eddy current probe 100 is extended or retracted, it is also necessary to fix the eddy current probe 100. In the present invention, this is achieved by a locking screw 500. An internal threaded hole connected to the through hole is provided on the limiting step plate 200, so that the locking screw 500 is threadedly connected to the internal threaded hole. The end of the locking screw 500 passes through the internal threaded hole and extends into the through hole and abuts against the circumferential surface of the probe rod 300. The probe rod 300 can be locked by rotating the locking screw 500. After rotating the locking screw 500 in the opposite direction, the telescopic length of the eddy current probe 100 can be adjusted by extending or retracting the probe rod 300.

[0027] When using the above-mentioned aircraft engine compressor disc in-situ eddy current flaw detection device to perform flaw detection work, follow the steps below:

[0028] Step 1: coupling the limiting step 210 of the in-situ eddy current flaw detection device for the compressor disk of an aircraft engine to the inner hole arc of the compressor disk;

[0029] Step 2: vertically attach the eddy current probe 100 of the in-situ eddy current flaw detection device for the compressor disk of the aircraft engine to the disk surface of the compressor disk;

[0030] Step 3: Under the limiting action of the limiting step 210, the in-situ eddy current flaw detection device of the aircraft engine compressor disk is scanned along the inner hole arc of the compressor disk through the sliding component 220 to complete the eddy current flaw detection of the radial area of ​​the compressor disk;

[0031] Step 4: Adjust the telescopic length of the eddy current probe 100 to change the flaw detection scanning area, and perform eddy current flaw detection in the corresponding area.

Claims

1. An in-situ eddy current flaw detection device for an aircraft engine compressor disk, comprising an eddy current probe (100), characterized in that: The eddy current probe (100) is further provided with a limiting step plate (200), the eddy current probe (100) is scalably arranged on the limiting step plate (200), the bottom of the limiting step plate (200) is vertically fixed with a limiting step (210), and the limiting step (210) is provided with at least one sliding component (220); the eddy current probe (100) is connected to a probe rod (300), and the limiting step plate (200) is provided with a through hole that is clearance-matched with the probe rod (300); a clamping portion (400) is fixed to one end of the probe rod (300) that is not connected to the eddy current probe (100), and the limiting step plate (200) is provided with a through hole that is clearance-matched with the clamping portion The eddy current probe (100) is provided with a limiting groove (230) that matches the limiting step (400), and the limiting groove (230) is connected to the through hole on the limiting step plate (200) and is perpendicular to each other; it also includes a locking screw (500), the locking screw (500) is threadedly connected to the through hole provided on the limiting step plate (200), the end of the locking screw (500) extends into the through hole and abuts against the circumference of the probe rod (300); the sliding component (220) is a ball bearing rotatably provided on the limiting step (210); the number of the sliding components (220) is two, and the two sliding components (220) are symmetrically provided on both sides of the eddy current probe (100).

2. The in-situ eddy current flaw detection device for an aircraft engine compressor disk according to claim 1, characterized in that: The circumferential surface of the probe rod (300) is provided with scale lines extending along the length direction of the probe rod (300).

3. A method for flaw detection using the in-situ eddy current flaw detection device for an aircraft engine compressor disk according to claim 1 or 2, characterized in that: The following steps are involved: Step 1: coupling the limiting step (210) of the in-situ eddy current flaw detection device for the compressor disk of an aircraft engine to the inner hole arc of the compressor disk; Step 2: vertically attaching the eddy current probe (100) of the in-situ eddy current flaw detection device for the compressor disk of an aircraft engine to the disk surface of the compressor disk; Step 3: Under the limiting action of the limiting step (210), the in-situ eddy current flaw detection device of the aircraft engine compressor disk is scanned along the inner hole arc of the compressor disk through the sliding component (220), thereby completing the eddy current flaw detection of the radial area of ​​the compressor disk; Step 4: Adjust the telescopic length of the eddy current probe (100) to change the flaw detection scanning area, and perform eddy current flaw detection in the corresponding area.

Images