Method and system for measuring and detecting chord angle of turbine blade section of aircraft engine

Abstract

The present invention discloses a method and system for measuring and detecting the cross-section chord angle of an aircraft engine turbine blade, and belongs to the technical field of measuring and detecting the cross-section chord angle of an aircraft engine turbine blade. The method comprises: fixing the turbine blade; abutting the straight stop edge provided on the rotating scale plate against the leading edge and the trailing edge of the blade of the metrological detection section of the turbine blade, and using the straight stop edge as a chord passing through the current metrological detection section and tangent to the leading edge and the trailing edge of the blade; detecting the magnetic field strength and magnetic field direction generated by the magnetic element at the current rotation angle position by a magnetic field detection element, and the magnetic field detection element outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction; obtaining the chord angle of the current metrological detection section of the turbine blade according to the electrical signal output by the magnetic field detection element. The metrological detection method in the present invention facilitates the detection of the cross-section chord angle of the turbine blade during the processing process and reduces the detection cost.

Description

Technical Field

[0001] The present invention relates to the technical field of measuring and detecting the cross-section chord angle of an aero-engine turbine blade, and in particular to a method and system for measuring and detecting the cross-section chord angle of an aero-engine turbine blade. Background Art

[0002] Turbine blades are important parts that play an energy conversion role in aircraft engines. With the development of the aviation industry, the performance requirements for engines are constantly increasing. In addition, the blade body profile of the turbine blade is a spatial curved surface formed by stacking basic element blade profiles according to a certain stacking rule. The manufacturing quality of the blade body directly affects the performance of the entire engine. Among them, the multiple cross-sectional chord angles on the turbine blade are one of the important factors affecting the performance of the engine. The qualification of the multiple cross-sectional chord angles on the turbine blade is an important indicator of whether the turbine blade is qualified. Therefore, detecting the multiple cross-sectional chord angles on the turbine blade is one of the important qualification inspection items for the turbine blade.

[0003] At present, in order to detect the cross-sectional chord angle of turbine blades, the existing detection method usually uses a three-coordinate measuring machine for detection. The three-coordinate measuring machine is a high-precision precision measurement and testing equipment that integrates light, electricity, and computers. However, the three-coordinate measuring machine is only suitable for batch measurement of finished turbine blade parts, and is not suitable for detecting turbine blade parts during the processing process; further, the three-coordinate measuring machine is expensive, difficult to maintain, and has strict requirements on the temperature and humidity of the detection site. For large-scale turbine blade production, each turbine blade must be sent to the three-coordinate for cross-sectional chord angle detection, which is not only time-consuming and labor-intensive, but also inefficient. Therefore, there is an urgent need for a metrological detection method that is convenient for measuring the cross-sectional chord angle of turbine blades during the processing process and reduces the detection cost. Summary of the invention

[0004] The object of the present invention is to overcome at least one of the shortcomings of the above-mentioned prior art and to provide a method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade, which is convenient for measuring and detecting the cross-sectional chord angle of the turbine blade during the processing process and reduces the detection cost; in addition, a system for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade is also provided.

[0005] The technical solution of the present invention to solve the above technical problems is as follows:

[0006] According to one aspect of the present application, a method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade is provided, the method comprising:

[0007] Fix the turbine blades;

[0008] The straight stop edge provided on the rotating scale plate is stopped on the leading edge and the trailing edge of the blade of the metering detection section of the turbine blade, and the straight stop edge is used as a chord passing through the current metering detection section and tangent to the leading edge and the trailing edge of the blade, wherein the straight stop edge is provided on the side of the rotating scale plate facing the leading edge and the trailing edge of the blade, and the straight stop edge is used to stop with the leading edge and the trailing edge of the blade, the rotating scale plate is rotatably mounted on the support plate through a rotating support shaft, the rotating support shaft is fixedly connected to one side of the rotating scale plate, the rotating support shaft is rotatably mounted on the support plate, and a magnetic element is mounted on the rotating support shaft, and the magnetic element rotates synchronously around the central axis of the rotating support shaft as the rotating scale plate rotates;

[0009] detecting the magnetic field strength and magnetic field direction generated by the magnetic element at the current rotation angle position by means of a magnetic field detection element, wherein the magnetic field detection element outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction;

[0010] According to the electrical signal output by the magnetic field detection element, the chord angle of the current metering detection section of the turbine blade is obtained, wherein different electrical signals are used to characterize different chord angles, respectively. When the rotational angle position of the magnetic element changes, the magnetic field strength and magnetic field direction sensed by the magnetic field detection element change with the change of the rotational angle position of the magnetic element, and the electrical signal output by the magnetic field detection element changes with the change of the magnetic field strength and magnetic field direction sensed by the magnetic field detection element.

[0011] The beneficial effects of the present invention are as follows: in the method for measuring and detecting the chord angle of the section of the turbine blade of an aircraft engine in the present embodiment, the straight stop edge provided on the rotating scale plate is stopped on the leading edge and the trailing edge of the blade of the measuring and detecting section of the turbine blade, which is conducive to using the straight stop edge as a chord passing through the current measuring and detecting section and tangent to the leading edge and the trailing edge of the blade, thereby facilitating the measurement of the angle of the straight stop edge to achieve the measurement of the chord angle of the current measuring and detecting section, and facilitating the acquisition of the chord angle of the measuring and detecting section; further, the rotating scale plate and the magnetic element in the present embodiment can rotate synchronously, and the magnetic field detection is used to detect the chord angle of the measuring and detecting section. The element detects the magnetic field strength and magnetic field direction generated by the magnetic element located at the current rotation angle position. The magnetic field detection element outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction, and obtains the chord angle of the current metrological detection section of the turbine blade according to the electrical signal output by the magnetic field detection element, thereby realizing the characterization of the chord angle of the metrological detection section by the electrical signal, which is beneficial to the measurement and acquisition of the chord angle of the current metrological detection section of the turbine blade, facilitates the metrological detection of the cross-sectional chord angle of the turbine blade during the processing process and reduces the detection cost, and is not easily affected by the temperature and humidity in the detection environment.

[0012] According to one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of a turbine blade of an aircraft engine further includes:

[0013] The straight stop edge provided on the rotating scale plate is sequentially stopped against the blade leading edge and the blade trailing edge of the next metering detection section of the turbine blade, and the chord angle of the next metering detection section of the turbine blade is obtained sequentially, wherein a plurality of metering detection sections are selected at intervals on the turbine blade along the extension direction of the blade body.

[0014] In this embodiment, the straight stop edges provided on the rotating scale plate are sequentially stopped on the leading edge and trailing edge of the next metrological detection section of the turbine blade, and the chord angle of the next metrological detection section of the turbine blade is obtained in turn, which is beneficial to detecting multiple metrological detection sections on the entire turbine blade and obtaining the chord angles of multiple metrological detection sections on the entire turbine blade.

[0015] According to an embodiment of the present application, obtaining the chord angle of the current measurement detection section of the turbine blade according to the electrical signal output by the magnetic field detection element includes:

[0016] The electrical signal output by the magnetic field detection element is input into a signal processing unit, and the electrical signal input by the magnetic field detection element is processed by the signal processing unit to obtain the chord angle of the current measurement detection section of the turbine blade.

[0017] In this embodiment, the electrical signal output by the magnetic field detection element is input into the signal processing unit. The signal processing unit processes the electrical signal input by the magnetic field detection element, which is beneficial for converting the chord angle signal represented by the electrical signal into angle data that is easy to identify, so as to facilitate identification and judgment by detection personnel.

[0018] According to one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of a turbine blade of an aircraft engine further includes:

[0019] Compare the obtained chord angle of the current metering detection section of the turbine blade with the preset qualified chord angle threshold corresponding to the current metering detection section to obtain a comparison result of the chord angle of the current metering detection section, wherein one metering detection section corresponds to one preset qualified chord angle threshold, different metering detection sections correspond to different preset qualified chord angle thresholds, and the preset qualified chord angle thresholds corresponding to different metering detection sections are pre-set according to the qualified ranges of the chord angles of different metering detection sections;

[0020] According to the obtained comparison result of the chord angle of the current measurement detection section, it is determined whether the chord angle of the current measurement detection section is qualified, and a determination result of whether the chord angle of the current measurement detection section is qualified is obtained.

[0021] In this embodiment, the chord angle of the current metering detection section of the turbine blade is obtained and compared with the preset qualified chord angle threshold corresponding to the current metering detection section, so as to facilitate the determination of whether the chord angle of the current metering detection section is qualified, and facilitate the automatic determination of whether the chord angle of the current metering detection section is qualified.

[0022] According to one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of a turbine blade of an aircraft engine further includes:

[0023] When the result of determining whether the chord angle of the current metering detection section is qualified is qualified, the straight stop edge provided on the rotating scale plate is stopped against the blade leading edge and the blade trailing edge of the next metering detection section of the turbine blade to obtain the chord angle of the next metering detection section of the turbine blade, wherein a plurality of metering detection sections are selected at intervals along the extension direction of the blade body of the turbine blade, and the plurality of metering detection sections are pre-selected metering detection sections;

[0024] According to the obtained comparison result of the chord angle of the next measurement detection section, whether the chord angle of the next measurement detection section is qualified is determined, and a determination result of whether the chord angle of the next measurement detection section is qualified is obtained;

[0025] Continue to detect and determine the chord angle of the next metrology detection section of the turbine blade until all the metrology detection sections on the turbine blade have completed detection and determination, wherein, when the result of determination as to whether the chord angle of any one of the metrology detection sections is qualified is unqualified, stop detection and warn that the turbine blade is an unqualified product and indicate the unqualified metrology detection section; when all the metrology detection sections on the turbine blade have completed detection and the comparison results of the chord angles of all the metrology detection sections are qualified, stop detection and provide feedback that the turbine blade is a qualified product.

[0026] In this embodiment, the chord angles of the metrological inspection sections are detected and determined in sequence whether they are qualified, and when the determination result of whether the chord angle of any metrological inspection section is qualified is unqualified, the detection is stopped and a warning is given that the turbine blade is an unqualified product and an unqualified metrological inspection section is indicated, which is beneficial for inspectors to discover unqualified metrological inspection sections and improve inspection efficiency, and is also beneficial for realizing automatic detection and determination of whether the chord angles of multiple metrological inspection sections are qualified.

[0027] According to one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of a turbine blade of an aircraft engine further includes:

[0028] The support plate is driven to move linearly along the extension direction of the blade body of the turbine blade by a linear displacement driving device, and the position of the support plate is adjusted along the extension direction of the blade body of the turbine blade, so as to adjust the position of the linear stop edge along the extension direction of the blade body of the turbine blade, so as to sequentially align the linear stop edge with the plurality of the metrological detection sections to be detected;

[0029] The support plate is driven by a stop drive device to move linearly relative to the turbine blade in a direction perpendicular to the turbine blade. When the straight stop edge needs to be abutted against the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, the support plate is driven by the stop drive device to move linearly close to the turbine blade so that the straight stop edge abuts against the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade. When the straight stop edge needs to be released from the abutment with the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, the support plate is driven by the stop drive device to move linearly away from the turbine blade.

[0030] In the present embodiment, the support plate is driven to move linearly along the extension direction of the blade body of the turbine blade by a linear displacement driving device, which is beneficial to improving the reliability and alignment accuracy of aligning the linear stop edge with multiple metrological inspection sections to be inspected; further, in the present embodiment, the support plate is driven to move linearly relative to the turbine blade in a direction perpendicular to the turbine blade by a stop driving device, which is beneficial to achieving the stop and release of the linear stop edge with the leading edge and trailing edge of the metrological inspection section of the turbine blade.

