An experimental device and method for simulating rubbing effect of an aero-engine rotor blade

Abstract

The present application relates to the technical field of aero-engine experiment, and particularly relates to an experimental device and method for simulating rubbing effect of aero-engine rotor blades, which comprises a supporting seat, a rotating shaft, a simulated fan, an additional rotor, a coupling, a driving motor, a rubbing simulation assembly and a test assembly. The scheme adopts an electromagnetic driving principle based on the electromagnetic induction law and the Lenz law, can accurately realize control of rubbing force by changing the current size, and can conveniently simulate different rubbing modes such as single-point, multi-point, local arc segment and even whole circle for each blade unit, and complex working conditions such as friction coefficient change. Compared with the prior art, the scheme has the advantages of no contact, no actual wear, no noise, smooth and adjustable rubbing force and simple maintenance, and improves the experimental efficiency, reliability and accuracy of the simulation of the rubbing effect of the aero-engine rotor blades.

Description

Technical Field

[0001] This invention relates to the field of aero-engine experimental technology, and in particular to an experimental apparatus and method for simulating the rubbing effect of aero-engine rotor blades. Background Technology

[0002] As the "crown jewel" of modern industry, the performance of the rotor system—the core component of an aero-engine—directly determines its operational reliability, vibration and noise levels, and service life. In engineering practice, constrained by the rotor's service life, extreme environments, and maintenance conditions, the rotor's inherent imbalance gradually accumulates, leading to a progressively larger imbalance response in the rotor system. When the dynamic response amplitude exceeds the rotor-stator clearance, rubbing failure occurs between the rotor blades and the casing, severely impacting the aero-engine's performance, reliability, and safety. Therefore, to ensure the vibration safety of aero-engines, it is necessary to conduct research on the rubbing response characteristics of aero-engine rotor blades under operating conditions.

[0003] Publicly available information describes a method to simulate rotor-to-rotor static friction force by applying lubricant to the rotor's friction surfaces to achieve a viscous damping effect. While this method is simple, the lubricant's viscosity is limited, and its viscosity changes with deterioration when exposed to air, resulting in unstable viscous forces. Meanwhile, Chinese invention patent application CN110361177A discloses a friction simulation device consisting of a frame, springs, a friction head, and a double-threaded rod. The friction stiffness is adjusted by modifying the spring's length and material. However, mechanically driving the friction head can lead to retraction under reaction force, resulting in a short-lived friction force. Furthermore, mechanically adjusting the friction head's position makes precise control of the friction force difficult, hindering the handling of high-frequency dynamic friction. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of the aforementioned background technology by providing a solution based on electromagnetic drive to simulate the rubbing effect of aero-engine rotor blades, so as to accurately control the rubbing force and achieve the advantages of no contact, no wear, no noise, smooth and adjustable rubbing force, and simple maintenance.

[0005] To achieve the above objectives, the present invention provides an experimental apparatus for simulating the rubbing effect of rotor blades of an aero-engine, including a support base, a rotating shaft, a simulated fan, an additional rotor, a coupling, a drive motor, a rubbing simulation component, and a test component.

[0006] The support base is used for overall support. The rotating shaft is rotatably connected to the support base via bearings. The simulated fan is connected to the rotating shaft and rotates synchronously. The simulated fan is used to simulate an aero-engine blade. The additional rotor is connected to the rotating shaft and rotates synchronously. The additional rotor is used to simulate an aero-engine rotor. The rotating shaft is connected to the output shaft of the drive motor via the coupling.

[0007] The simulated fan has multiple blade units, each blade unit has a mounting slot, and a metal strip is placed in the mounting slot. The two ends of the metal strip are connected to a DC power supply to form a closed loop. The collision simulation component includes a collision mounting base and an electromagnetic coil disposed inside the collision mounting base. The collision mounting base has a groove, which corresponds to the blade unit. The magnetic field lines generated by the electromagnetic coil after being energized pass through the groove. A ferromagnetic body is also disposed inside the collision mounting base, and the electromagnetic coil is wound sequentially around the ferromagnetic body.

[0008] The testing component is used to detect and collect test data.

[0009] Furthermore, the ferromagnetic material is configured in a U-shape, and the ferromagnetic material is distributed along the cross-sectional contour of the rubbing mounting base.

[0010] Furthermore, an insulating material is provided between the metal strip and the blade unit to ensure insulation between them.

