Aero-engine blade detection device

Abstract

The invention discloses an aero-engine blade detection device which comprises a detection rod, the detection rod comprises a connecting part and a detection part which are connected with each other, one end of the connecting part is connected with the detection part, a first containing cavity is formed in the detection part, and an eddy current coil is arranged in the first containing cavity; the axial direction of the eddy current coil is perpendicular to the length direction of the detection part, the appearance of the detection part is matched with the curvature of the aero-engine blade, and the detection part is used for extending into the aero-engine and acting on the blade through electromagnetic induction to generate an induction signal; and the detector is in communication connection with the detection part and is used for receiving the induction signal generated by the detection part and determining the leaf quality information of the leaf according to the induction signal. Therefore, the eddy current coil located on the detection part can extend into the aero-engine to detect the blade, and blade quality information of the blade is obtained.

Description

Technical Field

[0001] The present application belongs to the field of aircraft engine detection, and in particular, relates to an aircraft engine blade detection device. Background Art

[0002] Aircraft engine rotors operate under high temperatures, high centrifugal loads, aerodynamic loads, vibration and other alternating loads. The back of the blade is a stress concentration area, which is prone to fatigue cracks. In recent years, there have been several cases of blades breaking due to fatigue. In order to avoid the recurrence of the same type of failure and to ensure flight safety, in-situ inspection of in-service blades is required.

[0003] Since the back area of ​​the blade is a deformed curved surface, it is not visible under in-situ inspection conditions, and the width of the fatigue crack in the initial stage of initiation is less than 1 micron, which is very easy to be covered and blocked. Therefore, commonly used in-situ inspection methods such as visual inspection, endoscopic inspection, and fluorescent penetrant inspection are unable to accurately inspect aircraft engine blades.

[0004] At present, aircraft engine blades are usually inspected by endoscope observation and fluorescent penetration marking. Among them, the patent with publication number CN118169135A proposes an in-service detection device and repair method for micro cracks in aircraft engine blades, which relates to the field of blade inspection technology, including: an endoscope; a grinding head, which is rotatably connected to the front end of the endoscope through a driving motor; a fluorescent agent delivery mechanism, including a delivery pipe, a delivery pump and a material box, the delivery pipe is arranged inside the endoscope, one end of the delivery pipe extends to the front end of the endoscope, and the other end of the delivery pipe extends from the end of the endoscope and is connected to the material box, the material box stores fluorescent agent, and the delivery pump is arranged on the delivery pipe. The present invention combines the fluorescent agent delivery mechanism with the grinding head and the endoscope, and uses the fluorescent penetration marking method for grinding, so that the staff can accurately judge the crack grinding situation, ensure that the grinding is intact and there is no over-grinding; the blade is subjected to fluorescent inspection, and whether there are micro cracks on the blade surface can be checked, and in-service inspection and in-service repair can be realized at the same time.

[0005] The above patent uses an endoscope to observe the blade surface and marks small cracks with a fluorescent agent. However, this detection method can only detect and identify open cracks on the blade surface, and cannot detect fine cracks whose openings are covered and blocked. Summary of the invention

[0006] The present application provides an aircraft engine blade detection device, which improves the in-situ detection capability of in-service aircraft engine blades.

[0007] According to a first aspect of the present application, there is provided an aircraft engine blade detection device, the device comprising:

[0008] The detection rod comprises a connecting portion and a detection portion which are connected to each other, one end of the connecting portion is connected to the detection portion, a first accommodating cavity is provided inside the detection portion, an eddy current coil is arranged in the first accommodating cavity, the axial direction of the eddy current coil is arranged perpendicular to the length direction of the detection portion, the shape of the detection portion matches the curvature of the aircraft engine blade, the detection portion is used to extend into the interior of the aircraft engine, and acts on the blade through electromagnetic induction to generate an induction signal;

[0009] The detector is communicatively connected to the detection unit and is used to receive the sensing signal generated by the detection unit and determine the blade quality information of the blade according to the sensing signal.