[0031] According to one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of a turbine blade of an aircraft engine further includes:

[0032] The stop driving device is installed on the linear displacement driving device, and the linear displacement driving device drives the stop driving device to move linearly along the extension direction of the blade body of the turbine blade, so as to drive the support plate to move linearly along the extension direction of the blade body of the turbine blade;

[0033] Controlling the linear displacement driving device to sequentially adjust the position of the linear stop edge along the extension direction of the blade body of the turbine blade based on a first preset displacement control program by a control unit, so that the linear stop edge is aligned with a plurality of the metrology detection sections to be detected, wherein the first preset displacement control program is pre-programmed according to the positions of the plurality of the metrology detection sections of the turbine blade;

[0034] After the straight stop edge is aligned with a metering detection section to be detected, the control unit controls the stop drive device to drive the support plate to move linearly relative to the turbine blade in a direction perpendicular to the turbine blade based on a second preset displacement control program, so that the straight stop edge stops on the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, wherein the second preset displacement control program is pre-programmed according to the distances from the midpoints of the chords of multiple metering detection sections to the central axis of the rotating support shaft in a direction perpendicular to the turbine blade.

[0035] In this embodiment, the stop drive device is installed on the linear displacement drive device, which is convenient for driving the stop drive device to move linearly along the extension direction of the blade body of the turbine blade; further, the linear displacement drive device is controlled by the control unit based on the first preset displacement control program, which is conducive to realizing the automation of aligning the linear stop edge with multiple metrological detection sections to be inspected, and further improving the reliability and alignment accuracy of aligning the linear stop edge with the multiple metrological detection sections to be inspected; further, the stop drive device is controlled by the control unit based on the second preset displacement control program, which is conducive to automatically driving the linear stop edge to stop with the blade leading edge and blade trailing edge of the metrological detection section of the turbine blade in turn, thereby realizing the automation of detecting multiple metrological detection sections.

[0036] According to one embodiment of the present application, before fixing the turbine blade, the method includes:

[0037] Fixing a standard turbine blade, wherein the standard turbine blade and the turbine blade are products of the same specification, a plurality of metrological detection sections on the standard turbine blade correspond one to one with a plurality of the metrological detection sections on the turbine blade, a blade body structural parameter of the standard turbine blade meets product standard indicators, a fixing posture of the standard turbine blade is consistent with a fixing posture of the turbine blade, and the standard turbine blade and the turbine blade are metrologically detected using the same metrological detection equipment;

[0038] The straight stop edge provided on the rotating scale plate is sequentially stopped against the leading edge and trailing edge of the blade of the plurality of the metrological detection sections of the standard turbine blade, and the magnetic field strength and magnetic field direction generated by the magnetic element at different rotation angles are sequentially detected by the magnetic field detection element, and the magnetic field detection element sequentially outputs electrical signals based on the sensed magnetic field strength and magnetic field direction;

[0039] According to the electrical signals sequentially output by the magnetic field detection elements, standard metrological chord angles of a plurality of metrological detection sections of the standard turbine blade are obtained;

[0040] After obtaining the chord angle of the current measurement detection section of the turbine blade, the aeroengine turbine blade section chord angle measurement detection method further includes:

[0041] The chord angle of the current metrology detection section of the turbine blade is compared with the standard metrology chord angle of the metrology detection section with the same position as the standard turbine blade, and the chord angle errors are obtained in turn. According to the obtained chord angle errors, it is determined whether the chord angle of the current metrology detection section is qualified.

[0042] In this embodiment, a metrological inspection is performed on a standard turbine blade to obtain standard metrological chord angles of multiple metrological inspection sections of the standard turbine blade. In addition, the chord angle of the current metrological inspection section of the turbine blade is compared with the standard metrological chord angle of the metrological inspection section at the same position of the standard turbine blade to obtain a chord angle error, and based on the obtained chord angle error, it is determined in turn whether the chord angle of the current metrological inspection section is qualified. Since the same metrological inspection equipment is used for the metrological inspection, and the standard turbine blade whose blade body structural parameters meet the product standard indicators is used as the metrological inspection comparison object, it is beneficial to offset the influence of the error caused by the accuracy of the metrological inspection equipment itself, and it is beneficial to improve the accuracy of the chord angle measurement of the metrological inspection section of the turbine blade, and also improve the accuracy of determining whether the chord angle of the current metrological inspection section of the turbine blade is qualified.

[0043] According to another aspect of the present application, a system for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade is provided, which is used to implement the above-mentioned method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade, comprising:

[0044] Pedestal;

[0045] A blade fixing seat, mounted on the base, and used to fix the turbine blade;

[0046] A linear displacement driving device is installed on one side of the blade fixing seat;

[0047] A stop driving device is installed on the linear displacement driving device and is located on one side of the blade fixing seat, and the stop driving device can move linearly along the extension direction of the blade body of the turbine blade installed on the blade fixing seat under the drive of the linear displacement driving device;

[0048] The support plate is mounted on the stop driving device, and the support plate can move linearly relative to the turbine blade in a direction perpendicular to the turbine blade mounted on the blade fixing seat under the drive of the stop driving device;

[0049] The rotating ruler plate is rotatably mounted on the support plate via the rotating support shaft, and the rotating ruler plate is provided with the linear stop edge on one side facing the blade leading edge and the blade trailing edge of the turbine blade mounted on the blade fixing seat, and the linear stop edge is used to stop with the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade mounted on the blade fixing seat, and the linear stop edge serves as a chord passing through the current metering detection section and tangent to the blade leading edge and the blade trailing edge;

[0050] The magnetic element is mounted on the rotating support shaft, and the magnetic element rotates synchronously around the central axis of the rotating support shaft as the rotating ruler plate rotates;

[0051] The magnetic field detection element is mounted on the support plate and located on one side of the magnetic element. The magnetic field detection element is used to detect the magnetic field strength and magnetic field direction generated by the magnetic element located at the current rotation angle position, and the magnetic field detection element can output an electrical signal based on the sensed magnetic field strength and magnetic field direction.

[0052] The straight stop edge provided on the rotating scale plate in the present embodiment is used to stop against the leading edge and trailing edge of the blade of the metering detection section of the turbine blade, which is conducive to stopping the straight stop edge on the leading edge and trailing edge of the blade of the metering detection section of the turbine blade, and using the straight stop edge as a chord passing through the current metering detection section and tangent to the leading edge and trailing edge of the blade, thereby facilitating the measurement of the angle of the straight stop edge to achieve the measurement of the chord angle of the current metering detection section, and facilitating the acquisition of the chord angle of the metering detection section; further, the rotating scale plate and the magnetic element in the present embodiment can rotate synchronously, and the magnetic field detection is detected by The element detects the magnetic field strength and direction generated by the magnetic element at the current rotation angle position. The magnetic field detection element outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction, and obtains the chord angle of the current metrological detection section of the turbine blade according to the electrical signal output by the magnetic field detection element, so as to characterize the chord angle of the metrological detection section by the electrical signal, which is conducive to the measurement and acquisition of the chord angle of the current metrological detection section of the turbine blade, facilitates the metrological detection of the cross-sectional chord angle of the turbine blade during the processing process, reduces the detection cost, and is not easily affected by the temperature and humidity in the detection environment. Furthermore, by providing a linear displacement drive device and a stop drive device, it is convenient to adjust the position of the linear stop edge and drive the linear stop edge to stop with the leading edge and trailing edge of the blade of the metrological detection section.

[0053] According to one embodiment of the present application, the turbine blade cross-section chord angle measurement detection system further includes:

[0054] An elastic force-applying device is installed on the stop drive device and is located on one side of the blade fixing seat. The support plate is installed on the elastic force-applying device. The elastic force-applying device is used to apply an elastic extrusion force to the rotating scale plate rotatably installed on the support plate, so that the straight stop edge provided on the rotating scale plate stops on the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade.

[0055] The elastic force-applying device in this embodiment can apply an elastic squeezing force to the rotating scale plate rotatably mounted on the support plate, thereby facilitating that the straight stop edge provided on the rotating scale plate abuts against the blade leading edge and blade trailing edge of the metering detection section of the turbine blade, and the elastic force-applying device can apply a pre-tightening force to the straight stop edge, which is facilitating that the straight stop edge tightly abuts against the blade leading edge and blade trailing edge of the metering detection section, and is facilitating avoiding excessive squeezing of the straight stop edge and the blade leading edge and blade trailing edge of the metering detection section.

[0056] According to one embodiment of the present application, the elastic force applying device includes:

[0057] An installation support seat is vertically installed on the stop driving device;

[0058] A plurality of guide rods are provided, wherein the plurality of guide rods are horizontally connected to the mounting support seat and extend linearly toward the blade fixing seat;

[0059] A support movable seat, movably mounted between the plurality of guide rods, the support movable seat is provided with a plurality of guide through holes corresponding to the plurality of guide rods, the guide rods are inserted into the guide through holes corresponding to the plurality of guide rods and pass through the guide through holes, and the support plate is vertically connected to the side of the support movable seat away from the mounting support seat;

[0060] A spring is installed between the supporting movable seat and the mounting supporting seat, one end of the spring is connected to the mounting supporting seat, and the other end of the spring is connected to the supporting movable seat.

[0061] The multiple guide rods in the present embodiment can guide the supporting movable seat, which is conducive to the linear movement of the supporting movable seat along the extension direction of the guide rods, and then conducive to driving the support plate installed on the supporting movable seat to move directly, which is conducive to improving the alignment of the linear stop edge installed on the support plate with the metering detection section of the turbine blade; further, the spring is installed between the supporting movable seat and the mounting support seat, which is conducive to the spring being compressed to form an elastic force and act on the linear stop edge installed on the support plate, so that the linear stop edge is tightly stopped on the leading edge and trailing edge of the blade of the metering detection section, and when the extrusion pressure between the linear stop edge and the leading edge and trailing edge of the blade of the metering detection section is large, the spring is further elastically compressed to avoid excessive extrusion of the linear stop edge and the leading edge and trailing edge of the blade of the metering detection section.

[0062] According to one embodiment of the present application, the linear displacement driving device includes a first screw mechanism, and the first screw mechanism is horizontally mounted on the base;

[0063] The stop drive device includes a second screw mechanism, which is horizontally mounted on a first drive block provided on the first screw mechanism and is vertically arranged relative to the first screw mechanism, and the second screw mechanism can move linearly along the extension direction of the blade body of the turbine blade installed on the blade fixing seat under the drive of the first screw mechanism, and the second screw mechanism and the first screw mechanism together constitute a cross slide mechanism;

[0064] The support plate is mounted on a second driving block on the second screw mechanism, and the support plate can move linearly relative to the turbine blade in a direction perpendicular to the turbine blade mounted on the blade fixing seat under the drive of the second screw mechanism.

[0065] The second screw mechanism and the first screw mechanism in this embodiment together constitute a cross slide mechanism, which is conducive to the first screw mechanism driving the second screw mechanism to move linearly along the extension direction of the blade body of the turbine blade installed on the blade fixing seat, so that the straight stop edges installed on the support plate are respectively aligned with the metering and detection sections to be detected. It is also conducive to the second screw mechanism driving the support plate to move linearly, thereby facilitating the straight stop edges to accurately stop on the leading edge and trailing edge of the blade of the metering and detection section.