[0011] Furthermore, both the metal strip and the mounting groove are radially distributed along the simulated fan.

[0012] Furthermore, the blade unit is also provided with a wiring groove, which is divided into two sections and connected to both ends of the mounting groove. The wiring groove is used to arrange a first conductive wire, which is used to transfer electrical energy from the DC power supply to the metal strip.

[0013] Furthermore, the simulated fan also includes a rotor and a stator; the rotor is arranged inside the hub of the simulated fan and fixedly connected to the hub, and the rotor is also fixedly connected to the rotating shaft. The rotor is provided with a plurality of rotor electrode slots, and rotor electrodes are provided in the rotor electrode slots. The rotor electrode slots are connected to the circuit slots so that the rotor electrodes are connected to the first conductive wire.

[0014] The rotating shaft is configured as a hollow structure, and the stator is disposed inside the rotating shaft. The stator has multiple stator electrode slots, which correspond one-to-one with the rotor electrode slots. Stator electrodes are disposed within the stator electrode slots. The stator is configured as a hollow structure, and the DC power supply is disposed inside the stator. Through holes leading to the interior of the stator are opened in the stator electrode slots. A second conductive wire is connected between the stator electrode and the DC power supply, and the second conductive wire passes through the through holes. Both the stator electrode and the rotor electrode are made of conductive material.

[0015] Furthermore, the rotor electrode slots connected to the two line slots of each blade unit are symmetrical about the center point of the circular cross-section of the rotor. The stator electrode located at the 0°~180° phase of the center point of the circular cross-section is connected to the positive terminal of the DC power supply, and the stator electrode located at the 180°~360° phase is connected to the negative terminal of the DC power supply.

[0016] Furthermore, the conductive material of the stator electrode and the rotor electrode is graphite.

[0017] Furthermore, the testing component includes multiple sensors and a data acquisition module. The sensors are installed at preset locations to detect data, and the data acquisition module is electrically connected to the sensors to acquire the data detected by the sensors.

[0018] This invention also provides an experimental method for simulating the rubbing effect of aero-engine rotor blades, using the experimental apparatus for simulating the rubbing effect of aero-engine rotor blades as described above, including the following steps:

[0019] S1, Install the support base, rotating shaft, simulated fan, additional rotor, coupling, drive motor, and rubbing simulation components, and install and debug the test components in place;

[0020] S2, start the magnetization of the rubbing simulation component, so that the rubbing simulation component and the simulated fan are filled with a magnetic field, and the current of the electromagnetic coil is the preset value;

[0021] S3, start the drive motor. After the drive motor speed stabilizes, connect the metal strip to the DC power supply to generate DC current in the closed circuit of the metal strip.

[0022] S4, adjust the current of the electromagnetic coil or the current of the metal strip to achieve precise adjustment of the friction force;

[0023] S5, record data, complete the experiment, turn off the drive motor, DC power supply and collision simulation component in sequence, and disassemble the relevant parts.

[0024] The above-described solution of the present invention has the following beneficial effects:

[0025] The experimental apparatus and method for simulating the rubbing effect of aero-engine rotor blades provided by this invention, through the setting of support base, rotating shaft, simulated fan, additional rotor, coupling, drive motor, etc., and the setting of rubbing simulation components, adopts the electromagnetic drive principle based on the law of electromagnetic induction and Lenz's law. The rubbing force can be precisely controlled by changing the current magnitude. Moreover, it can easily simulate different rubbing modes such as single point, multi-point, local arc segment, or even the whole circle for each blade unit, as well as complex working conditions such as changes in friction coefficient. Compared with the existing technology, it has the advantages of non-contact, no actual wear, no noise, smooth and adjustable rubbing force, and simple maintenance, which improves the experimental efficiency, reliability and accuracy of simulating the rubbing effect of aero-engine rotor blades.

[0026] Other beneficial effects of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0028] Figure 2 This is a schematic diagram of the collision simulation component of the present invention;

[0029] Figure 3 This is a schematic diagram of the magnetic field lines generated by the rubbing simulation component of the present invention;

[0030] Figure 4 This is a schematic diagram showing the rotation of the metal strip of the simulated fan relative to the rubbing simulation component of the present invention.

[0031] Figure 5 This is a schematic diagram of the simulated fan of the present invention;

[0032] Figure 6 This is a schematic diagram of the rotor of the present invention;

[0033] Figure 7 This is a schematic diagram of the stator of the present invention;

[0034] Figure 8 This is a schematic diagram of the rotor electrode and stator electrode of the present invention.

