CN-121977845-A - Experimental device and method for simulating rubbing effect of rotor blade of aero-engine

Abstract

The invention relates to the technical field of aero-engine experiments, in particular to an experimental device and method for simulating the rubbing effect of a rotor blade of an aero-engine. According to the scheme, the electromagnetic driving principle based on the electromagnetic induction law and the Lenz law is adopted, the control of the friction force can be accurately realized by changing the current, different friction modes such as single points, multiple points, partial arc sections, even whole circles and the like can be conveniently simulated aiming at each blade unit, and the complex working conditions such as friction coefficient change and the like are adopted.

Inventors

• WANG QINGSHAN
• HU SHUANGWEI
• ZHANG HAIBIAO
• FANG CHUNJIAO

Assignees

• 中南大学

Dates

Publication Date

20260505

Application Date

20260407

Claims (10)

1. 1. The experimental device for simulating the rubbing effect of the rotor blade of the aero-engine is characterized by comprising a supporting seat, a rotating shaft, a simulation fan, an additional rotor, a coupler, a driving motor, a rubbing simulation assembly and a testing assembly; The support seat is used for integrally supporting, the rotating shaft is in rotary connection with the support seat through a bearing, the simulation fan is connected with the rotating shaft and keeps synchronous rotation, the simulation fan is used for simulating aero-engine blades, the additional rotor is connected with the rotating shaft and keeps synchronous rotation, the additional rotor is used for simulating aero-engine rotors, and the rotating shaft is connected with an output shaft of the driving motor through the coupler; The friction simulation assembly comprises a friction mounting seat and an electromagnetic coil arranged in the friction mounting seat, the friction mounting seat is provided with a groove, the groove corresponds to the blade unit, a magnetic induction wire generated after the electromagnetic coil is electrified passes through the groove, a ferromagnetic body is further arranged in the friction mounting seat, and the electromagnetic coil is sequentially wound on the ferromagnetic body; The test assembly is used for detecting and collecting test data.
2. 2. An experimental device for simulating the friction effect of a rotor blade of an aircraft engine according to claim 1, wherein the ferromagnetic body is configured in a U-shape and is distributed along the cross-sectional profile of the friction mount.
3. 3. An experimental device for simulating the friction effect of a rotor blade of an aircraft engine according to claim 1, wherein an insulating material is disposed between the metal strip and the blade unit to insulate the metal strip from the blade unit.
4. 4. An experimental device for simulating friction effect of a rotor blade of an aircraft engine according to claim 1, wherein the metal strips and the mounting grooves are distributed along the radial direction of the simulated fan.
5. 5. The experimental device for simulating friction effect of aircraft engine rotor blades according to claim 1, wherein the blade unit is further provided with a circuit slot, the circuit slot is divided into two sections and is respectively communicated with two ends of the mounting slot, the circuit slot is used for arranging a first conductive wire, and the first conductive wire is used for transmitting electric energy of a direct-current power supply to the metal strip.
6. 6. The experimental device for simulating the friction effect of a rotor blade of an aircraft engine according to claim 5, wherein the simulated fan further comprises a rotor and a stator, the rotor is arranged inside a fan hub of the simulated fan and is fixedly connected with the fan hub, the rotor is simultaneously fixedly connected with the rotating shaft, the rotor is provided with a plurality of rotor electrode grooves, rotor electrodes are arranged in the rotor electrode grooves, and the rotor electrode grooves are communicated with the line grooves so as to connect the rotor electrodes with the first conductive wires; The rotary shaft is arranged to be of a hollow structure, the stator is arranged in the rotary shaft, the stator is provided with a plurality of stator electrode grooves, the stator electrode grooves are arranged in one-to-one correspondence with the rotor electrode grooves, stator electrodes are arranged in the stator electrode grooves, the stator is arranged to be of a hollow structure, a direct current power supply is arranged in the stator, a through hole leading to the inside of the stator is formed in the stator electrode grooves, a second conductive wire is connected between the stator electrode and the direct current power supply, the second conductive wire penetrates through the through hole, and the stator electrode and the rotor electrode are made of conductive materials.
7. 7. The experimental device for simulating friction effect of an aircraft engine rotor blade according to claim 6, wherein the rotor electrode grooves respectively communicated with the two circuit grooves of each blade unit are symmetrical with respect to the center point of the circular section of the rotor, the stator electrode positioned at the center point of the circular section and in the phase of 0-180 degrees is connected with the positive electrode of the direct current power supply, and the stator electrode positioned at the phase of 180-360 degrees is connected with the negative electrode of the direct current power supply.
8. 8. The experimental device for simulating friction effect of a rotor blade of an aircraft engine of claim 6, wherein the conductive material of the stator electrode and the rotor electrode is a graphite material.
9. 9. The experimental device for simulating friction effect of an aircraft engine rotor blade according to claim 1, wherein the testing assembly comprises a plurality of sensors and a data acquisition module, the sensors are used for detecting data at preset positions, the data acquisition module is electrically connected with the sensors, and the data acquisition module is used for acquiring data detected by the sensors.
10. 10. An experimental method for simulating the rubbing effect of a rotor blade of an aero-engine, which adopts the experimental device for simulating the rubbing effect of the rotor blade of the aero-engine as claimed in any one of claims 1 to 9, and is characterized by comprising the following steps: S1, installing a supporting seat, a rotating shaft, a simulation fan, an additional rotor, a coupling, a driving motor and a rub-impact simulation assembly, and installing and debugging a test assembly in place; S2, starting magnetization of the rub-impact simulation assembly, so that a magnetic field is filled between the rub-impact simulation assembly and the simulation fan, and the current of the electromagnetic coil is a preset value; s3, starting the driving motor, and after the rotation speed of the driving motor is stable, switching on the metal strip and the direct current power supply to enable direct current to be generated in a closed loop of the metal strip; S4, adjusting the current of the electromagnetic coil or the current of the metal strip to realize accurate adjustment of friction force; s5, recording data, completing experiments, sequentially closing the driving motor, the direct current power supply and the rub-impact simulation assembly, and disassembling related parts.

