WO2021031223A1

WO2021031223A1 - Device for testing operational reliability of composite blade subjected to impact, vibration, and high-temperature excitation

Info

Publication number: WO2021031223A1
Application number: PCT/CN2019/102591
Authority: WO
Inventors: 李晖; 郭亚冲; 张紫文; 郭瑞安; 李则霖; 刘洋; 闻邦椿
Original assignee: 东北大学
Priority date: 2019-08-21
Filing date: 2019-08-26
Publication date: 2021-02-25
Also published as: CN110470446B; CN110470446A

Abstract

A device for testing operational reliability of composite blade subjected to impact, vibration, and high-temperature excitation comprising a power supply module, a measurement module, an angle-adjustable impact module (1), a holding module (2), a thermal environment module (3), a projectile recovery module (4), a basic excitation module (5), and a machine body module (6). The holding module (2) is provided in the thermal environment module (3), and is used to hold and fix a blade specimen under test. The angle-adjustable impact module (1) is used to launch a projectile to impact the blade specimen. The power supply module provides power to the angle-adjustable impact module (1). The projectile recovery module (4) is disposed in the thermal environment module (3), and is located behind the holding module (2) so as to recover projectiles. The thermal environment module (3) is provided on the machine body module (6), and provides an adjustable high-temperature test environment. The basic excitation module (5) is provided on the machine body module (6), and is used to provide a single-degree-of-freedom vibration to the holding module (2). The measurement module is used to measure a vibration amplitude, a trajectory of the projectile, and impact force. The device simulates an actual operating environment of a composite blade, and provides realistic and reliable test data of impact tests.

Description

Experimental device for service reliability of composite blade under shock, vibration and high temperature excitation

Technical field

The invention belongs to the field of impact dynamics, and relates to an experimental device for service reliability of composite blades under impact, vibration, and high temperature excitation.

Background technique

With the rapid progress and development of aerospace technology, the demand for high-performance aerospace materials has gradually increased. For a long time, the research on high-speed machinery-related materials such as aircraft has often focused on the static or low-speed characteristics of the materials, which has gradually exposed some problems , And cause some more serious consequences. For example, there were many bird strikes that first appeared in the United States at the end of the last century. With the passage of time and the rapid development of global air traffic, such events have attracted widespread attention from related scholars. As a result, the theory of shock dynamics has begun to develop rapidly, and shock dynamics experiments have also developed.

Impact dynamics experiments are designed to simulate the response behavior of materials to high-speed impacts in various environments, which requires a set of related professional experimental equipment. At present, most of the most widely used experimental equipment is Hopkinson pressure rods. This type of experimental device is used for The basic improved device has been widely produced and used. The more typical modifications such as the V-shaped modification of the entrance rod and the transmission rod head in the patent CN200810017503.4 realize the simultaneous application of compression and shear impact loads to the specimen. ; The separated Hopkinson pressure bar in patent CN201420107552.8 can adapt to test pieces of various specifications. However, the above two patents do not take any consideration into the test environment, which is often quite different from the actual situation;

The patent CN208537320U uses a vertical drop hammer structure to complete the impact excitation, and uses an energy absorbing pad based on photoelectric switch control to prevent secondary impacts in the vertical impact test. However, the impact prevention device has a complex structure and is very difficult for related components. The performance requirements are strict and the cost is high.

Patent CN201811044265.6 uses a quartz lamp radiation heating source to load the environment in a fully enclosed hot box at high temperature; Patent CN201420374580.6 uses a Hopkinson rod device covered with a heating sleeve. Both patents are designed to The aerodynamic thermal environment of the internal structure of the gas turbine is simulated. Although the above two patents consider the influence of the temperature part of the external environment, they do not consider the mechanical influence during the working process of the machine. For example, under the influence of the manufacturing process or the external environment, the turbine blades during operation will inevitably produce vibration. This should be one of the factors to be considered in the impact test.