[0066] According to one embodiment of the present application, the turbine blade cross-section chord angle measurement detection system further includes:

[0067] a signal processing unit, the magnetic field detection element being electrically connected to the signal processing unit, the signal processing unit being used to perform signal processing on the electrical signal output by the magnetic field detection element to obtain a chord angle of the current measurement detection section of the turbine blade;

[0068] A display unit, electrically connected to the signal processing unit, and configured to display the obtained chord angle of the current measurement detection section of the turbine blade;

[0069] The control unit, the magnetic field detection element, the linear displacement drive device, the stop drive device, the signal processing unit and the display unit are electrically connected to the control unit respectively.

[0070] In this embodiment, the magnetic field detection element is electrically connected to the signal processing unit, so that the signal processing unit can process the electrical signal output by the magnetic field detection element to obtain the chord angle of the current metrological detection section of the turbine blade; further, the display unit is electrically connected to the signal processing unit, so that the obtained chord angle of the metrological detection section of the turbine blade can be displayed for easy viewing by the inspectors; further, the magnetic field detection element, the linear displacement drive device, the stop drive device, the signal processing unit and the display unit are electrically connected to the control unit respectively, which is conducive to realizing the automation of metrological detection of the chord angles of multiple metrological detection sections of the turbine blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0071] In order to more clearly illustrate the technical solutions in the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0072] Figure 1 This is a flow chart of a method for measuring and detecting the cross-section chord angle of an aircraft engine turbine blade in an embodiment of the present application;

[0073] Figure 2 It is a schematic diagram of the structure of the aircraft engine turbine blade cross-section chord angle measurement and detection system in the embodiment of the present application;

[0074] Figure 3 for Figure 2 Front view after straightening;

[0075] Figure 4 for Figure 3 A top view of

[0076] Figure 5 for Figure 3 Left view of;

[0077] Figure 6 for Figure 3 Right view of;

[0078] Figure 7 This is a structural schematic diagram of a rotating ruler plate rotatably mounted on a support plate in an embodiment of the present application;

[0079] Figure 8 A schematic diagram of a chord line of a measurement detection section obtained by truncating along the width direction of a turbine blade body in an embodiment of the present application, being tangent to a leading edge and a trailing edge of a blade;

[0080] Fig. 9 Schematic diagram of the structure of the rotating ruler in the embodiment of the present application.

[0081] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0082] 1. Base, 2. Blade fixing seat, 3. Turbine blade, 4. First screw mechanism, 5. Second screw mechanism, 6. Elastic force device, 7. Support plate, 8. Rotating ruler, 9. Magnetic element, 10. Support convex block 1, 11. Support convex block 2, 12. Support convex block 3, 13. Mounting support frame, 20. Mounting convex block, 21. Tenon positioning block, 22. Blade crown positioning support block, 23. Blade body positioning stop block, 2 4. Movable avoidance opening, 25. Fixing bolt 1, 26. Fixing nut 1, 27. Locking stop swing arm, 28. Thrust control knob, 29. Tension spring, 30. Tenon, 31. Blade crown, 32. Blade body, 33. Chord, 40. Horizontal support plate 1, 41. Vertical mounting plate 1, 42. Rotating support seat 1, 43. Rotating support seat 2, 44. Driving motor 1, 45. Lead screw 1, 46. First driving block, 4 7. Sliding guide rail 1, 48. Slider 1, 50. Horizontal support plate 2, 51. Vertical mounting plate 2, 52. Rotating support seat 3, 53. Rotating support seat 4, 54. Driving motor 2, 55. Lead screw 2, 56. Second driving block, 57. Sliding guide rail 2, 58. Slider 2, 59. Horizontal connecting plate, 60. Mounting support seat, 61. Guide rod, 62. Support movable seat, 63. Spring, 70. Magnetic field detection element, 80. Straight stop edge, 81. Connecting protrusion, 211. Tenon lateral positioning part, 321. Blade leading edge, 322. Blade trailing edge, 441. Driving shaft 1, 442. Connector 1, 541. Driving shaft 2, 542. Connector 2, 591. Vertical connecting plate, 701. Cable interface, 811. Rotating support shaft, 812. Magnet mounting section, 813. Locking screw, 8121. Threaded hole 1. DETAILED DESCRIPTION

[0083] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0084] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0085] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the protection scope of the present invention is not limited to the specific embodiments disclosed below.

[0086] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0087] According to an embodiment of the present application, an embodiment of a method for measuring the chord angle of a cross-section of a turbine blade of an aircraft engine is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0088] Figure 1 is a flow chart of a method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade according to an embodiment of the present application. The method adopts Figures 2 to 9 The chord angle measurement and detection system of the aircraft engine turbine blade section shown in the figure is used for measurement and detection, such as Figure 1 As shown, the method comprises the following steps:

[0089] Step S102, fixing the turbine blade 3;

[0090] Step S104, the straight stop edge 80 provided on the rotating scale plate 8 is stopped on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, and the straight stop edge 80 is used as the chord 33 passing through the current metering detection section and tangent to the blade leading edge 321 and the blade trailing edge 322, wherein the rotating scale plate 8 is provided with a straight stop edge 80 on the side facing the blade leading edge 321 and the blade trailing edge 322, and the straight stop edge 80 is used to stop with the blade leading edge 321 and the blade trailing edge 322, the rotating scale plate 8 is rotatably mounted on the support plate 7 through the rotating support shaft 811, the rotating support shaft 811 is fixedly connected to one side of the rotating scale plate 8, the rotating support shaft 811 is rotatably mounted on the support plate 7, and a magnetic element 9 is mounted on the rotating support shaft 811, and the magnetic element 9 rotates synchronously around the central axis of the rotating support shaft 811 as the rotating scale plate 8 rotates;

[0091] Step S106, detecting the magnetic field strength and magnetic field direction generated by the magnetic element 9 at the current rotation angle position through the magnetic field detection element 70, and the magnetic field detection element 70 outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction;

[0092] Step S108, obtaining the chord angle of the current metering detection section of the turbine blade 3 according to the electrical signal output by the magnetic field detection element 70, wherein different electrical signals are used to characterize different chord angles, respectively. When the rotation angle position of the magnetic element 9 changes, the magnetic field strength and magnetic field direction sensed by the magnetic field detection element 70 change with the change of the rotation angle position of the magnetic element 9, and the electrical signal output by the magnetic field detection element 70 changes with the change of the magnetic field strength and magnetic field direction sensed by the magnetic field detection element 70.

[0093] In the present embodiment, in the method for measuring and detecting the chord angle of the section of the turbine blade of an aircraft engine, the straight stop edge 80 provided on the rotating ruler plate 8 is stopped on the blade leading edge 321 and the blade trailing edge 322 of the measuring and detecting section of the turbine blade 3, which is conducive to using the straight stop edge 80 as the chord 33 passing through the current measuring and detecting section and tangent to the blade leading edge 321 and the blade trailing edge 322, and then facilitating the measurement of the angle of the straight stop edge 80 to achieve the measurement of the chord angle of the current measuring and detecting section, so as to facilitate the acquisition of the chord angle of the measuring and detecting section; further, the rotating ruler plate 8 and the magnetic element 9 in the present embodiment can rotate synchronously, through the magnetic field The detection element 70 detects the magnetic field strength and magnetic field direction generated by the magnetic element 9 located at the current rotation angle position. The magnetic field detection element 70 outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction, and obtains the chord angle of the current metering detection section of the turbine blade 3 according to the electrical signal output by the magnetic field detection element 70, thereby realizing the characterization of the chord angle of the metering detection section by the electrical signal, which is beneficial to the measurement and acquisition of the chord angle of the current metering detection section of the turbine blade 3, facilitates the metering detection of the cross-sectional chord angle of the turbine blade 3 during the processing process and reduces the detection cost, and is not easily affected by the temperature and humidity in the detection environment.

[0094] In step S102 of this embodiment, Figure 2 As shown, in this embodiment, the turbine blade 3 is specifically fixed on the blade fixing seat 2; in addition, there can be multiple ways to fix the turbine blade 3 on the blade fixing seat 2, which is convenient for realizing that the straight stop edge 80 provided on the rotating scale plate 8 is stopped on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, and the metering detection of multiple metering detection sections of the turbine blade 3 is realized in turn, and the chord angles of multiple metering detection sections of the turbine blade 3 are obtained.

[0095] In step S104 of this embodiment, Figures 2 to 6 As shown, the straight stop edge 80 provided on the rotating ruler plate 8 is stopped on the blade leading edge 321 and the blade trailing edge 322 of the measurement detection section of the turbine blade 3; further, as Figure 8 and Fig. 9 As shown, the straight stop edge 80 is taken as the chord line 33 passing through the current measurement detection section and tangent to the blade leading edge 321 and the blade trailing edge 322; it should be noted that in this embodiment, Figure 8 The metering detection section shown and the chord line 33 of the current metering detection section are one of the metering detection sections of the turbine blade 3, and are not Figures 2 to 6 The rotating scale plate 8 shown abuts the current metering detection cross section of the turbine blade 3 .

[0096] It should be noted that the "current metrology detection section" in this embodiment refers to the metrology detection section where the next rotating scale plate 8 stops. When the rotating scale plate 8 stops at the next metrology detection section, the next metrology detection section where the rotating scale plate 8 stops will be used as the current metrology detection section; when it is necessary to detect a certain metrology detection section of the turbine blade 3 during the processing process or other circumstances, the rotating scale plate 8 can be directly stopped at the metrology detection section that needs to be detected, and this metrology detection section will be used as the current metrology detection section.

[0097] In the present embodiment, the magnetic field detection element 70 in the present embodiment is specifically a Hall sensor, the Hall sensor is electrically connected to the signal processing unit through a cable, and the Hall sensor is also electrically connected through a cable control unit; it should be noted that in step S106 of the present embodiment, the Hall sensor detects the magnetic field strength and magnetic field direction generated by the magnetic element 9 based on the Hall effect, and the principle of the Hall sensor detecting the magnetic field strength and magnetic field direction generated by the element and the specific structure of the Hall sensor can refer to the existing technology in the field, and will not be repeated here.

[0098] Furthermore, in step S106 of the present embodiment, the magnetic field detection element 70 outputs an electrical signal, specifically a voltage signal, based on the sensed magnetic field strength and magnetic field direction. The magnetic field detection element 70 outputs a voltage signal corresponding to a sensed magnetic field strength and magnetic field direction. The magnetic field detection element 70 outputs voltage signals with different voltage values ​​in sequence based on different sensed magnetic field strengths and magnetic field directions.

[0099] Further, in step S108 of the present embodiment, the voltage signal outputted by the magnetic field detection element 70 based on the sensed magnetic field strength and magnetic field direction is processed to obtain the chord angle of the current measurement detection section of the turbine blade 3. The specific method and implementation of processing the voltage signal in step S108 can refer to the prior art in the art. In addition, the electrical signal in the present embodiment can also be other digital signals obtained after processing by the Hall sensor.

[0100] In one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade further includes:

[0101] The straight stop edge 80 provided on the rotating scale plate 8 is sequentially stopped on the blade leading edge 321 and the blade trailing edge 322 of the next metering detection section of the turbine blade 3, and the chord angle of the next metering detection section of the turbine blade 3 is obtained sequentially, wherein a plurality of metering detection sections are selected at intervals on the turbine blade 3 along the extension direction of its blade body 32.

[0102] In this embodiment, the straight stop edge 80 provided on the rotating scale plate 8 is sequentially stopped on the blade leading edge 321 and the blade trailing edge 322 of the next metrological detection section of the turbine blade 3, and the chord angle of the next metrological detection section of the turbine blade 3 is obtained in turn, which is conducive to detecting multiple metrological detection sections on the entire turbine blade 3 and obtaining the chord angles of multiple metrological detection sections on the entire turbine blade 3.