[0035] [Explanation of Labels in the Attached Image]

[0036] 10-Support base; 20-Rotating shaft; 30-Simulated fan; 31-Metal strip; 32-Mounting slot; 33-Wire slot; 34-Rotor; 35-Stator; 36-Rotor electrode slot; 37-Rotor electrode; 38-Stator electrode slot; 39-Stator electrode; 40-Additional rotor; 50-Coupling; 60-Drive motor; 70-Collision simulation component; 71-Collision mounting base; 72-Electromagnetic coil; 73-Groove; 74-Ferromagnetic material; 80-Test component; 81-Sensor; 82-Data acquisition module. Detailed Implementation

[0037] To make the technical problems, solutions, and advantages of this invention clearer, a detailed description will be provided below with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention. Furthermore, the technical features involved in the different embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0038] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a locking connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0040] In existing technologies, electromagnetic drive is a non-contact loading method. When a metal conductor moves relative to a magnetic field, the conductor cuts the magnetic field lines. According to the law of electromagnetic induction, an induced electromotive force is generated inside the conductor. This induced electromotive force drives eddy currents inside the conductor. According to Lenz's law, the magnetic field generated by the eddy currents always opposes the relative motion that causes them. This "opposition" manifests as a braking force, the direction of which is opposite to the direction of motion. Based on this, embodiments of the present invention provide an experimental device for simulating the rubbing effect of aero-engine rotor blades. Based on the linear equations of the laws of electromagnetic induction and Lenz's law, the rubbing force is precisely controlled by changing the magnitude of the current. The device controls the amplitude, phase, waveform, and position of the current through software programming, and can easily simulate different rubbing modes such as single-point, multi-point, local arc segments, and full circles, as well as complex working conditions such as changes in the coefficient of friction.

[0041] Based on this, Figure 1 As shown, the experimental setup for simulating the rubbing effect of aero-engine rotor blades includes a support base 10, a rotating shaft 20, a simulated fan 30, an additional rotor 40, a coupling 50, a drive motor 60, a rubbing simulation component 70, and a test component 80. The support base 10 is mounted on the experimental platform to provide overall support for the other components, ensuring stability during the experiment. The rotating shaft 20 is rotatably connected to the support base 10 via bearings, for example... Figure 1 The intermediate support 10 has two support points, each with a bearing. The fixed part of the bearing is fixedly connected to the support 10 (bolt connection, interference fit, etc.), and the rotating part of the bearing is fixedly connected to the rotating shaft 20 (key, interference fit, etc.) to ensure stable rotation of the rotating shaft 20 during the experiment. A simulated fan 30 is connected to the first end of the rotating shaft 20 and rotates synchronously with it to simulate an aero-engine blade. An additional rotor 40 is mounted on the rotating shaft 20, located between the two support points in this embodiment, and rotates synchronously with the rotating shaft 20 to simulate an aero-engine rotor. The second end of the rotating shaft 20 is connected to the output shaft of a drive motor 60 via a coupling 50, so that the drive motor 60 drives the rotating shaft 20 to rotate, thereby driving the simulated fan 30, the additional rotor 40, etc., to simulate the rotation of the rotor system.

[0042] At the same time, such as Figure 2 , Figure 3As shown, in this embodiment, the rubbing simulation component 70 includes a rubbing mounting base 71 and an electromagnetic coil 72 disposed inside the rubbing mounting base 71. The rubbing mounting base 71 has a groove 73, which is used by the simulated fan 30 blades to pass through sequentially during the experiment. The magnetic field lines generated by the electromagnetic coil 72 after being energized pass through the groove 73, so that when the simulated fan 30 rotates, each blade will sequentially cut the magnetic field lines. In a preferred embodiment, the rubbing mounting base 71 also contains a ferromagnetic body 74, which is distributed along the cross-sectional contour of the rubbing mounting base 71, i.e., the ferromagnetic body 74 is U-shaped. The electromagnetic coil 72 is sequentially wound around the ferromagnetic body 74 to amplify the magnetic field lines generated by the electromagnetic coil 72 through the ferromagnetic body 74, thereby improving the accuracy of the rubbing effect.