The patent CN201710896598.0 uses a light gas gun as the impact power source. The mechanical structure can load the sample with preset axial pressure and preset impact force to simulate a variety of mechanical environments, but the patent has an impact on the thermal environment of the specimen. Without consideration, in fact, the aerodynamic thermal environment that most of the steam turbine blades and other components face during working conditions will have a significant impact on the performance of the material. High-temperature environmental impact has its unique mechanical properties, and it should be one of the indispensable factors in impact experiments.

Summary of the invention

The purpose of the present invention is to provide a service reliability experiment device for composite blades under shock, vibration, and high temperature excitation to perform service reliability experiments of blades under high temperature and vibration conditions.

The invention provides an experimental device for service reliability of composite blades under shock, vibration, and high temperature excitation, which includes a power supply module, a measurement module, an adjustable angle impact module, a clamping module, a thermal environment module, a projectile recovery module, and basic excitation Module and platform module;

The clamping module is arranged in the thermal environment module for clamping and fixing the test piece of the blade to be tested;

The adjustable angle impact module is arranged on the platform module, and is used for launching projectiles to impact the blade specimen;

The power supply module is used to provide power for the adjustable angle impact module to launch projectiles;

The projectile recovery module is placed in the thermal environment module and behind the clamping module for recovering projectiles;

The thermal environment module is arranged on the platform module to provide an adjustable high temperature test environment;

The basic excitation module is arranged on the platform module and is used to provide single degree of freedom vibration to the clamping module;

The measurement module is used to measure the vibration magnitude, projectile trajectory and impact force.

In the test device for service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, the adjustable angle impact module includes: barrel support, light gas gun, infrared sight, ball screw mechanism, hydraulic cylinder , Servo motor, barrel holder and barrel holder;

The barrel support is L-shaped and consists of a long fixing plate and a short fixing plate. The long fixing plate is arranged on the platform module; the barrel tail of the light gas gun is arranged on the short fixing plate through the barrel fixing seat The upper part can realize two degrees of freedom rotation. The front end of the light gas gun barrel is equipped with an infrared sight. The clamping piece clamps and fixes the barrel and is connected to the piston rod of the lower hydraulic cylinder through two rotating pairs. The nut of the ball screw mechanism is fixedly connected, and the servo motor drives the screw of the ball screw mechanism to rotate to drive the nut and the hydraulic cylinder to move linearly; the end of the barrel of the light air gun is equipped with an air inlet, and the end of the barrel of the light air gun is provided There is a projectile loading port.

In the test device for the service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, one end of the barrel fixing seat is connected to the short fixed plate through a thrust bearing, and the other end is connected to the barrel of the light gas gun through a rotating pair The tail rotates to connect.

In the test device for service reliability of composite blades under shock, vibration, and high temperature excitation of the present invention, the thermal environment module includes: a hot box, a plurality of heating tubes arranged on the inner wall of the hot box, and a sensor feedback circuit; The top of the box is closed by a heat-insulating upper box cover. The front side of the hot box is provided with a projectile impact entrance. The projectile impact entrance is covered with a heat-resistant and light-transmitting soft film. The two side walls of the box are equipped with heat-resistant glass observation windows. The rear wall is equipped with four axial movement conductive sleeve holes, the inner wall of the sleeve hole is provided with a plurality of balls, the bottom surface of the heat box is a funnel-shaped slope, the center of the bottom surface is provided with an opening and connected with the recovery pipeline, and an electromagnetic relay control door is provided at the opening.

In the test device for service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, the clamping module includes a vibrating table with a through hole in the center, a plurality of clamp bases are evenly arranged around the through hole, and the clamp The base is connected to the vibrating table by vibrating springs arranged at four corners. The clamp base is provided with a clamping body for fixing the blade test piece. There are four conductive rods on the vibrating table. The conductive rods extend from the axial direction on the rear wall of the heat box. After the movement conduction sleeve hole is penetrated, it is connected with the basic excitation module arranged on the back side of the hot box.

In the test device for service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, the projectile recovery module includes a support plate, a buffer box, and fine sand arranged in the buffer box, and the support plate is fixed in the hot box The inside is located behind the clamping module, the buffer box is fixed on the support plate, the front side of the buffer box is provided with a projectile receiving port and is covered with a heat-resistant soft film, the upper side of the buffer box is opened with a sand loading port, and the lower side is opened with a sand discharge door. The opening and closing is controlled by an electromagnetic relay, and the four corners of the support plate are also provided with axial movement conductive sleeve holes for the conductive rod to pass through.