[0103] In this embodiment, when the rotating scale plate 8 is stopped at the next metrology detection section, the next metrology detection section that the rotating scale plate 8 stops at is used as the current metrology detection section; when two or more metrology detection sections of the turbine blade 3 need to be detected during the processing process or other situations, the rotating scale plate 8 can be stopped at the metrology detection sections that need to be detected in turn, and the metrology detection section that the rotating scale plate 8 stops at is used as the current metrology detection section, and the metrology detection section to be detected belongs to the next metrology detection section.

[0104] In one embodiment of the present application, the chord angle of the current measurement detection section of the turbine blade 3 is obtained according to the electrical signal output by the magnetic field detection element 70, including:

[0105] The electrical signal output by the magnetic field detection element 70 is input into the signal processing unit, and the signal processing unit processes the electrical signal input by the magnetic field detection element 70 to obtain the chord angle of the current measurement detection section of the turbine blade 3.

[0106] In this embodiment, the electrical signal output by the magnetic field detection element 70 is input into the signal processing unit. The signal processing unit processes the electrical signal input by the magnetic field detection element 70, which is beneficial for converting the chord angle signal represented by the electrical signal into angle data that is easy to identify, so as to facilitate identification and judgment by the detection personnel.

[0107] In this embodiment, the electrical signal input by the magnetic field detection element 70 is processed by a signal processing unit, and the processing of the electrical signal may include but is not limited to analog filtering, deviation adjustment, amplification, and AC coupling processing; further, the signal processing technology in the prior art may also be used to process the electrical signal in this embodiment, so as to obtain the chord angle of the metering detection section of the turbine blade 3.

[0108] In one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade further includes:

[0109] The obtained chord angle of the current metrology detection section of the turbine blade 3 is compared with the preset qualified chord angle threshold corresponding to the current metrology detection section to obtain the chord angle comparison result of the current metrology detection section, wherein one metrology detection section corresponds to one preset qualified chord angle threshold, different metrology detection sections correspond to different preset qualified chord angle thresholds, and the preset qualified chord angle thresholds corresponding to different metrology detection sections are pre-set according to the qualified ranges of the chord angles of different metrology detection sections;

[0110] According to the obtained comparison result of the chord angle of the current measurement and detection section, it is determined whether the chord angle of the current measurement and detection section is qualified, and the determination result of whether the chord angle of the current measurement and detection section is qualified is obtained.

[0111] In this embodiment, the chord angle of the current metering detection section of the turbine blade 3 is obtained and compared with the preset qualified chord angle threshold corresponding to the current metering detection section, so as to facilitate the determination of whether the chord angle of the current metering detection section is qualified, and facilitate the automatic determination of whether the chord angle of the current metering detection section is qualified.

[0112] In this embodiment, multiple metrology detection sections are selected at intervals along the extension direction of the blade body 32 of the turbine blade 3. For example, in the blade body 32 of a certain model of the turbine blade 3, seven metrology detection sections, namely sections L1-L7, are selected in sequence starting from the blade crown 31 of the turbine blade 3. The spacing from section L1 to the end face of the blade crown 31 is 10.00 mm, the spacing from section L1 to section L2 is 15.20 mm, the spacing from section L2 to section L3 is 20.50 mm, the spacing from section L3 to section L4 is 22.50 mm, the spacing from section L4 to section L5 is 24.30 mm, the spacing from section L5 to section L6 is 24.00 mm, and the spacing from section L6 to section L7 is 25.40 mm. If section L1 is detected for the first time, section L1 will be used as the current metrology detection section when being detected, and any of sections L1-L7 can be regarded as the next metrology detection section.

[0113] In this embodiment, taking section L1 as an example, if the preset qualified chord angle threshold of section L1 is (34.6°-36.6°), when the chord angle of section L1 is within the range of (34.6°-36.6°), section L1 is judged as having a qualified chord angle; and when the chord angle of section L1 is not within the range of (34.6°-36.6°), section L1 is judged as having an unqualified chord angle. Further, the obtained chord angle of the current metering detection section of the turbine blade 3 is compared with the preset qualified chord angle threshold corresponding to the current metering detection section, specifically using a comparator, the working principle and connection method of the comparator can refer to the prior art, and further, the chord angle can also be compared and determined by the inspector.

[0114] Further, such as Figure 8 As shown, in this embodiment, the angle formed between the chord 33 of the measurement detection section and the X-axis is used as the chord angle of the measurement detection section. The chord angle of the measurement detection section can also select different reference axes as references as needed.

[0115] It should be noted that the multiple metrology detection sections of the blade body 32 of the turbine blade 3 can be set according to the metrology detection needs of the turbine blade 3, the spacing between two adjacent metrology detection sections can also be set according to the metrology detection needs of the turbine blade 3, and the number of metrology detection sections can also be adjusted according to the metrology detection needs of the turbine blade 3.

[0116] In one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade further includes:

[0117] When the result of determining whether the chord angle of the current metering detection section is qualified is qualified, the straight stop edge 80 provided on the rotating ruler 8 is stopped on the blade leading edge 321 and the blade trailing edge 322 of the next metering detection section of the turbine blade 3 to obtain the chord angle of the next metering detection section of the turbine blade 3, wherein a plurality of metering detection sections are selected at intervals along the extension direction of the blade body 32 of the turbine blade 3, and the plurality of metering detection sections are pre-selected metering detection sections;

[0118] According to the obtained comparison result of the chord angle of the next measurement and inspection section, whether the chord angle of the next measurement and inspection section is qualified is determined, and a determination result of whether the chord angle of the next measurement and inspection section is qualified is obtained;

[0119] Continue to detect and determine the chord angle of the next metrology detection section of the turbine blade 3 until all the metrology detection sections on the turbine blade 3 have completed detection and determination, wherein, when the determination result of whether the chord angle of any metrology detection section is qualified is unqualified, stop the detection and warn that the turbine blade 3 is an unqualified product and the unqualified metrology detection section is prompted; when all the metrology detection sections on the turbine blade 3 have completed detection and the comparison results of the chord angles of all the metrology detection sections obtained are qualified, stop the detection and feedback that the turbine blade 3 is a qualified product.

[0120] In this embodiment, the chord angles of the metrological inspection sections are detected and determined in sequence whether they are qualified, and when the determination result of whether the chord angle of any metrological inspection section is qualified is unqualified, the detection is stopped and a warning is given that the turbine blade 3 is an unqualified product and an unqualified metrological inspection section is indicated, which is beneficial for inspectors to find unqualified metrological inspection sections and improve inspection efficiency, and is also beneficial for realizing automatic detection and determination of whether the chord angles of multiple metrological inspection sections are qualified.

[0121] In this embodiment, if section L1 is detected for the first time, section L1 is used as the current metrological detection section when being detected, and any section among sections L2-L7 can be regarded as the next metrological detection section; if the preset qualified chord angle threshold of section L1 is (34.6°-36.6°), when the chord angle of section L1 is within the range of (34.6°-36.6°), section L1 is determined to have a qualified chord angle, and the next step is to detect one of the metrological detection sections among sections L2-L7, which are generally detected in sequence, and then section L2 is detected, and it is determined whether the chord angle of section L2 is qualified, and sections L2-L7 are detected and determined in sequence; and when the result of the determination of whether the chord angle of any metrological detection section among sections L2-L7 is qualified is unqualified, the detection is stopped and a warning is given that the turbine blade 3 is an unqualified product and an unqualified metrological detection section is prompted; further, the stopping of detection and the warning can be realized by a pre-edited control program, and the warning can be a flashing light or a whistle.

[0122] In one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade further includes:

[0123] The support plate 7 is driven to move linearly along the extension direction of the blade body 32 of the turbine blade 3 by the linear displacement driving device, and the position of the support plate 7 is adjusted along the extension direction of the blade body 32 of the turbine blade 3, so as to adjust the position of the linear stop edge 80 along the extension direction of the blade body 32 of the turbine blade 3, so that the linear stop edge 80 is aligned with the multiple metrology detection sections to be detected in turn;

[0124] The support plate 7 is driven by the stop drive device to move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3. When the straight stop edge 80 needs to be stopped on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, the support plate 7 is driven by the stop drive device to move linearly close to the turbine blade 3, so that the straight stop edge 80 stops on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3. When the straight stop edge 80 needs to be released from the stop with the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, the support plate 7 is driven by the stop drive device to move linearly away from the turbine blade 3.

[0125] In the present embodiment, the support plate 7 is driven by a linear displacement driving device to move linearly along the extension direction of the blade body 32 of the turbine blade 3, which is beneficial to improving the reliability and alignment accuracy of aligning the linear stop edge 80 with multiple metrological detection sections to be detected; further, in the present embodiment, the support plate 7 is driven by a stop driving device to move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3, which is beneficial to achieve the stop and release of the linear stop edge 80 with the blade leading edge 321 and the blade trailing edge 322 of the metrological detection section of the turbine blade 3.

[0126] In this embodiment, if Figures 2 to 6 As shown, in this embodiment, the linear displacement driving device includes a first screw mechanism 4, and the stop driving device includes a second screw mechanism 5. The upper side of the second driving block 56 provided on the second screw mechanism 5 is horizontally connected with a horizontal connecting plate 59, and the upper side of the horizontal connecting plate 59 is vertically connected with a vertical connecting plate 591; in this embodiment, the first screw mechanism 4 is used to drive the support plate 7 to move linearly along the extension direction of the blade body 32 of the turbine blade 3, and the second screw mechanism 5 is used to drive the support plate 7 to move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3; further, the linear displacement driving device in this embodiment can also adopt other linear displacement driving mechanisms, and the stop driving device in this embodiment can also adopt other linear displacement driving mechanisms, so as to facilitate driving the support plate 7 to move linearly in the left and right directions, and then adjust the position of the rotating scale plate 8 in the left and right directions, and can drive the support plate 7 to move linearly in the front and rear directions, and then adjust the position of the rotating scale plate 8 in the front and rear directions, so as to realize that the rotating scale plate 8 is aligned in sequence and with the measurement detection section to be measured and detected.

[0127] In one embodiment of the present application, the method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade further includes:

[0128] The stop driving device is installed on the linear displacement driving device, and the linear displacement driving device drives the stop driving device to move linearly along the extension direction of the blade body 32 of the turbine blade 3, so as to drive the support plate 7 to move linearly along the extension direction of the blade body 32 of the turbine blade 3;

[0129] The control unit controls the linear displacement driving device to sequentially adjust the position of the linear stop edge 80 along the extension direction of the blade body 32 of the turbine blade 3 based on the first preset displacement control program, so that the linear stop edge 80 is aligned with the multiple metrology detection sections to be detected, wherein the first preset displacement control program is pre-programmed according to the positions of the multiple metrology detection sections of the turbine blade 3;

[0130] After the straight stop edge 80 is aligned with a metering detection section to be detected, the control unit controls the stop drive device based on the second preset displacement control program to drive the support plate 7 to move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3, so that the straight stop edge 80 stops on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, wherein the second preset displacement control program is pre-programmed according to the distance from the midpoint of the chord 33 of multiple metering detection sections to the central axis of the rotating support shaft 811 in a direction perpendicular to the turbine blade 3.

[0131] In this embodiment, the stop drive device is installed on the linear displacement drive device, which is convenient for driving the stop drive device to move linearly along the extension direction of the blade body 32 of the turbine blade 3; further, the linear displacement drive device is controlled by the control unit based on the first preset displacement control program, which is conducive to realizing the automation of aligning the linear stop edge 80 with multiple metrological detection sections to be detected, and further improving the reliability and alignment accuracy of aligning the linear stop edge 80 with multiple metrological detection sections to be detected; further, the stop drive device is controlled by the control unit based on the second preset displacement control program, which is conducive to automatically driving the linear stop edge 80 to stop with the blade leading edge 321 and the blade trailing edge 322 of the metrological detection section of the turbine blade 3 in turn, thereby realizing the automation of detecting multiple metrological detection sections.