Description

Experimental device and method for simulating rubbing effect of rotor blade of aero-engine Technical Field The invention relates to the technical field of aero-engine experiments, in particular to an experimental device and method for simulating a rub-impact effect of a rotor blade of an aero-engine. Background The aero-engine is used as a 'bright bead on a crown' in the modern industry, and the performance of a core component, namely a rotor system, directly determines the working reliability, the vibration noise level, the service life and the like of the engine. In the engineering practice process, the unbalance amount of the rotor can be gradually accumulated under the restriction of the service cycle, the extreme environment and the maintenance condition of the rotor, so that the unbalance response of a rotor system can be gradually increased. When the dynamic response amplitude exceeds the rotor-stator clearance value, rub-impact faults occur between the rotor blades and the casing, and the performance, reliability and safety of the aeroengine are seriously affected. Therefore, in order to ensure the vibration safety of the aero-engine, it is necessary to develop the research on the rub-impact response characteristics of the rotor blades of the aero-engine under the working conditions. In the published data, the viscous damping effect is achieved by applying a lubricant to the rotor friction surface to simulate the stiction force. Although this method is very simple, the viscosity of the lubricant is limited, and the viscosity of the lubricant changes with deterioration when the lubricant is exposed to air, and the generated viscosity is unstable. Meanwhile, the Chinese patent application with publication number of CN110361177A discloses a rub-impact experimental device, rub-impact simulation is composed of a frame, a spring, a rub-impact head, a double-head threaded rod and the like, and the adjustment of rub-impact rigidity is realized by adjusting the length and the material of the spring. However, the rubbing head is driven mechanically, so that the rubbing head is easy to retract under the reaction force, and the rubbing force is not durable. In addition, the rubbing head position is adjusted in a mechanical mode, so that the rubbing force cannot be accurately controlled, and the high-frequency dynamic rubbing is difficult to deal with. Disclosure of Invention Aiming at the defects in the background technology, the invention provides a scheme for simulating the rub-impact effect of the rotor blade of the aero-engine based on electromagnetic driving so as to accurately realize the control of rub-impact force and achieve the advantages of no contact, no abrasion, no noise, smooth rub-impact force, adjustability and simple maintenance. In order to achieve the aim, the invention provides an experimental device for simulating the rubbing effect of a rotor blade of an aero-engine, which comprises a supporting seat, a rotating shaft, a simulation fan, an additional rotor, a coupling, a driving motor, a rubbing simulation assembly and a testing assembly, wherein the supporting seat is arranged on the supporting seat; The support seat is used for integrally supporting, the rotating shaft is in rotary connection with the support seat through a bearing, the simulation fan is connected with the rotating shaft and keeps synchronous rotation, the simulation fan is used for simulating aero-engine blades, the additional rotor is connected with the rotating shaft and keeps synchronous rotation, the additional rotor is used for simulating aero-engine rotors, and the rotating shaft is connected with an output shaft of the driving motor through the coupler; The friction simulation assembly comprises a friction mounting seat and an electromagnetic coil arranged in the friction mounting seat, the friction mounting seat is provided with a groove, the groove corresponds to the blade unit, a magnetic induction wire generated after the electromagnetic coil is electrified passes through the groove, a ferromagnetic body is further arranged in the friction mounting seat, and the electromagnetic coil is sequentially wound on the ferromagnetic body; The test assembly is used for detecting and collecting test data. Further, the ferromagnetic body is arranged in a U shape, and the ferromagnetic body is distributed along the cross-sectional profile of the rubbing mounting seat. Further, an insulating material is provided between the metal strip and the blade unit to insulate between the metal strip and the blade unit. Further, the metal strips and the mounting grooves are distributed along the radial direction of the simulated fan. Further, a circuit groove is further formed in the blade unit, the circuit groove is divided into two sections and is respectively communicated with two ends of the mounting groove, the circuit groove is used for arranging a first conductive wire, and the first conductive wire is used for transmitting