[0043] At the same time, such as Figure 4 As shown, each blade unit of the simulated fan 30 has a mounting groove 32, and a metal strip 31 is embedded and fixed in the mounting groove 32. The metal strip 31 is also separated from the blade unit itself by insulating material to prevent leakage accidents caused by current being transmitted from the blade unit to other components or the experimental platform after current is applied to the metal strip 31. The two ends of the metal strip 31 are connected to a DC power supply to form a closed loop, and the metal strip 31 and the mounting groove 32 are distributed radially along the simulated fan 30. Therefore, when the simulated fan 30 rotates, the metal strip 31, which is energized by DC current in each blade unit, cuts the magnetic field lines in the groove 73, generating an Ampere force. According to the left-hand rule for determining the direction of the Ampere force... Figure 4 When the simulated fan 30 rotates clockwise, the current inside the metal strip 31 flows radially outward, while the magnetic field flows inward along the plane of the paper. At this time, an Ampere force opposite to the rotation direction of the simulated fan 30 can be obtained. This Ampere force has a hindering effect on the rotation of the simulated fan 30. Therefore, the friction (resistance) force generated by the rubbing phenomenon can be simulated.

[0044] In one specific implementation, simultaneously as Figure 5 As shown, the mounting groove 32 is located at the center of the blade unit. A wiring groove 33 is also provided on the blade unit. The wiring groove 33 is divided into two sections and connects to both ends of the mounting groove 32. The wiring groove 33 is used to arrange the first conductive wire to energize the metal strip 31 within the mounting groove 32. Since there are a large number of blade units, it is relatively difficult to arrange the power supply inside the hub of the simulated fan 30. Therefore, in this embodiment, the simulated fan 30 also includes a rotor 34 and a stator 35. Figure 6 , Figure 7As shown. The rotor 34 is arranged inside the fan hub and fixedly connected to the fan hub. The rotor 34 is also fixedly connected to the rotating shaft 20 so as to rotate synchronously with the rotating shaft 20. The inner surface of the rotor 34 is provided with a plurality of rotor electrode slots 36. The rotor electrode slots 36 are provided with rotor electrodes 37. At the same time, the rotor electrode slots 36 are connected to the wiring slots 33 so that the rotor electrodes 37 can be connected to the first conductive wire.

[0045] Correspondingly, the rotating shaft 20 is hollow, and the stator 35 is located inside the rotating shaft 20. Multiple stator electrode slots 38 are provided on the outer surface of the stator 35, with each stator electrode slot 38 corresponding to a rotor electrode slot 36. Stator electrodes 39 are housed within the stator electrode slots 38. The stator 35 itself is also hollow, with its interior used to house a DC power supply (battery), etc. Through holes are formed within the stator electrode slots 38, leading to the interior of the stator 35, allowing the second conductive wire connecting the stator electrode 39 to pass directly through the through holes into the interior of the stator 35 and connect to the DC power supply, thus powering the stator electrode 39. When the stator electrode 39 contacts the rotor electrode 37, it can transfer electrical energy to the rotor electrode 37, ultimately powering the metal strip 31. This method effectively prevents the conductive wire from exiting through the rotor 34, thus avoiding the risk of the conductive wire becoming entangled and causing an electrical hazard when the rotor 34 rotates.

[0046] It is understandable that the two ends of the metal strip 31 need to be connected to the positive and negative terminals respectively. For the stator electrode 39, it may be connected to either the positive or negative terminal of the DC power supply; therefore, the rotor electrode 37 in contact with it is also correspondingly either positive or negative. Based on this, the two line slots 33 need to be connected to different rotor electrode slots 36, one rotor electrode slot 36 corresponding to the positive terminal of the DC power supply, and the other rotor electrode slot 36 corresponding to the negative terminal of the DC power supply. As a preferred embodiment, in this embodiment, the rotor electrode slots 36 connected to the two line slots 33 of each blade unit are symmetrical about the center point of the circular cross-section of the rotor 34, i.e., the phase difference relative to the center point is 180 degrees. For the stator electrode 39, stator electrodes 39 with a phase of 0°~180° are connected to the positive terminal of the DC power supply, and stator electrodes 39 with a phase of 180°~360° are connected to the negative terminal of the DC power supply, such as... Figure 8As shown. When rotor 34 rotates, because there are enough electrodes distributed between stator 35 and rotor 34, and rotor electrode 37 and stator electrode 39 are almost always in contact, positive electricity is always connected to the positive terminal of metal strip 31, and negative electricity is always connected to the negative terminal of metal strip 31. During this period, the blade unit can obtain a stable friction force when passing through the magnetic field. When rotor 34 has rotated half a revolution, the positive terminal of metal strip 31 is connected to the negative terminal of DC power supply, and the negative terminal of metal strip 31 is connected to the positive terminal of DC power supply. At this time, the current direction of metal strip 31 is reversed. However, the blade unit has already received friction force at the previous moment, and at this moment it has left the magnetic field region. Therefore, even if the current direction is reversed, it will not be subjected to a reverse Ampere force. All blade units can be guaranteed to receive friction force in the same direction when passing through the magnetic field region during rotation.