[0010] Optionally, the device further comprises:

[0011] A control switch is installed on the connecting portion and is connected to the eddy current coil to control the eddy current coil to send an induction signal to the detector.

[0012] Optionally, there are multiple eddy current coils, and the multiple eddy current coils are arranged in parallel.

[0013] Optionally, the device further comprises:

[0014] A multiplexer, one end of the multiplexer is connected to the detector, and the other end of the multiplexer is respectively connected to each eddy current coil.

[0015] Optionally, among the multiple eddy current coils arranged in parallel, the distance between any two adjacent eddy current coils is equal, and the distance is not greater than the diameter of the eddy current coil.

[0016] Optionally, a marking line is provided on the detection rod, and the marking line is used to indicate the distance that the detection part extends into the interior of the aircraft engine.

[0017] Optionally, a gripping portion is further provided at one end of the connecting portion away from the detecting portion, and the gripping portion is provided with anti-slip stripes.

[0018] Optionally, both the detector and the detection rod are provided with data interfaces, and the detector and the detection rod are connected via a data line.

[0019] Optionally, a power supply module is provided inside the detector, and the power supply module is used to supply power to the detector and / or the detection rod.

[0020] Optionally, a storage module is also provided inside the detector, and the storage module is used to store the sensing signal and the blade status information.

[0021] The technical solution provided by the embodiments of the present application brings at least the following beneficial effects:

[0022] The embodiment of the present application provides an aeroengine blade detection device, which is provided with a detector and a detection rod, and a connection part and a detection part are provided on the detection rod. Since the shape of the detection part matches the curvature of the blade, the detection part can be sent into the interior of the aeroengine by operating the connection part, and the electromagnetic induction of the eddy current coil provided on the detection part acts on the aeroengine blade to generate an induction signal, and the induction signal is sent to the detector, so that the induction signal can be analyzed by the detector to determine the blade quality information of the blade. Based on this, by providing a detection part whose shape matches the curvature of the aeroengine blade, the eddy current coil located on the detection part can be extended into the interior of the aeroengine to detect the blade, reducing the possibility of interference between the detection part and the blade, so that the eddy current coil can be well attached to the blade, and the eddy current signal generated by the eddy current coil can act on the interior of the blade, and can also better reflect the condition of the interior of the blade, thereby obtaining more accurate blade quality information.

[0023] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification are used to explain the principles of the present application, and do not constitute an improper limitation on the present application.

[0025] Figure 1 is a schematic structural diagram of an aircraft engine blade detection device according to an exemplary embodiment;

[0026] Figure 2 The figure is a partial structural diagram of an aircraft engine blade detection device according to an exemplary embodiment.

[0027] Legend:

[0028] legend name legend name 100 Aircraft engine blade detection device 110 Detection rod 111 Connection 112 Testing Department 112a Accommodation cavity 112b Eddy current coil 113 Control switch 114 Marking line 115 Grip 120 Detector 121 Power supply module 122 Storage Module DETAILED DESCRIPTION

[0029] In order to more clearly understand the above-mentioned objectives, features and advantages of the present disclosure, the scheme of the present disclosure will be further described below. It should be noted that the embodiments of the present disclosure and the features in the embodiments can be combined with each other without conflict.

[0030] In the following description, many specific details are set forth to facilitate a full understanding of the present disclosure, but the present disclosure may also be implemented in other ways different from those described herein; it is obvious that the embodiments in the specification are only part of the embodiments of the present disclosure, rather than all of the embodiments.

[0031] As described in the background technology, since the back area of ​​the blade is a deformed curved surface, it is not visible under in-situ detection conditions, and the width of the fatigue crack in the initial stage of initiation is less than 1 micron, which is very easy to be covered and blocked. Therefore, commonly used in-situ detection methods such as visual inspection, endoscopic inspection, and fluorescent penetrant inspection are unable to accurately inspect aircraft engine blades.