In the test device for the service reliability of composite blades under shock, vibration, and high temperature excitation of the present invention, the basic excitation module includes: a guide rail slider mechanism, a vibration spring, a vibration base, a gear box, an AC speed regulating motor, and a coupling The guide rail slider mechanism is fixed on the platform module, the vibration base and the sliding block of the guide rail slider mechanism can move linearly along the guide rail, the gear box is arranged on the vibration base, and two identical gear boxes are provided in the gear box And the gears that mesh with each other, each gear is rotatably connected with the gear box through the gear shaft and the bearings provided at the two ends of the gear shaft. The AC speed control motor is fixed on the vibration base, and is connected to one of the gear shafts through a coupling to drive the two Two mutually meshing gears rotate, each gear shaft is provided with an eccentric block, and the two eccentric blocks move in opposite phases.

In the test device for the service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, the power supply module is a movable integrated high-pressure gas cylinder, which is connected to the air inlet at the tail of the light gas barrel through a hose To provide compressed gas.

In the test device for the service reliability of composite blades under impact, vibration, and high temperature excitation of the present invention, the measurement module includes a high-speed camera, a laser vibrometer and a force sensor arranged in the projectile.

The service reliability experiment device for composite blades under various shock, vibration, and high temperature excitations of the present invention can realize shock excitation, thermal excitation, and vibration excitation at the same time, more realistically simulate the actual working environment of composite blades, and provide impact experiments More real and reliable experimental data.

Description of the drawings

Fig. 1 is a structural diagram of an experimental device for service reliability of composite blades under shock, vibration, and high temperature excitation of the present invention;

Figure 2 is a structural diagram of the adjustable angle impact module;

Figure 3 is a schematic diagram of the installation of the barrel mount and the light gas gun;

Figure 4 is a structural diagram of the clamping module;

Figure 5 is an internal cross-sectional view of the hot box;

Figure 6 is a structural diagram of the basic incentive module;

In the figure: 1 adjustable angle impact module; 2 clamping module; 3 thermal environment module; 4 projectile recovery module; 5 basic excitation module; 6 body module; 7 barrel support; 8 light gas gun; 9 projectile loading port ; 10 infrared sight; 11 ball screw mechanism; 12 hydraulic cylinder; 13 servo motor; 14 barrel clamp; 15 air inlet; 16 barrel mount; 17 vibration table; 18 clamp base; 19 clamp concrete; 20 vibration spring; 21 heat insulation upper box cover; 22 hot box; 23 support plate; 24 heat-resistant glass observation window; 25 projectile impact entrance; 26 buffer sand box; 27 electromagnetic relay control door; 28 recovery pipe; 29 through hole 30 rail slider mechanism; 31 vibration spring; 32 heating tube; 33 vibration base; 34 conduction rod; 35 gear box; 36 rolling bearing; 37 eccentric block; 38 AC motor; 39 coupling; 40 gear; 41 drive shaft.

detailed description

The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

As shown in Figure 1, the service reliability experiment device for composite blades under shock, vibration, and high temperature excitation of the present invention includes: a power supply module, a measurement module, an adjustable angle impact module 1, a clamping module 2, and a thermal environment module 3. Projectile recovery module 4, basic excitation module 5 and table body module 6. The clamping module 2 is arranged in the thermal environment module 3 and is used for clamping and fixing the blade specimen to be tested; the adjustable angle impact module 1 is arranged on the table body module 6 and is used for launching projectiles to impact the blade specimen; The power supply module is used to provide power for the adjustable angle impact module 1 to launch projectiles; the projectile recovery module 4 is placed in the thermal environment module 3 and located behind the clamping module 2 for recovering projectiles; the thermal environment module 3 is set on the platform module 6 to provide an adjustable high-temperature test environment; the basic excitation module 5 is set on the platform module 6 to provide single-degree-of-freedom vibration to the clamping module 2. The measurement module is used to measure the vibration magnitude, projectile trajectory and impact force.