[0047] In a preferred embodiment, both the rotor electrode 37 and the stator electrode 39 are made of graphite material. This serves two purposes: firstly, it acts as a conductor to conduct electricity; secondly, it provides lubrication for the rotation between the rotor 34 and the stator 35. It should be noted that a bearing is also provided between the stator 35 and the rotating shaft 20 to ensure that the stator 35 remains stationary (or rotates only at a low speed) when the rotating shaft 20 rotates.

[0048] The force exerted on the metal strip 31 in the magnetic field is derived theoretically below. Considering the combination of the electromagnetic coil 72 and the ferromagnetic body 74, the magnetic field strength at each point in space is... The magnetic field strength that can be generated by electromagnetic coil 72 (current source generates current) The magnetic field strength generated by the magnetized ferromagnetic material 74 To express it as the sum:

[0049] ;

[0050] According to the Biot-Savart law:

[0051] ;

[0052] We can obtain:

[0053] ;

[0054] in, Indicates current density, Represents a position vector. This represents the magnitude of the position vector, and

[0055] ;

[0056] Represents the coordinates of a point in space. Represents the coordinates of the origin in space. , They represent respectively to and Solving the differential operation, i.e. , Indicates magnetization intensity. Represents spatial volume, Representing the volume element, we can obtain the following by applying vector operations:

[0057] ;

[0058] Thus scalar magnetic potential for:

[0059] ;

[0060] From the vector analysis identity, we have:

[0061] ;

[0062] Therefore, the scalar magnetic potential can be further written as:

[0063] ;

[0064] According to Gauss's theorem, rewriting the first term on the right-hand side of the above equation in terms of area fractions yields:

[0065] ;

[0066] in Indicates surface, This represents a surface element vector, with its direction being the outward normal direction. , For the unit normal vector, by Substituting, we get:

[0067] ;

[0068] in, Represents surface magnetic charge density, Represents the volume magnetic charge density in a homogeneous ferromagnetic material. Since it is 0, we can obtain:

[0069] ;

[0070] To solve for the surface magnetic charge density The value was determined by dividing the surface of the ferromagnetic material 74 into equal parts using the finite element method. Small noodles , face The magnetic field strength at the center point is:

[0071] ;

[0072] in, Indicates the first Individual The surface magnetic charge density, and the first Individual elements and elements Not the same one, Indicates the first Individual The magnetic field strength generated by electromagnetic coil 72. Interacting both sides of the above equation with the normal unit vector... Perform a dot product operation to obtain the normal component. The relation is:

[0073] ;

[0074] Due to the magnetic field strength generated by the electromagnetic coil 72 and other surface elements Surface magnetic charge in surface element The normal magnetic field strength generated above is continuous on both sides of the interface, and the surface element... The magnetic field strength generated by the surface magnetic charge itself is equal in magnitude and opposite in direction on both sides of the interface, so the above equation can be transformed into:

[0075] ;

[0076] in, Represents the magnetic susceptibility. Indicates the first Surface magnetic charge density of the surface element, Indicates the first The normal vector of each face element. Indicates that the electromagnetic coil 72 is in the first The normal magnetic field strength generated by each facet element.

[0077] Solve for the surface magnetic charge density in the above equation. Then, by substituting the result into the formula for scalar magnetic potential, the magnetic field strength of the ferromagnetic body 74 at any point in space can be calculated. The magnetic field strength generated by the electromagnetic coil 72 itself is negligible, so the magnetic field strength at any point in space can be obtained.