[0032] Based on this, the present application provides an aircraft engine blade detection device. The aircraft engine blade detection device provided in the embodiment of the present application is first introduced below.

[0033] Embodiment 1;

[0034] Figure 1 A schematic diagram of the structure of an aircraft engine blade detection device provided by an embodiment of the present application is shown. Figure 2 FIG. 1 is a schematic diagram showing a partial structure of an aircraft engine blade detection device provided by an embodiment of the present application. Figure 1 and Figure 2 As shown, it may include the following structures:

[0035] The detection rod 110 includes a connecting portion 111 and a detection portion 112 which are connected to each other. One end of the connecting portion 111 is connected to the detection portion 112. A first accommodating cavity 112a is provided inside the detection portion 112. An eddy current coil 112b is provided inside the first accommodating cavity 112a. The axial direction of the eddy current coil 112b is perpendicular to the length direction of the detection portion 112. The shape of the detection portion 112 matches the curvature of the blade of the aircraft engine. The detection portion 112 is used to extend into the interior of the aircraft engine and act on the blade through electromagnetic induction to generate an induction signal.

[0036] The detector 120 is communicatively connected to the detection unit 112 and is used to receive the sensing signal generated by the detection unit 112 and determine the blade quality information of the blade according to the sensing signal.

[0037] Based on the above embodiment, a detector 120 and a detection rod 110 are provided, and a connecting portion 111 and a detection portion 112 are provided on the detection rod 110. Since the shape of the detection portion 112 matches the curvature of the blade, the detection portion 112 can be sent into the interior of the aircraft engine by operating the connecting portion 111, and the eddy current generated by the eddy current coil 112b provided on the detection portion 112 acts on the blade of the aircraft engine to generate an induction signal, and the induction signal is sent to the detector 120, so that the induction signal can be analyzed by the detector 120 to determine the blade quality information of the blade. Based on this, a detection part 112 having a shape matching the curvature of the aircraft engine blade is provided, so that the eddy current coil 112b located on the detection part 112 can be extended into the interior of the aircraft engine to detect the blade, thereby reducing the possibility of interference between the detection part 112 and the blade, so that the eddy current coil 112b can fit well with the blade, and the eddy current signal generated by the eddy current coil 112b can act on the interior of the blade, and can also better reflect the internal condition of the blade, thereby obtaining more accurate blade quality information.

[0038] Specifically, during the inspection process, the inspector can first stick a layer of protective film on the inspection part 112, which can be used to protect the inspection part 112 and reduce the resistance when the inspection part 112 contacts the blade. Then, holding the connecting part 111, extend one end of the inspection part 112 of the inspection rod 110 into the blade inside the aircraft engine. By rotating the connecting part 111, the eddy current coil 112b of the inspection part 112 can be directed to one side of the blade. The eddy current coil 112b acts on the blade through electromagnetic induction to generate an induction signal. The inspector can then hold the connecting part 111 and move it along the length direction of the blade, so that the eddy current coil 112b completes the inspection of a blade. In the process of the eddy current coil 112b scanning the blade, the generated induction signal is also sent to the detector 120 in real time. By analyzing the induction signal displayed by the detector 120, the blade quality information of the blade is determined, wherein the blade quality information may include information such as whether there is a crack on the blade and the length of the crack.

[0039] More specifically, the detector 120 can generate a signal curve according to the real-time sensing signal by receiving the sensing signal generated by the eddy current coil 112b when scanning the blade in real time. In order to determine the sensitivity of the detection unit 112, a comparison sample with artificial grooves can be processed in advance, and the detection unit 112 can be used to scan it, and the sensitivity of the detection unit 112 can be determined by observing whether the signal on the detector 120 is clear and discernible, which can be specifically reflected as the display amplitude is not less than 50% FSH of the full screen.