As shown in Figure 2, the adjustable angle impact module 1 includes: barrel support 7, light gas cannon 8, infrared sight 10, ball screw mechanism 11, hydraulic cylinder 12, servo motor 13, barrel clamping Piece 14 and barrel fixing seat 16. The barrel support 7 is L-shaped and is formed by connecting a long fixing plate and a short fixing plate. The long fixing plate is arranged on the base module 6; the barrel tail of the light gas gun 8 is set through the barrel fixing seat 16 On the short fixing plate, as shown in Figure 3, one end of the barrel fixing seat 16 is connected to the short fixing plate through a thrust bearing 161, and the other end is connected to the barrel tail of the light gas gun 8 through a rotating pair 162, which can achieve two freedoms. Degree rotation. The front end of the barrel of the light gas gun 8 is equipped with an infrared sight 10, the barrel clamp 14 clamps and fixes the barrel and is connected to the piston rod of the lower hydraulic cylinder 12 through two rotating pairs. The bottom of the hydraulic cylinder 12 is connected to the ball The nut of the screw mechanism 11 is fixedly connected, and the servo motor 13 drives the screw of the ball screw mechanism 11 to rotate to drive the nut and the hydraulic cylinder 12 to move linearly. The end of the barrel of the light-air gun 8 is provided with an air inlet 15. The end of the barrel of 8 is equipped with a projectile loading port 9.

As shown in Figure 5, the thermal environment module 3 includes: a hot box 22, a plurality of heating tubes 32 arranged on the inner wall of the hot box, and a sensor feedback circuit. The box is realized by the heating tube 32 on the inner wall of the box and an external sensor feedback circuit. Control of internal temperature. The top of the hot box 22 is closed by a heat-insulating upper box cover 21. The front side of the hot box 22 is provided with a projectile impact inlet 25. The projectile impact inlet 25 is covered with a heat-resistant and light-transmitting soft film to ensure that the infrared sight 10 can test the blades. The correct positioning of the impact point of the piece reduces the heat exchange inside and outside the heat box 22 after the projectile is incident. The two side walls of the box are provided with heat-resistant glass observation windows 24 for test records by related test recording instruments. The back wall of the hot box is equipped with four axial movement conductive sleeve holes. The inner wall of the sleeve hole is provided with a plurality of balls. The bottom surface of the hot box is a funnel-shaped slope. The center of the bottom surface is provided with an opening and is connected with the recovery pipe 28. The opening is equipped with an electromagnetic relay Electric control gate 27.

As shown in FIG. 4, the clamping module 2 includes a vibrating table 17 with a through hole 29 in the center. A plurality of clamp bases 18 are evenly arranged around the through hole 29, and the clamp base 18 passes through vibration springs 20 arranged at four corners. Connect with the vibration table 17 to realize the vibration response of the blade specimen. The clamp base 18 is provided with a clamp body 19 for fixing the blade test piece, and four conductive rods 34 are provided on the vibrating table 17, and the conductive rods 34 penetrate through the axial movement conductive sleeve holes on the rear wall of the heat box. The basic excitation module 5 arranged on the rear side of the hot box is connected. Through the axial movement of the ball on the inner wall of the conductive sleeve hole and the conductive rod 34, the movement cooperation is realized, and the friction force during the movement is reduced. The test of blade specimens under different boundary conditions can be realized by changing the number of fixtures.