[0078] Let the projected length of metal strip 31 in the direction perpendicular to the magnetic field lines be... After the metal strips 31 form a closed loop, DC current is input into the closed loop. According to the definition of Ampere force, the magnitude of the Ampere force on the metal strip 31 is... for:

[0079] ;

[0080] in, The magnitude of the magnetic field strength at any point in space is represented by the Ampere force. This refers to the friction force. Therefore, after the friction simulation component 70 is installed, the magnetic field strength at any point in space can be adjusted by regulating the current of the electromagnetic coil 72, and simultaneously, or by adjusting the current of the metal strip 31, the magnitude of the friction force can be adjusted to simulate the effect of different friction forces on the rotor blades of an aero-engine. Obviously, compared with the imprecise problem of mechanical adjustment of the friction gap, this method can be more precise and maintain through the adjustment of the magnetic field and current, thus making the experiment more stable. At the same time, since each blade unit is independently equipped with a metal strip 31 and connected to a DC power supply, the energization of different metal strips 31 can be easily controlled, thereby simulating different friction modes such as single point, multi-point, local arc segment, or even the entire circle, further improving the realism and specificity of the experimental device.

[0081] In a preferred embodiment, the collision simulation component 70 is further equipped with a magnetic field control circuit, which consists of a rectifier circuit, a control circuit, and a protection circuit. The rectifier circuit consists of a transformer and a bridge rectifier to output 110V DC power. The control circuit is used for magnetization and demagnetization control. During magnetization, the electromagnetic coil 72 is energized; after the experiment is completed, the DC power on the electromagnetic coil 72 is cut off. Since dust or metal particles may be present in the experimental site, the electromagnetic coil 72 needs to be demagnetized. The control circuit controls the electromagnetic coil 72 to be energized in reverse to demagnetize it. The protection device consists of a resistor, a capacitor, and an undervoltage relay. The resistor and capacitor are used because when the collision simulation component is turned on, the electromagnetic coil 72 stores a large amount of magnetic field energy. At the moment the power is disconnected, a large self-induced electromotive force is generated at both ends of the electromagnetic coil 72, which may damage the electromagnetic coil 72 and other electrical components. Therefore, a discharge circuit is formed by the resistor and capacitor. Taking advantage of the characteristic that the voltage across the capacitor cannot change abruptly, the voltage change across the electromagnetic coil 72 tends to be slow, while the resistor dissipates the electromagnetic energy.

[0082] In this embodiment, the test assembly 80 includes multiple sensors 81 and a data acquisition module 82. The sensors 81 are installed at designated locations to collect relevant data. For example, the sensor 81 is an eddy current sensor 81, used to measure the circumferential disturbance effect of the additional rotor 40 during the rubbing process, simulating a fan 30, etc. The probe of the eddy current sensor 81 contains a coil carrying a high-frequency alternating current. Once the distance between the surface of the additional rotor 40 and the probe changes, the intensity and distribution of the eddy currents change accordingly, resulting in a precise change in the impedance (or inductance, voltage) of the coil. By linearly converting the change in electrical quantity into a distance value, the disturbance effect of the additional rotor 40 during the rubbing process is accurately measured. The data acquisition module 82 is electrically connected to each sensor 81 to collect the relevant test data detected by the sensors 81 for subsequent analysis.

[0083] Based on the same inventive concept, this embodiment also provides an experimental method for simulating the rubbing effect of aero-engine rotor blades, including the following steps:

[0084] S1, install support 10, rotating shaft 20, simulated fan 30, additional rotor 40, coupling 50, drive motor 60, and rubbing simulation component 70; install sensor 81 of test component 80 in the designated position; connect sensor 81 to data acquisition module 82; and check whether the data acquisition channel can acquire data.

[0085] S2, start the magnetization of the rubbing simulation component 70, so that the rubbing simulation component 70 and the simulated fan 30 are filled with a magnetic field, and the current of the electromagnetic coil 72 is the preset value;

[0086] S3, start the drive motor 60. After the speed of the drive motor 60 stabilizes, connect the metal strip 31 to the DC power supply to generate DC current in the closed circuit of the metal strip 31.

[0087] S4, adjust the current of the electromagnetic coil 72 or the current of the metal strip 31 to achieve precise adjustment of the friction force;

[0088] S5, record data, complete the experiment, turn off the drive motor 60, DC power supply and collision simulation component 70 in sequence, and disassemble the relevant components.

[0089] The experimental method for simulating the rubbing effect of aero-engine rotor blades provided in this embodiment has the same inventive concept and beneficial effects as the aforementioned experimental device for simulating the rubbing effect of aero-engine rotor blades, and will not be repeated here.