[0040] During the testing process, when the inspector has doubts about the test results and the testing system, or when the test status changes (such as replacing the inspector, the detector 120, the testing unit 112 and the protective film, etc.), the sensitivity of the testing unit 112 needs to be recalibrated.

[0041] It should be noted that the length and width of the artificial grooves processed on the comparison specimens are usually determined by technical personnel based on industry standards or negotiated with the client.

[0042] It should be noted that the protective film should be pasted flat without wrinkles, and the sensitivity of the instrument should be adjusted to be the same as the protective film pasted during the blade inspection. During the inspection, the wear of the protective film should be observed at any time, and if it is damaged, it should be replaced immediately. In one example, the protective film can include: Teflon film, polyimide film, etc.

[0043] Optionally, the eddy current coil 112b can be a differential coil, which can enhance detection sensitivity and improve signal-to-noise ratio by connecting two components with theoretically identical structures, dimensions, and sizes. In differential eddy current detection, two identical detection inductance coils form a differential structure, and the circuit design is completely symmetrical. This allows the temperature drift and time drift of the two loops to cancel each other as common-mode signals, thereby improving the stability of detection.

[0044] Since the aircraft engine blade detection device 100 needs to be transported and moved to various places to detect the aircraft engine, in order to facilitate transportation and movement, and to be suitable for detection in different environments, preferably, the detector 120 has a size no larger than 8 inches and a weight no more than 2kg; and can adapt to an operating temperature of -20°C to +55°C to meet the ambient temperature of use in different regions and seasons.

[0045] In order to more accurately detect that the detection unit 112 sends a sensing signal to the detector 120, the present application also provides another structure of the aircraft engine blade detection device 100, which further includes:

[0046] The control switch 113 is installed on the connecting portion 111 . The control switch 113 is connected to the eddy current coil 112 b and is used to control the eddy current coil 112 b to send an induction signal to the detector 120 .

[0047] Based on the above embodiment, by setting the control switch 113, the inspector can control the eddy current coil 112b to send an induction signal to the detector 120 by using the control switch 113, so that the inspector can turn on the eddy current coil 112b to send an induction signal to the detector 120 before and after each inspection of a blade, and stop the eddy current coil 112b from sending an induction signal to the detector 120, so that the induction signal received by the detector 120 is related to the induction signal of a blade, which is convenient for later quality tracing.

[0048] In order to detect the blades more quickly, the present application also provides another structure of the aircraft engine blade detection device 100:

[0049] The number of the eddy current coils 112 b is plural, and the plural eddy current coils 112 b are arranged in parallel.

[0050] Based on the above embodiment, by setting the number of eddy current coils 112b to be multiple, and the multiple eddy current coils 112b are arranged in parallel, when the detection unit 112 is in one position, the eddy current coil 112b can cover a larger area on the blade, thereby improving the detection efficiency of the detection unit 112 in detecting the blade.

[0051] Optionally, in one example, the number of eddy current coils 112b is 4 groups, and each group of eddy current coils 112b is composed of a detection coil with a diameter of 1.7mm and a magnetic core wound by 0.03mm enameled wire, which is evenly arranged perpendicular to the axial direction of the probe housing (the diameter of the detection part 112 housing is 4.0mm) at the front end of the probe, and the center spacing of adjacent detection coils is 2.0mm. It should be noted that the number of eddy current coils 112b is related to the surface area of ​​the blade. This application does not limit the number of eddy current coils 112b, and the above data is only a preferred embodiment.

[0052] In order to reduce the mutual interference between the multiple eddy current coils 112b, the present application also provides another structure of the aircraft engine blade detection device 100, which further includes:

[0053] A multiplexer, one end of the multiplexer is connected to the detector 120, and the other end of the multiplexer is connected to each eddy current coil 112b respectively.

[0054] Based on the above embodiment, due to the use of a multiplexer, one end of the multiplexer is connected to the detector 120, and the other end is connected to each eddy current coil 112b respectively, so that at any time, only one coil unit is working and the other coil units are in a non-working state, thereby avoiding electromagnetic interference between them.