[0132] In this embodiment, if Figures 2 to 6As shown, in this embodiment, the linear displacement drive device includes a first screw mechanism 4, and the stop drive device includes a second screw mechanism 5. The drive motor 1 44 on the first screw mechanism 4 is electrically connected to the control unit, and the drive motor 1 44 is controlled by the control unit based on a first preset displacement control program to adjust the position of the linear stop edge 80 in sequence along the extension direction of the blade body 32 of the turbine blade 3; the drive motor 2 54 on the second screw mechanism 5 is electrically connected to the control unit, and the drive motor 2 54 is controlled by the control unit based on a second preset displacement control program to move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3, so that the linear stop edge 80 stops on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3; further, the drive motor 1 44 and the drive motor 2 54 in this embodiment are respectively connected to movable power supply cables and are respectively powered by the power supply cables. There are many ways to connect the drive motor 1 44 and the drive motor 2 54 to the power supply cables, and reference can also be made to the prior art, which will not be described in detail here. It should be noted that drive motor 1 44 is controlled by the control unit based on a first preset displacement control program, and drive motor 2 54 is controlled by the control unit based on a second preset displacement control program. The specific control methods involved, the relevant control programs for implementing the control, and the way in which drive motor 1 44 and drive motor 2 54 are electrically connected to the control unit can all be designed and obtained or implemented using the automation control technology in the prior art, and will not be elaborated here.

[0133] In one embodiment of the present application, before fixing the turbine blade 3, the method includes:

[0134] The standard turbine blade is fixed, wherein the standard turbine blade and the turbine blade 3 are products of the same specification, a plurality of metrological detection sections on the standard turbine blade correspond to a plurality of metrological detection sections on the turbine blade 3, a blade body structural parameter of the standard turbine blade meets the product standard index, a fixed posture of the standard turbine blade is consistent with a fixed posture of the turbine blade, and the standard turbine blade and the turbine blade 3 are metrologically detected using the same metrological detection equipment;

[0135] The straight stop edge 80 provided on the rotating ruler plate 8 is sequentially stopped against the leading edge 321 and the trailing edge 322 of the blade of multiple measurement detection sections of the standard turbine blade, and the magnetic field strength and magnetic field direction generated by the magnetic element 9 at different rotation angle positions are sequentially detected by the magnetic field detection element 70, and the magnetic field detection element 70 sequentially outputs electrical signals based on the sensed magnetic field strength and magnetic field direction;

[0136] According to the electrical signals sequentially output by the magnetic field detection element 70, the standard metrological chord angles of a plurality of metrological detection sections of the standard turbine blade are obtained;

[0137] After obtaining the chord angle of the current measurement detection section of the turbine blade 3, the method for measuring and detecting the chord angle of the section of the turbine blade of an aircraft engine further includes:

[0138] The chord angle of the current metrological detection section of the turbine blade 3 is compared with the standard metrological chord angle of the metrological detection section with the same standard turbine blade position, and the chord angle errors are obtained in turn. According to the obtained chord angle errors, it is determined whether the chord angle of the current metrological detection section is qualified.

[0139] In this embodiment, a metrological inspection is performed on a standard turbine blade to obtain a standard metrological chord angle of multiple metrological inspection sections of the standard turbine blade. In addition, the chord angle of the current metrological inspection section of the turbine blade 3 is compared with the standard metrological chord angle of the metrological inspection section at the same position of the standard turbine blade to obtain a chord angle error, and based on the obtained chord angle error, it is determined in turn whether the chord angle of the current metrological inspection section is qualified. Since the same metrological inspection equipment is used for the metrological inspection, and the standard turbine blade whose blade body structural parameters meet the product standard indicators is used as the metrological inspection comparison object, it is beneficial to offset the influence of the error caused by the accuracy of the metrological inspection equipment itself, and it is beneficial to improve the accuracy of the chord angle measurement of the metrological inspection section of the turbine blade 3, and also improve the accuracy of determining whether the chord angle of the current metrological inspection section of the turbine blade 3 is qualified.

[0140] In this embodiment, multiple metrological detection sections of the standard turbine blade correspond one-to-one to multiple metrological detection sections at the position of the standard turbine blade, and multiple metrological detection sections are selected at intervals in the extension direction of the blade body of the standard turbine blade. For example, in the blade body of a certain model of standard turbine blade, seven metrological detection sections, namely sections L1-L7, are selected in sequence from the blade crown position of the standard turbine blade. The spacing from section L1 to the blade crown end face is 10.00 mm, the spacing from section L1 to section L2 is 15.20 mm, the spacing from section L2 to section L3 is 20.50 mm, the spacing from section L3 to section L4 is 22.50 mm, the spacing from section L4 to section L5 is 24.30 mm, the spacing from section L5 to section L6 is 24.00 mm, and the spacing from section L6 to section L7 is 25.40 mm. If section L1 is detected for the first time, section L1 will be used as the current metrological detection section when being detected, and any of sections L2-L7 of the standard turbine blade can be regarded as the next metrological detection section.

[0141] In this embodiment, taking section L1 as an example, if the standard metrological chord angle of section L1 of a standard turbine blade is 35.6°, and if the allowable error range is plus or minus 1.0°, when the chord angle of section L1 of turbine blade 3 is greater than or equal to 34.6° and less than or equal to 36.6°, section L1 of turbine blade 3 is judged to have a qualified chord angle; and when the chord angle of section L1 is less than 34.6° or greater than 36.6°, section L1 of turbine blade 3 is judged to have an unqualified chord angle. Further, according to the obtained chord angle error, it is judged in turn whether the chord angle of the current metrological detection section is qualified, and other calculation or judgment methods can also be used.

[0142] In the present embodiment, the aircraft engine turbine blade cross-section chord angle metrology detection system in the present embodiment is used to perform metrology detection on multiple metrology detection sections of the standard turbine blade to obtain standard metrology chord angles of the multiple metrology detection sections of the standard turbine blade; then, the aircraft engine turbine blade cross-section chord angle metrology detection system in the present embodiment is used to perform metrology detection on multiple metrology detection sections of turbine blade 3, and the obtained chord angles of the multiple metrology detection sections of turbine blade 3 are respectively compared with the standard metrology chord angles of the multiple metrology detection sections of the corresponding standard turbine blades. When the same aircraft engine turbine blade cross-section chord angle metrology detection system is used for metrology detection, it is beneficial to offset the influence of errors caused by the accuracy of the aircraft engine turbine blade cross-section chord angle metrology detection system itself.

[0143] According to another aspect of the present application, a system for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade is provided, which is used to implement the above-mentioned method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade, such as Figures 2 to 9 As shown, including:

[0144] Base 1;

[0145] The blade fixing seat 2 is installed on the base 1, and the blade fixing seat 2 is used to fix the turbine blade 3;

[0146] A linear displacement driving device is installed on one side of the blade fixing seat 2;

[0147] The stop driving device is installed on the linear displacement driving device and is located on one side of the blade fixing seat 2, and the stop driving device can move linearly along the extension direction of the blade body 32 of the turbine blade 3 installed on the blade fixing seat 2 under the drive of the linear displacement driving device;

[0148] The support plate 7 is mounted on the stop driving device, and the support plate 7 can move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3 mounted on the blade fixing seat 2 under the drive of the stop driving device;

[0149] The rotating ruler plate 8 is rotatably mounted on the supporting plate 7 by means of the rotating supporting shaft 811. A straight stop edge 80 is provided on one side of the rotating ruler plate 8 facing the leading edge 321 and the trailing edge 322 of the turbine blade 3 mounted on the blade fixing seat 2. The straight stop edge 80 is used to stop against the leading edge 321 and the trailing edge 322 of the measuring detection section of the turbine blade 3 mounted on the blade fixing seat 2, and the straight stop edge 80 serves as a chord line 33 passing through the current measuring detection section and being tangent to the leading edge 321 and the trailing edge 322 of the blade.

[0150] The magnetic element 9 is mounted on the rotating support shaft 811. The magnetic element 9 rotates synchronously around the central axis of the rotating support shaft 811 as the rotating ruler 8 rotates.

[0151] The magnetic field detection element 70 is mounted on the support plate 7 and located on one side of the magnetic element 9. The magnetic field detection element 70 is used to detect the magnetic field strength and magnetic field direction generated by the magnetic element 9 located at the current rotation angle position, and the magnetic field detection element 70 can output an electrical signal based on the sensed magnetic field strength and magnetic field direction.

[0152] In this embodiment, if Figures 2 to 6 As shown, the straight stop edge 80 provided on the rotating ruler plate 8 in this embodiment is used to stop against the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, which is conducive to stopping the straight stop edge 80 on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, and using the straight stop edge 80 as the chord 33 passing through the current metering detection section and tangent to the blade leading edge 321 and the blade trailing edge 322, thereby facilitating the measurement of the angle of the straight stop edge 80 to achieve the measurement of the chord angle of the current metering detection section, and facilitating the acquisition of the chord angle of the metering detection section; further, the rotating ruler plate 8 and the magnetic element 9 in this embodiment It can rotate synchronously, and detects the magnetic field strength and direction generated by the magnetic element 9 at the current rotation angle position through the magnetic field detection element 70. The magnetic field detection element 70 outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction, and obtains the chord angle of the current metering detection section of the turbine blade 3 according to the electrical signal output by the magnetic field detection element 70, so as to characterize the chord angle of the metering detection section through the electrical signal, which is conducive to the measurement and acquisition of the chord angle of the current metering detection section of the turbine blade 3, and is convenient for the measurement and detection of the cross-sectional chord angle of the turbine blade 3 during the processing process and reduces the detection cost, and is not easily affected by the temperature and humidity in the detection environment. Furthermore, by providing a linear displacement drive device and a stop drive device, it is convenient to adjust the position of the linear stop edge 80 and drive the linear stop edge 80 to stop with the blade leading edge 321 and the blade trailing edge 322 of the metering detection section.

[0153] In this embodiment, if Figures 2 to 6 As shown, the base 1 in this embodiment is a rectangular plate-shaped structure, and four supporting protrusions 10 are provided on the lower side of the base 1, and the base 1 is horizontally supported by the four supporting protrusions 10; further, four supporting protrusions 2 11 are provided on the upper side of the base 1, and four mounting protrusions 20 are provided on the blade fixing seat 2 respectively facing the four supporting protrusions 2 11, and the mounting protrusions 20 are respectively installed on the supporting protrusions 11 by fixing bolts 25 and fixing nuts 26.

[0154] In this embodiment, if Figures 2 to 6 As shown, the turbine blade 3 in this embodiment includes a tenon 30, a blade crown 31 and a blade body 32, and the blade body 32 is connected between the tenon 30 and the blade crown 31; a tenon positioning block 21 is installed on the left side of the blade fixing seat 2 in this embodiment by bolts, and the tenon positioning block 21 is horizontally installed on the upper side of the blade fixing seat 2, and the tenon 30 of the turbine blade 3 is horizontally supported by the tenon positioning block 21, and a tenon lateral positioning portion 211 is provided at the rear of the tenon positioning block 21, and the tenon 30 of the turbine blade 3 is positioned by the tenon lateral positioning portion 211; further, a blade crown positioning support block 22 is installed on the right side of the blade fixing seat 2 by bolts, and the blade crown 31 of the turbine blade 3 is horizontally supported by the blade crown positioning support block 22. In addition, a blade body positioning stop block 23 is also installed on the right side of the blade fixing seat 2 by bolts, and the blade body positioning stop block 23 is located on the left side of the blade crown positioning support block 22, and the rear side of the right end of the blade body 32 is stopped and limited by the blade body positioning stop block 23.