[0090] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0091] The above embodiments are merely illustrative of several implementation methods of this application, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. An experimental apparatus for simulating the rubbing effect of aero-engine rotor blades, characterized in that, It includes a support base, rotating shaft, simulated fan, additional rotor, coupling, drive motor, collision simulation assembly, and test assembly; The support base is used for overall support. The rotating shaft is rotatably connected to the support base via bearings. The simulated fan is connected to the rotating shaft and rotates synchronously. The simulated fan is used to simulate an aero-engine blade. The additional rotor is connected to the rotating shaft and rotates synchronously. The additional rotor is used to simulate an aero-engine rotor. The rotating shaft is connected to the output shaft of the drive motor via the coupling. The simulated fan has multiple blade units, each blade unit has a mounting slot, and a metal strip is placed in the mounting slot. The two ends of the metal strip are connected to a DC power supply to form a closed loop. The collision simulation component includes a collision mounting base and an electromagnetic coil disposed inside the collision mounting base. The collision mounting base has a groove, which corresponds to the blade unit. The magnetic field lines generated by the electromagnetic coil after being energized pass through the groove. A ferromagnetic body is also disposed inside the collision mounting base, and the electromagnetic coil is wound sequentially around the ferromagnetic body. The testing component is used to detect and collect test data.

2. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 1, characterized in that, The ferromagnetic material is U-shaped and distributed along the cross-sectional contour of the rubbing mounting base.

3. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 1, characterized in that, An insulating material is provided between the metal strip and the blade unit to ensure insulation between them.

4. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 1, characterized in that, The metal strip and the mounting groove are both distributed radially along the simulated fan.

5. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 1, characterized in that, The blade unit is also provided with a wiring groove, which is divided into two sections and connected to both ends of the mounting groove. The wiring groove is used to arrange a first conductive wire, which is used to transfer electrical energy from the DC power supply to the metal strip.

6. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 5, characterized in that, The simulated fan also includes a rotor and a stator; the rotor is arranged inside the hub of the simulated fan and fixedly connected to the hub, and the rotor is also fixedly connected to the rotating shaft. The rotor is provided with a plurality of rotor electrode slots, and rotor electrodes are provided in the rotor electrode slots. The rotor electrode slots are connected to the circuit slots so that the rotor electrodes are connected to the first conductive wire. The rotating shaft is configured as a hollow structure, and the stator is disposed inside the rotating shaft. The stator has multiple stator electrode slots, which correspond one-to-one with the rotor electrode slots. Stator electrodes are disposed within the stator electrode slots. The stator is configured as a hollow structure, and the DC power supply is disposed inside the stator. Through holes leading to the interior of the stator are opened in the stator electrode slots. A second conductive wire is connected between the stator electrode and the DC power supply, and the second conductive wire passes through the through holes. Both the stator electrode and the rotor electrode are made of conductive material.

7. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 6, characterized in that, The rotor electrode slots connected by the two line slots of each blade unit are symmetrical about the center point of the circular cross-section of the rotor. The stator electrode located at the 0°~180° phase of the center point of the circular cross-section is connected to the positive terminal of the DC power supply, and the stator electrode located at the 180°~360° phase is connected to the negative terminal of the DC power supply.

8. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 6, characterized in that, The conductive material of the stator electrode and the rotor electrode is graphite.

9. The experimental apparatus for simulating the rubbing effect of aero-engine rotor blades according to claim 1, characterized in that, The test assembly includes multiple sensors and a data acquisition module. The sensors are installed at preset locations to detect data, and the data acquisition module is electrically connected to the sensors to acquire the data detected by the sensors.

10. An experimental method for simulating the rubbing effect of aero-engine rotor blades, comprising an experimental apparatus for simulating the rubbing effect of aero-engine rotor blades as described in any one of claims 1-9, characterized in that, Includes the following steps: S1, Install the support base, rotating shaft, simulated fan, additional rotor, coupling, drive motor, and rubbing simulation components, and install and debug the test components in place; S2, start the magnetization of the rubbing simulation component, so that the rubbing simulation component and the simulated fan are filled with a magnetic field, and the current of the electromagnetic coil is the preset value; S3, start the drive motor. After the drive motor speed stabilizes, connect the metal strip to the DC power supply to generate DC current in the closed circuit of the metal strip. S4, adjust the current of the electromagnetic coil or the current of the metal strip to achieve precise adjustment of the friction force; S5, record data, complete the experiment, turn off the drive motor, DC power supply and collision simulation component in sequence, and disassemble the relevant parts.

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