[0055] Similarly, in order to improve the accuracy and reliability of detection, the present application also provides another structure of an aircraft engine blade detection device 100;

[0056] Among the multiple eddy current coils 112 b arranged in parallel, the distance between any two adjacent eddy current coils 112 b is equal and greater than the diameter of the eddy current coil 112 b.

[0057] By setting the distance between any two adjacent coils of the plurality of eddy current coils 112b to be equal, it is convenient to judge the length of the crack. The diameter of the eddy current generated by each eddy current coil 112b is twice the diameter of the eddy current coil 112b, and in order to avoid the gap between the eddy currents generated by the two eddy current coils 112b, which may lead to insufficient scanning of the blade and missed detection; therefore, the spacing between the two eddy current coils 112b cannot be greater than the diameter of the eddy current coil 112b, thereby ensuring that the eddy current coil 112b can cover and scan the blade.

[0058] Embodiment 2:

[0059] Based on Example 1, in order to make it more convenient for inspectors to inspect the blades of an aircraft engine, this application also provides another implementation of the aircraft engine blade inspection device 100.

[0060] A marking line 114 is provided on the detection rod 110 , and the marking line 114 is used to indicate the distance that the detection portion 112 extends into the interior of the aircraft engine.

[0061] Based on the above embodiment, by setting the marking line 114, when the inspector operates the inspection rod 110, once the inspector visually sees that the outer edge of the aircraft engine blade coincides with the marking line 114 on the connecting portion 111, it means that the inspection portion 112 has extended into the interior of the aircraft engine and reached the position where the internal blades need to be inspected. Therefore, the blades can be scanned by turning on the control switch 113, thereby improving the operability of the inspection portion 112 when inspecting the internal blades of the aircraft engine.

[0062] In order to facilitate the inspection personnel to use the aircraft engine blade inspection device 100, the present application also provides another structure of the aircraft engine blade inspection device 100.

[0063] A gripping portion 115 is further disposed at one end of the connecting portion 111 away from the detecting portion 112 , and the gripping portion 115 is provided with anti-slip stripes.

[0064] Based on the above embodiment, by providing a gripping portion 115 with anti-slip stripes at one end of the connecting portion 111 away from the detecting portion 112, the friction between the gripping portion 115 and the hand of the detecting person is increased, so that the detecting person can hold the detecting rod 110 more stably and reliably.

[0065] Preferably, the shape of the grip portion 115 is ergonomic.

[0066] In the above-mentioned embodiment 2, each process of the above-mentioned embodiment 1 can be implemented and the same technical effect can be achieved. To avoid repetition, it will not be described again here.

[0067] Embodiment 3:

[0068] Based on Example 1, in order to improve the confidentiality of the sensing signal, this application also provides another implementation method of the aircraft engine blade detection device 100.

[0069] Data interfaces are provided on the detector 120 and the detection rod 110 , and the detector 120 and the detection rod 110 are connected via a data line.

[0070] Based on the above embodiment, by opening a data interface on the detector 120 and the detection rod 110, and connecting the detector 120 and the detection rod 110 with a data line, the possibility of the sensing signal being intercepted is reduced during the transmission of the sensing signal through the data line, which is beneficial to the confidentiality of the signal transmission.

[0071] In another embodiment, the detector 120 and the detection rod 110 can also be connected via wireless communication. By using wireless communication connection, the detector 120 and the detection rod 110 can be used more flexibly and are not easily restricted by the length of the wiring harness.

[0072] In order to make the aircraft engine blade detection device 100 more convenient to use, the present application also provides another implementation method of the aircraft engine blade detection device 100.

[0073] A power supply module 121 is disposed inside the detector 120 , and the power supply module 121 is used to supply power to the detector 120 and / or the detection rod 110 .