[0155] Further, such as Figures 2 to 6 As shown, a mounting groove is provided on the lower side of the blade fixing seat 2 in this embodiment, and the lower side of the mounting groove is open. In this embodiment, in order to limit the front side of the blade body 32 of the turbine blade 3, a locking stop swing arm 27 is installed on the blade fixing seat 2. The locking stop swing arm 27 is used to limit the front side of the blade body 32 of the turbine blade 3; the locking stop swing arm 27 is approximately L-shaped, and the locking stop swing arm 27 includes a vertical plate and a stop portion, and the stop portion is used to fit and stop with the recessed front side wall of the blade body 32, and the stop portion is used to One end that abuts against the recessed front side wall of the blade body 32 is in an arc shape, and a movable avoidance opening 24 is opened on the front side of the blade fixing seat 2. The movable avoidance opening 24 is opened vertically and connected to the mounting groove body. The vertical plate of the locking and abutting swing arm 27 passes through the movable avoidance opening 24. The lower end of the vertical plate of the locking and abutting swing arm 27 is hingedly connected to the lower end of the blade fixing seat 2 and is located in the mounting groove body. The front side of the vertical plate of the locking and abutting swing arm 27 is also connected to one end of a tension spring 29, and the other end of the tension spring 29 is connected to the front side wall of the mounting groove body.

[0156] Further, such as Figures 2 to 6As shown, the locking and abutting swing arm 27 in this embodiment adjusts the position of the locking and abutting swing arm 27 through the thrust control knob 28, so that the locking and abutting swing arm 27 abuts or releases the abutment with the blade body 32 of the turbine blade 3. Specifically, a threaded through hole is provided on the front side wall of the blade fixing seat 2, and the thrust control knob 28 includes a thrust threaded rod and a control knob. The thrust threaded rod and the control knob are connected, and the thrust threaded rod is threadedly connected with the threaded through hole provided on the front side wall of the blade fixing seat 2. The threaded through hole is located on the upper side of the tension spring 29, and the thrust threaded rod extends into the mounting groove body provided on the lower side of the blade fixing seat 2 and abuts against the front side of the vertical plate of the locking and abutting swing arm 27; further, when the thrust control knob 28 is turned, the thrust control knob The thrust threaded rod 28 is screwed backward, and the thrust threaded rod pushes the locking stop arm 27 backward to swing backward in the movable avoidance opening 24, and makes the stop portion of the locking stop arm 27 fit and stop against the front side wall of the recess. Therefore, in this embodiment, the turbine blade 3 is fixed together by the tenon positioning block 21, the blade crown positioning support block 22, the blade body positioning stop block 23 and the locking stop arm 27; in addition, when it is necessary to remove the turbine blade 3, the thrust control knob 28 is turned in the opposite direction, so that the thrust threaded rod of the thrust control knob 28 is rotated forward, and under the pulling force of the tension spring 29, the thrust threaded rod swings forward in the movable avoidance opening 24 and releases the pushing effect on the locking stop arm 27, thereby releasing the fixation of the turbine blade 3.

[0157] It should be noted that the structure of the blade fixing seat 2 in this embodiment can be various, and there can be various ways to fix the turbine blade 3 placed on the blade fixing seat 2, so as to facilitate the realization of stopping the straight stop edge 80 provided on the rotating scale plate 8 on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3, and successively realize the metering detection of multiple metering detection sections of the turbine blade 3, and obtain the chord angles of multiple metering detection sections of the turbine blade 3.

[0158] In this embodiment, if Figures 2 to 7 and Fig. 9As shown, the magnetic field detection element 70 in this embodiment is specifically a Hall sensor, and a cable interface 701 is provided on the magnetic field detection element 70, which is convenient for connecting to the cable interface 701 through a cable, so as to facilitate the magnetic field detection element 70 to output the electrical signal based on the sensed magnetic field strength and magnetic field direction. The Hall sensor in this embodiment is specifically electrically connected to the signal processing unit through a cable, and the Hall sensor is also electrically connected through a cable control unit; it should be noted that the Hall sensor detects the magnetic field strength and magnetic field direction generated by the magnetic element 9 based on the Hall effect, and the principle of the Hall sensor detecting the magnetic field strength and magnetic field direction generated by the element and the specific structure of the Hall sensor can refer to the existing technology in the field, and will not be repeated here; in addition, the magnetic field detection element 70 in this embodiment can also adopt other magnetic field detection elements 70 that can detect the magnetic field strength and magnetic field direction generated by the magnetic element 9 and output electrical signals based on the sensed magnetic field strength and magnetic field direction.

[0159] In this embodiment, if Figure 2 and Figure 7 As shown, the magnetic element 9 in this embodiment is specifically a circular ring magnet; further, the rotating scale plate 8 in this embodiment is in the shape of a straight strip, and an inclined slope structure is provided on the rear side of the rotating scale plate 8, and the rear end of the inclined slope structure forms a straight stop edge 80, and the inclined slope structure in this embodiment is inclined in a manner of narrowing to the right. In addition, a connecting protrusion 81 is connected to the middle part of the side of the rotating scale plate 8 away from the blade fixing seat 2, and a rotating support shaft 811 is connected to the right side of the connecting protrusion 81, and the right section of the rotating support shaft 811 is a magnet mounting section 812, and the magnet mounting section 812 is in a cylindrical structure, and the circular ring magnet is mounted on the magnet mounting section 812. In addition, a threaded hole 8121 is provided at the right end of the magnet mounting section 812 in this embodiment, and the circular ring magnet is locked and mounted on the magnet mounting section 812 by a locking screw 813, and the locking screw 813 is threadedly connected to the threaded hole.

[0160] Furthermore, the annular magnet in this embodiment includes an N pole and an S pole. When the rotating scale plate 8 rotates, the angular position of the annular magnet including the N pole and the S pole also changes. The magnetic field detection element 70 detects the magnetic field strength and magnetic field direction generated by the magnetic element 9 located at the current rotation angle position. The magnetic element 9 is located at different angular positions, and the magnetic field strength and magnetic field direction sensed by the magnetic field detection element 70 correspond to the angular position; further, the specific data of the voltage signal output by the magnetic field detection element 70 based on the sensed magnetic field strength and magnetic field direction is jointly determined by the magnetic field strength of the annular magnet used, the initial installation position of the annular magnet, and the initial angular position of the N pole and S pole of the annular magnet, and will not be described in detail here.

[0161] An embodiment of the present application, such as Figures 2 to 6As shown, the turbine blade 3-section chord angle measurement and detection system also includes:

[0162] The elastic force-applying device 6 is installed on the stop drive device and is located on one side of the blade fixing seat 2. The support plate 7 is installed on the elastic force-applying device 6. The elastic force-applying device 6 is used to apply an elastic extrusion force to the rotating scale plate 8 rotatably installed on the support plate 7, so that the straight stop edge 80 provided on the rotating scale plate 8 stops on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section of the turbine blade 3.

[0163] In this embodiment, if Figures 2 to 6 As shown, the elastic force-applying device 6 in this embodiment can apply an elastic squeezing force to the rotating scale plate 8 rotatably mounted on the support plate 7, thereby facilitating the straight stop edge 80 provided on the rotating scale plate 8 to stop against the blade leading edge 321 and the blade trailing edge 322 of the metering and detection section of the turbine blade 3, and the elastic force-applying device 6 can apply a pre-tightening force to the straight stop edge 80, which is facilitating the straight stop edge 80 to tightly stop against the blade leading edge 321 and the blade trailing edge 322 of the metering and detection section, and is facilitating avoiding excessive squeezing of the straight stop edge 80 and the blade leading edge 321 and the blade trailing edge 322 of the metering and detection section.

[0164] An embodiment of the present application, such as Figures 2 to 6 As shown, the elastic force applying device 6 comprises:

[0165] Install the support seat 60, which is vertically installed on the stop driving device;

[0166] A plurality of guide rods 61 are provided, and the plurality of guide rods 61 are horizontally connected to the mounting support seat 60 and extend linearly toward the blade fixing seat 2;

[0167] The support movable seat 62 is movably installed between the multiple guide rods 61. The support movable seat 62 is provided with multiple guide through holes corresponding to the multiple guide rods 61. The guide rods 61 are inserted into the guide through holes corresponding to them and pass through the guide through holes. The support plate 7 is vertically connected to the side of the support movable seat 62 away from the installation support seat 60.

[0168] The spring 63 is installed between the supporting movable seat 62 and the mounting supporting seat 60 . One end of the spring 63 is connected to the mounting supporting seat 60 , and the other end of the spring 63 is connected to the supporting movable seat 62 .

[0169] In this embodiment, if Figures 2 to 6As shown, the multiple guide rods 61 in this embodiment can guide the supporting movable seat 62, which is conducive to the linear movement of the supporting movable seat 62 along the extension direction of the guide rods 61, and then it is conducive to driving the support plate 7 installed on the supporting movable seat 62 to move directly, which is conducive to improving the alignment of the linear stop edge 80 installed on the support plate 7 with the metering detection section of the turbine blade 3; further, the spring 63 is installed between the supporting movable seat 62 and the mounting support seat 60, which is conducive to the spring 63 being compressed to form an elastic force and acting on the linear stop edge 80 installed on the support plate 7, so that the linear stop edge 80 is tightly stopped on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section, and when the extrusion pressure between the linear stop edge 80 and the blade leading edge 321 and the blade trailing edge 322 of the metering detection section is large, the spring 63 is further elastically compressed to avoid excessive extrusion of the linear stop edge 80 and the blade leading edge 321 and the blade trailing edge 322 of the metering detection section.

[0170] In this embodiment, if Figures 2 to 6 As shown, the stop drive device in this embodiment includes a second screw mechanism 5, and the upper side of the second drive block 56 provided on the second screw mechanism 5 is horizontally connected to a horizontal connecting plate 59, and the upper side surface of the horizontal connecting plate 59 is vertically connected to a vertical connecting plate 591, and the elastic force applying device 6 in this embodiment is installed on the vertical connecting plate 591.

[0171] Further, such as Figures 2 to 6 As shown, the mounting support seat 60 in this embodiment is a rectangular plate-shaped structure, and the mounting support seat 60 is fixedly connected to the horizontal connecting plate 59. In this embodiment, four guide rods 61 are provided, and the four guide rods 61 are horizontally connected to the rear side of the mounting support seat 60 and extend linearly backward; the supporting movable seat 62 in this embodiment is a rectangular plate-shaped structure, and four guide through holes are provided on the supporting movable seat 62 facing the four guide rods 61, and the guide rods 61 are inserted into the guide through holes corresponding to them and pass through the guide through holes backward; further The support plate 7 in this embodiment is vertically connected to the rear side surface of the supporting movable seat 62. In addition, a cylindrical protrusion 1 is connected to the middle part of the rear side surface of the mounting support seat 60, and a cylindrical protrusion 2 is connected to the front side surface of the supporting movable seat 62 opposite to the cylindrical protrusion 1. One end of the spring 63 is fixedly connected to the cylindrical protrusion 1, and the other end of the spring 63 is fixedly connected to the cylindrical protrusion 2, so that the spring 63 is connected between the mounting support seat 60 and the supporting movable seat 62; further, the elastic force applying device 6 in this embodiment is also arranged as other structures.

[0172] An embodiment of the present application, such as Figures 2 to 6 As shown, the linear displacement driving device includes a first screw mechanism 4, and the first screw mechanism 4 is horizontally mounted on the base 1;

[0173] The stop drive device includes a second screw mechanism 5, which is horizontally mounted on a first drive block 46 provided on the first screw mechanism 4 and is vertically arranged relative to the first screw mechanism 4. The second screw mechanism 5 can move linearly along the extension direction of the blade body 32 of the turbine blade 3 installed on the blade fixing seat 2 under the drive of the first screw mechanism 4. The second screw mechanism 5 and the first screw mechanism 4 together constitute a cross slide mechanism.

[0174] The support plate 7 is mounted on the second driving block 56 on the second screw mechanism 5 , and the support plate 7 can move linearly relative to the turbine blade 3 in a direction perpendicular to the turbine blade 3 mounted on the blade fixing seat 2 under the drive of the second screw mechanism 5 .

[0175] In this embodiment, if Figures 2 to 6 As shown, the second screw mechanism 5 and the first screw mechanism 4 in this embodiment together constitute a cross slide mechanism, which is conducive to the first screw mechanism 4 driving the second screw mechanism 5 to move linearly along the extension direction of the blade body 32 of the turbine blade 3 installed on the blade fixing seat 2, so that the straight stop edges 80 installed on the support plate 7 are respectively aligned with the metering detection sections to be detected, and it is also conducive to the second screw mechanism 5 driving the support plate 7 to move linearly, thereby facilitating the straight stop edge 80 to accurately stop on the blade leading edge 321 and the blade trailing edge 322 of the metering detection section.

[0176] In this embodiment, if Figures 2 to 6 As shown, four supporting protrusions three 12 are provided on the front part of the upper side surface of the base 1, and the four supporting protrusions three 12 are installed with a mounting support frame 13. The mounting support frame 13 is installed on the four supporting protrusions three 12 by fixing bolts and fixing nuts, and the first screw mechanism 4 is horizontally installed on the upper side of the mounting support frame 13.

[0177] In this embodiment, if Figures 2 to 6As shown, the first screw mechanism 4 in this embodiment is installed on the upper side of the mounting support frame 13 along the left-right direction. The first screw mechanism 4 in this embodiment includes a horizontal support plate 40, a drive motor 44, a screw 45, a first drive block 46, a sliding guide rail 47 and a slider 48. The horizontal support plate 40 is a rectangular parallelepiped structure. The horizontal support plate 40 is horizontally installed on the upper side of the mounting support frame 13 and the length direction of the horizontal support plate 40 is oriented to the left-right direction. A vertical mounting plate 41 is installed at the right end of the horizontal support plate 40. The drive motor A vertical mounting plate 41 is mounted on a drive motor 44, a drive shaft 441 is provided on the drive motor 44 and passes through the vertical mounting plate 41 to the left horizontally. A lead screw 45 in this embodiment is horizontally arranged along the left and right directions. The left and right ends of the lead screw 45 are rotatably supported by a rotating support seat 42 and a rotating support seat 43. The rotating support seat 42 and the rotating support seat 43 are respectively fixedly connected to the horizontal support plate 40 by bolts. The right end of the lead screw 45 passes through the rotating support seat 42 and is fixedly connected to the drive shaft 441 by a connector 442.

[0178] Further, such as Figures 2 to 6 As shown, in this embodiment, there are two sliding guide rails 47, and the two sliding guide rails 47 are fixedly installed on the front and rear of the horizontal support plate 40 by multiple bolts, and a slider 48 is slidably installed on each of the sliding guide rails 47; a first driving block 46 is threadedly connected to the lead screw 45, and the first driving block 46 is slidably installed on the two sliding guide rails 47 in the front-to-back direction; further, the upper side surfaces of the two sliding blocks 48 and the first driving block 46 are fixedly connected with a horizontal support plate 2 50, and the horizontal support plate 2 50 fixes the two sliding blocks 48 and the first driving block 46 together; under the drive of the driving motor 44, the driving shaft 441 drives the lead screw 45 to rotate, and the rotating lead screw 45 drives the first driving block 46 to move in the left and right direction, and at the same time makes the slider 48 slide along the extension direction of the sliding guide rail 47.

[0179] In this embodiment, if Figures 2 to 6As shown, the second screw mechanism 5 in this embodiment is installed on the upper side of the first screw mechanism 4 along the front-to-back direction. The second screw mechanism 5 in this embodiment includes a horizontal support plate 2 50, a drive motor 2 54, a screw 2 55, a second drive block 56, a sliding guide rail 2 57 and a slider 2 58. The horizontal support plate 2 50 is a rectangular parallelepiped structure. The horizontal support plate 2 50 is horizontally fixedly installed on the upper side of the two sliders 2 58 and the upper side of the second drive block 56. The length direction of the horizontal support plate 2 50 is in the front-to-back direction. The front end of the horizontal support plate 2 50 is installed with a vertical mounting plate 2 51, a driving motor 2 54 is mounted on a vertical mounting plate 2 51, a driving shaft 2 541 provided on the driving motor 2 54 passes horizontally through the vertical mounting plate 2 51 backwards, a lead screw 2 55 in this embodiment is horizontally arranged along the front-to-back direction, the front and rear ends of the lead screw 2 55 are rotatably supported by a rotating support seat 3 52 and a rotating support seat 4 53, the rotating support seat 3 52 and the rotating support seat 4 53 are respectively fixedly connected to the horizontal support plate 2 50 by bolts, and the front end of the lead screw 2 55 passes through the rotating support seat 3 52 and is fixedly connected to the driving shaft 2 541 by a connector 2 542.

[0180] Further, such as Figures 2 to 6 As shown, in this embodiment, there are two sliding guide rails 2 57, and the two sliding guide rails 2 57 are fixedly installed on the left and right parts of the horizontal support plate 2 50 by multiple bolts, and a sliding block 2 58 is slidably installed on each of the sliding guide rails 2 57; a second driving block 56 is threadedly connected to the lead screw 2 55, and the second driving block 56 is slidably installed on the two sliding guide rails 2 57 in the left and right directions; further, the upper side surfaces of the two sliding blocks 2 58 and the second driving block 56 are fixedly connected with a horizontal connecting plate 59, and the horizontal connecting plate 59 fixes the two sliding blocks 2 58 and the second driving block 56 together; under the drive of the driving motor 2 54, the driving shaft 2 541 drives the lead screw 2 55 to rotate, and the rotating lead screw 2 55 drives the second driving block 56 to move in the front and rear directions, and at the same time makes the sliding block 2 58 slide along the extension direction of the sliding guide rail 2 57.

[0181] It should be noted that the linear displacement drive device in this embodiment can also adopt other linear displacement drive mechanisms, and the stop drive device in this embodiment can also adopt other linear displacement drive mechanisms, so as to facilitate driving the support plate 7 in this embodiment to move linearly in the left and right directions, and then adjust the position of the rotating scale plate 8 in the left and right directions, and can drive the support plate 7 to move linearly in the front and back directions, and then adjust the position of the rotating scale plate 8 in the front and back directions, so as to realize the alignment of the rotating scale plate 8 in sequence and with the measurement and detection section to be measured and detected.

[0182] In one embodiment of the present application, the turbine blade 3 cross-section chord angle measurement and detection system further includes:

[0183] A signal processing unit, the magnetic field detection element 70 is electrically connected to the signal processing unit, and the signal processing unit is used to perform signal processing on the electrical signal output by the magnetic field detection element 70 to obtain the chord angle of the current measurement detection section of the turbine blade 3;

[0184] A display unit, electrically connected to the signal processing unit, and used for displaying the obtained chord angle of the current measurement detection section of the turbine blade 3;

[0185] The control unit, the magnetic field detection element 70, the linear displacement driving device, the stop driving device, the signal processing unit and the display unit are electrically connected to the control unit respectively.

[0186] In this embodiment, the magnetic field detection element 70 is electrically connected to the signal processing unit, so that the signal processing unit can process the electrical signal output by the magnetic field detection element 70 to obtain the chord angle of the current metering detection section of the turbine blade 3; further, the display unit is electrically connected to the signal processing unit, so that the obtained chord angle of the metering detection section of the turbine blade 3 can be displayed for easy viewing by the inspection personnel; further, the magnetic field detection element 70, the linear displacement drive device, the stop drive device, the signal processing unit and the display unit are respectively electrically connected to the control unit, which is conducive to realizing the automation of metering detection of the chord angles of multiple metering detection sections of the turbine blade 3.

[0187] In this embodiment, the signal processing unit in this embodiment may be a signal processor, the display unit may be a display screen, the control unit may be a control chip, and the signal processing unit may also be integrated in the control chip. It should be noted that the signal processing unit, the display unit, and the control unit are not illustrated in this embodiment; in addition, based on this embodiment, other applicable metrology and detection equipment may also be used to implement the aircraft engine turbine blade cross-section chord angle metrology and detection method in this embodiment.

[0188] In another aspect of the present application, a computer-readable storage medium is provided, in which a computer program is stored. When the computer program is executed by a processor, the method of the embodiment of the present application is implemented.

[0189] In another aspect of the present application, an electronic device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the method of the embodiment of the present application is implemented when the processor executes the computer program.

[0190] In the present embodiment, the electronic device is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present invention described and / or claimed herein.

[0191] In this embodiment, the electronic device includes a computing unit, which may be various general and / or special processing components with processing and computing capabilities. Some examples of computing units include, but are not limited to, CPUs, graphics processing units (GPUs), various dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit performs the various methods and processes described above. For example, in some embodiments, the method embodiments of the present invention may be implemented as a computer program, which is tangibly contained in a machine-readable medium, such as a storage unit. In some embodiments, part or all of the computer program may be loaded and / or installed on an electronic device via a ROM and / or a communication unit. In some embodiments, the computing unit may be configured to perform the above method in any other appropriate manner (e.g., by means of firmware).

[0192] In this embodiment, the computer program for implementing the method of the embodiment of the present invention can be written in any combination of one or more programming languages. These computer programs can be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that when the computer program is executed by the processor or controller, the functions / operations specified in the flow chart and / or block diagram are implemented. The computer program can be executed entirely on the machine, partially on the machine, partially on the machine as a stand-alone software package and partially on a remote machine, or entirely on a remote machine or server.

[0193] In the context of an embodiment of the present invention, a computer-readable storage medium may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable signal medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or device, or any suitable combination of the foregoing. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0194] In addition, in addition to the technical solutions disclosed in this embodiment, the first screw mechanism 4, the second screw mechanism 5, the Hall sensor, the turbine blade 3, the signal processing unit, the display unit, the control unit and the working principle thereof in the present invention may refer to the conventional technical solutions in this technical field, and these conventional technical solutions are not the focus of the present invention, and the present invention will not describe them in detail herein.

[0195] It should be noted that the term "including" and its variations used in the embodiments of the present application are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". The modifications of "one" and "multiple" mentioned in the embodiments of the present application are illustrative and not restrictive. Those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0196] The term "embodiment" in this specification refers to specific features, structures or characteristics described in conjunction with the embodiment that can be included in at least one embodiment of the present invention. The appearance of this phrase in various places in the specification does not necessarily mean the same embodiment, nor does it mean that it is mutually exclusive with other embodiments and is independent or optional. The various embodiments in this specification are described in a related manner, and the same or similar parts between the various embodiments refer to each other. In particular, for the device, equipment, and system embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts refer to the partial description of the method embodiment.