[0074] Based on the above embodiment, by arranging a power supply module 121 on the detector 120, and using the power supply module 121 to supply power to the detector 120 and / or the detection rod 110, the detector 120 and the detection rod 110 can work without an external power supply, so that the aircraft engine blade detection device 100 is more flexible to use; and after the power supply module 121 has no power, the power supply module 121 can continue to be replaced to supply power to the detector 120 and / or the detection rod 110.

[0075] Optionally, the detector 120 and the detection rod 110 may each be provided with a power supply module 121 for supplying power to themselves.

[0076] Optionally, the power supply module 121 can be used continuously for 8 hours when fully charged, so as to solve the problem of no external power supply when going out for detection.

[0077] In order to verify the blade status information detected by the aircraft engine blade detection device 100, the present application also provides another implementation method of the aircraft engine blade detection device 100.

[0078] A storage module 122 is also provided inside the detector 120 , and the storage module 122 is used to store the sensing signal and the blade status information.

[0079] Based on the above embodiment, by setting a storage module 122 inside the detector 120, the storage module 122 can store the sensing signal and blade quality information when the blade is detected by the aircraft engine blade detection device 100, so that in the subsequent detection process, the sensing signal and blade quality information of the blade stored in the storage module 122 can be exported to further analyze and verify the sensing signal and blade quality information.

[0080] In the above-mentioned embodiment 3, each process of the above-mentioned embodiment 1 and / or the above-mentioned embodiment 2 can be implemented, and the same technical effect can be achieved. To avoid repetition, it will not be described here.

[0081] The above is only a specific implementation of the present application. Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the systems, modules and units described above can refer to the corresponding processes in the aforementioned method embodiments, and will not be repeated here. It should be understood that the protection scope of the present application is not limited to this. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed in this application, and these modifications or replacements should be included in the protection scope of this application.

Claims

1. An aircraft engine blade detection device, characterized in that: The device comprises: A detection rod, the detection rod comprising a connecting portion and a detection portion connected to each other, one end of the connecting portion being connected to the detection portion, a first accommodating cavity being provided inside the detection portion, an eddy current coil being provided inside the first accommodating cavity, the axial direction of the eddy current coil being provided perpendicularly to the length direction of the detection portion, the shape of the detection portion being matched with the curvature of the aeroengine blade, the detection portion being used to extend into the aeroengine and to act on the blade through electromagnetic induction to generate an induction signal; A detector is communicatively connected to the detection unit, and is used to receive the sensing signal generated by the detection unit, and determine the blade quality information of the blade according to the sensing signal.

2. The device according to claim 1, characterized in that The device also includes: A control switch is installed on the connecting portion, and the control switch is connected to the eddy current coil, and is used to control the eddy current coil to send the induction signal to the detector.

3. The device according to claim 2, characterized in that The number of the eddy current coils is multiple, and the multiple eddy current coils are arranged in parallel.

4. The device according to claim 3, characterized in that The device also includes: A multiplexer, one end of the multiplexer is connected to the detector, and the other end of the multiplexer is respectively connected to each of the eddy current coils.

5. The device according to claim 3, characterized in that Among the multiple eddy current coils arranged in parallel, the distance between any two adjacent eddy current coils is equal, and the distance is not greater than the diameter of the eddy current coil.

6. The device according to claim 1, characterized in that The detection rod is provided with a marking line, and the marking line is used to indicate the distance that the detection part extends into the interior of the aircraft engine.

7. The device according to claim 1, characterized in that A gripping portion is also provided at one end of the connecting portion away from the detecting portion, and the gripping portion is provided with anti-slip stripes.

8. The device according to any one of claims 1 to 7, characterized in that The detector and the detection rod are both provided with data interfaces, and the detector and the detection rod are connected via a data line.

9. The device according to claim 8, characterized in that A power supply module is arranged inside the detector, and the power supply module is used to supply power to the detector and / or the detection rod.

10. The device according to claim 8, characterized in that A storage module is also provided inside the detector, and the storage module is used to store the sensing signal and the blade quality information of the blade.

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