[0197] The above are only preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. 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. A method for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade, characterized in that: The method comprises: Fix the turbine blades; The straight stop edge provided on the rotating scale plate is stopped on the leading edge and the trailing edge of the blade of the metering detection section of the turbine blade, and the straight stop edge is used as a chord passing through the current metering detection section and tangent to the leading edge and the trailing edge of the blade, wherein the straight stop edge is provided on the side of the rotating scale plate facing the leading edge and the trailing edge of the blade, and the straight stop edge is used to stop with the leading edge and the trailing edge of the blade, the rotating scale plate is rotatably mounted on the support plate through a rotating support shaft, the rotating support shaft is fixedly connected to one side of the rotating scale plate, the rotating support shaft is rotatably mounted on the support plate, and a magnetic element is mounted on the rotating support shaft, and the magnetic element rotates synchronously around the central axis of the rotating support shaft as the rotating scale plate rotates; detecting the magnetic field strength and magnetic field direction generated by the magnetic element at the current rotation angle position by means of a magnetic field detection element, wherein the magnetic field detection element outputs an electrical signal based on the sensed magnetic field strength and magnetic field direction; According to the electrical signal output by the magnetic field detection element, the chord angle of the current metering detection section of the turbine blade is obtained, wherein different electrical signals are used to characterize different chord angles, respectively. When the rotational angle position of the magnetic element changes, the magnetic field strength and magnetic field direction sensed by the magnetic field detection element change with the change of the rotational angle position of the magnetic element, and the electrical signal output by the magnetic field detection element changes with the change of the magnetic field strength and magnetic field direction sensed by the magnetic field detection element.

2. The method according to claim 1, characterized in that The method further comprises: The straight stop edge provided on the rotating scale plate is sequentially stopped against the blade leading edge and the blade trailing edge of the next metering detection section of the turbine blade, and the chord angle of the next metering detection section of the turbine blade is obtained sequentially, wherein a plurality of metering detection sections are selected at intervals on the turbine blade along the extension direction of the blade body.

3. The method according to claim 1, characterized in that The step of obtaining the chord angle of the current measurement detection section of the turbine blade according to the electrical signal output by the magnetic field detection element comprises: The electrical signal output by the magnetic field detection element is input into a signal processing unit, and the electrical signal input by the magnetic field detection element is processed by the signal processing unit to obtain the chord angle of the current measurement detection section of the turbine blade.

4. The method according to claim 1, characterized in that: The method further comprises: Compare the obtained chord angle of the current metering detection section of the turbine blade with the preset qualified chord angle threshold corresponding to the current metering detection section to obtain a comparison result of the chord angle of the current metering detection section, wherein one metering detection section corresponds to one preset qualified chord angle threshold, different metering detection sections correspond to different preset qualified chord angle thresholds, and the preset qualified chord angle thresholds corresponding to different metering detection sections are pre-set according to the qualified ranges of the chord angles of different metering detection sections; According to the obtained comparison result of the chord angle of the current measurement detection section, it is determined whether the chord angle of the current measurement detection section is qualified, and a determination result of whether the chord angle of the current measurement detection section is qualified is obtained.

5. The method according to claim 4, characterized in that The method further comprises: When the result of determining whether the chord angle of the current metering detection section is qualified is qualified, the straight stop edge provided on the rotating scale plate is stopped against the blade leading edge and the blade trailing edge of the next metering detection section of the turbine blade to obtain the chord angle of the next metering detection section of the turbine blade, wherein a plurality of metering detection sections are selected at intervals along the extension direction of the blade body of the turbine blade, and the plurality of metering detection sections are pre-selected metering detection sections; According to the obtained comparison result of the chord angle of the next measurement detection section, whether the chord angle of the next measurement detection section is qualified is determined, and a determination result of whether the chord angle of the next measurement detection section is qualified is obtained; Continue to detect and determine the chord angle of the next metrology detection section of the turbine blade until all the metrology detection sections on the turbine blade have completed detection and determination, wherein, when the result of determination as to whether the chord angle of any one of the metrology detection sections is qualified is unqualified, stop detection and warn that the turbine blade is an unqualified product and indicate the unqualified metrology detection section; when all the metrology detection sections on the turbine blade have completed detection and the comparison results of the chord angles of all the metrology detection sections are qualified, stop detection and provide feedback that the turbine blade is a qualified product.

6. The method according to claim 5, characterized in that The method further comprises: The support plate is driven to move linearly along the extension direction of the blade body of the turbine blade by a linear displacement driving device, and the position of the support plate is adjusted along the extension direction of the blade body of the turbine blade, so as to adjust the position of the linear stop edge along the extension direction of the blade body of the turbine blade, so as to sequentially align the linear stop edge with the plurality of the metrological detection sections to be detected; The support plate is driven by a stop drive device to move linearly relative to the turbine blade in a direction perpendicular to the turbine blade. When the straight stop edge needs to be abutted against the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, the support plate is driven by the stop drive device to move linearly close to the turbine blade so that the straight stop edge abuts against the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade. When the straight stop edge needs to be released from the abutment with the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, the support plate is driven by the stop drive device to move linearly away from the turbine blade.

7. The method according to claim 6, characterized in that The method further comprises: The stop driving device is installed on the linear displacement driving device, and the linear displacement driving device drives the stop driving device to move linearly along the extension direction of the blade body of the turbine blade, so as to drive the support plate to move linearly along the extension direction of the blade body of the turbine blade; Controlling the linear displacement driving device to sequentially adjust the position of the linear stop edge along the extension direction of the blade body of the turbine blade based on a first preset displacement control program by a control unit, so that the linear stop edge is aligned with a plurality of the metrology detection sections to be detected, wherein the first preset displacement control program is pre-programmed according to the positions of the plurality of the metrology detection sections of the turbine blade; After the straight stop edge is aligned with a metering detection section to be detected, the control unit controls the stop drive device to drive the support plate to move linearly relative to the turbine blade in a direction perpendicular to the turbine blade based on a second preset displacement control program, so that the straight stop edge stops on the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade, wherein the second preset displacement control program is pre-programmed according to the distances from the midpoints of the chords of multiple metering detection sections to the central axis of the rotating support shaft in a direction perpendicular to the turbine blade.

8. The method according to any one of claims 1 to 3, characterized in that: Before fixing the turbine blade, the method includes: Fixing a standard turbine blade, wherein the standard turbine blade and the turbine blade are products of the same specification, a plurality of metrological detection sections on the standard turbine blade correspond one to one with a plurality of the metrological detection sections on the turbine blade, a blade body structural parameter of the standard turbine blade meets product standard indicators, a fixing posture of the standard turbine blade is consistent with a fixing posture of the turbine blade, and the standard turbine blade and the turbine blade are metrologically detected using the same metrological detection equipment; The straight stop edge provided on the rotating scale plate is sequentially stopped against the leading edge and trailing edge of the blade of the plurality of the metrological detection sections of the standard turbine blade, and the magnetic field strength and magnetic field direction generated by the magnetic element at different rotation angles are sequentially detected by the magnetic field detection element, and the magnetic field detection element sequentially outputs electrical signals based on the sensed magnetic field strength and magnetic field direction; According to the electrical signals sequentially output by the magnetic field detection elements, standard metrological chord angles of a plurality of metrological detection sections of the standard turbine blade are obtained; After obtaining the chord angle of the current metrology detection section of the turbine blade, the method further includes: The chord angle of the current metrology detection section of the turbine blade is compared with the standard metrology chord angle of the metrology detection section with the same position as the standard turbine blade, and the chord angle errors are obtained in turn. According to the obtained chord angle errors, it is determined whether the chord angle of the current metrology detection section is qualified.

9. A system for measuring and detecting the cross-sectional chord angle of an aircraft engine turbine blade, used for implementing the method described in any one of claims 1 to 5, characterized in that: include: Pedestal; A blade fixing seat, mounted on the base, and used to fix the turbine blade; A linear displacement driving device is installed on one side of the blade fixing seat; A stop driving device is installed on the linear displacement driving device and is located on one side of the blade fixing seat, and the stop driving device can move linearly along the extension direction of the blade body of the turbine blade installed on the blade fixing seat under the drive of the linear displacement driving device; The support plate is mounted on the stop driving device, and the support plate can move linearly relative to the turbine blade in a direction perpendicular to the turbine blade mounted on the blade fixing seat under the drive of the stop driving device; The rotating ruler plate is rotatably mounted on the support plate via the rotating support shaft, and the rotating ruler plate is provided with the linear stop edge on one side facing the blade leading edge and the blade trailing edge of the turbine blade mounted on the blade fixing seat, and the linear stop edge is used to stop with the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade mounted on the blade fixing seat, and the linear stop edge serves as a chord passing through the current metering detection section and tangent to the blade leading edge and the blade trailing edge; The magnetic element is mounted on the rotating support shaft, and the magnetic element rotates synchronously around the central axis of the rotating support shaft as the rotating ruler plate rotates; The magnetic field detection element is mounted on the support plate and located on one side of the magnetic element. The magnetic field detection element is used to detect the magnetic field strength and magnetic field direction generated by the magnetic element located at the current rotation angle position, and the magnetic field detection element can output an electrical signal based on the sensed magnetic field strength and magnetic field direction.

10. The aircraft engine turbine blade cross-section chord angle measurement and detection system according to claim 9, characterized in that: Also includes: An elastic force-applying device is installed on the stop drive device and is located on one side of the blade fixing seat. The support plate is installed on the elastic force-applying device. The elastic force-applying device is used to apply an elastic extrusion force to the rotating scale plate rotatably installed on the support plate, so that the straight stop edge provided on the rotating scale plate stops on the blade leading edge and the blade trailing edge of the metering detection section of the turbine blade.

11. The aircraft engine turbine blade cross-section chord angle measurement and detection system according to claim 10, characterized in that: The elastic force applying device comprises: An installation support seat is vertically installed on the stop driving device; A plurality of guide rods are provided, wherein the plurality of guide rods are horizontally connected to the mounting support seat and extend linearly toward the blade fixing seat; A support movable seat, movably mounted between the plurality of guide rods, the support movable seat is provided with a plurality of guide through holes corresponding to the plurality of guide rods, the guide rods are inserted into the guide through holes corresponding to the plurality of guide rods and pass through the guide through holes, and the support plate is vertically connected to the side of the support movable seat away from the mounting support seat; A spring is installed between the supporting movable seat and the mounting supporting seat, one end of the spring is connected to the mounting supporting seat, and the other end of the spring is connected to the supporting movable seat.

12. The aircraft engine turbine blade cross-section chord angle measurement and detection system according to claim 9, characterized in that: The linear displacement driving device comprises a first screw mechanism, and the first screw mechanism is horizontally mounted on the base; The stop drive device includes a second screw mechanism, which is horizontally mounted on a first drive block provided on the first screw mechanism and is vertically arranged relative to the first screw mechanism, and the second screw mechanism can move linearly along the extension direction of the blade body of the turbine blade installed on the blade fixing seat under the drive of the first screw mechanism, and the second screw mechanism and the first screw mechanism together constitute a cross slide mechanism; The support plate is mounted on a second driving block on the second screw mechanism, and the support plate can move linearly relative to the turbine blade in a direction perpendicular to the turbine blade mounted on the blade fixing seat under the drive of the second screw mechanism.

13. The aircraft engine turbine blade cross-section chord angle measurement and detection system according to claim 9, characterized in that: Also includes: a signal processing unit, the magnetic field detection element being electrically connected to the signal processing unit, the signal processing unit being used to perform signal processing on the electrical signal output by the magnetic field detection element to obtain a chord angle of the current measurement detection section of the turbine blade; A display unit, electrically connected to the signal processing unit, and configured to display the obtained chord angle of the current measurement detection section of the turbine blade; The control unit, the magnetic field detection element, the linear displacement drive device, the stop drive device, the signal processing unit and the display unit are electrically connected to the control unit respectively.

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