As shown in FIG. 5, the projectile recovery mold 4 includes a support plate 23, a buffer box 26 and fine sand arranged in the buffer box. The supporting plate 23 is fixed in the hot box 22 and located behind the clamping module, the buffer box 26 is fixed on the supporting plate 23, and the front side of the buffer box 26 is provided with a projectile receiving port and covered with a heat-resistant soft film. The upper side of the box 26 has a sand loading port for filling sand, and the lower side has a sand discharge door which is opened and closed by an electromagnetic relay. The four corners of the support plate 23 are also provided with axial movement conductive sleeve holes for the conductive rod 34 to pass through. To reduce the friction during the movement. The projectile penetrates the blade specimen and the soft membrane and enters the sandbox to achieve buffering. After being discharged through the sand gate, it slides down to the electromagnetic relay control door 27 through the funnel-shaped slope at the bottom of the hot box, and controls the electromagnetic relay control door 27 to open and enter the recovery Pipe 28. The recovery pipe 28 is spirally curved and fixed in the internal cavity of the platform module 6. The upper mouth of the recovery pipe 28 faces the bottom of the hot box and the normally closed electromagnetic relay control door 27. The lower mouth reaches the bottom of the cavity. The bottom of the cavity is The inclined surface guides the side opening of the platform module 6 to realize the recycling and reuse of projectiles and fine sand.

As shown in FIG. 6, the basic excitation module 5 includes: a rail slider mechanism 30, a vibration spring 31, a vibration base 33, a gear box 35, an AC motor 38 and a coupling 39. The guide rail and slider mechanism 30 is fixed on the platform module, and the vibration base 33 is connected with the sliding block of the guide rail and slider mechanism 30 to move linearly along the guide rail to reduce the sliding friction during the excitation motion and improve the basic excitation module. 5 Connection stiffness with hot box 22. The gear box 35 is arranged on the vibration base 33. Two identical and meshing gears 40 are provided in the gear box 25. Each gear 40 passes through a corresponding gear shaft 41 and rolling bearings 36 provided at both ends of the gear shaft 41. Rotatingly connected with the gear box 35, the AC motor 38 is fixed on the vibration base 33, and is connected to one of the gear shafts 41 through a coupling 39 to drive the two gears 40 that mesh with each other to rotate. Each gear shaft 41 is provided with One eccentric block 37 and the movement phases of the two eccentric blocks 37 are opposite, so as to realize the single-directional vibration excitation of the blade specimen by the basic excitation module 5.

In specific implementation, the power supply module is a movable integrated high-pressure gas cylinder, which is connected to the air inlet at the tail of the light gas gun barrel through a hose to provide compressed gas. The measurement module includes: a high-speed camera, a laser vibrometer and a force sensor arranged in the projectile.

The process of using the composite blade service reliability test device under the shock, vibration, and high temperature excitation of the present invention is as follows:

Step 1: After correctly assembling each experimental device, select the impact position and boundary conditions of the blade test piece, and fix the blade test piece to the vibration table through the clamp;

Step 2: Adjust and fix the posture of the light gas gun barrel through the hydraulic cylinder and servo motor, so that the infrared sight can be clearly aligned with the impact position;

Step 3: Load the projectiles, connect the light gas gun and the gas cylinder; choose whether to start the hot box temperature control and load basic excitation; arrange high-speed cameras and laser vibrometers and other experimental recording instruments, and make other preparations;

Step 4: Launch the projectile and start recording the experimental data. The specific recording process is as follows:

Use the force sensor in the projectile to measure the contact impact force to study the impedance; use the high-speed camera to observe the blade's displacement and damage mode; use the laser vibrometer to measure the blade's displacement or speed, output the time domain response, and then get the frequency response function To analyze the system parameters such as the natural frequency and damping ratio of each blade;

Step 5: After the experimental record is over, the projectile and fine sand in the projectile recovery mold are recovered and reused through the control system.

Step 6: Turn off the experimental equipment and analyze the experimental data.

The above are only the preferred embodiments of the present invention and are not used to limit the idea of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the present invention Within the scope of protection.

Claims

An experimental device for service reliability of composite blades under shock, vibration, and high temperature excitation, which is characterized by: power supply module, measurement module, adjustable angle impact module, clamping module, thermal environment module, projectile recovery module, and basic excitation module And platform module;

The clamping module is arranged in the thermal environment module for clamping and fixing the test piece of the blade to be tested;

The adjustable angle impact module is arranged on the platform module, and is used for launching projectiles to impact the blade specimen;

The power supply module is used to provide power for the adjustable angle impact module to launch projectiles;

The projectile recovery module is placed in the thermal environment module and behind the clamping module for recovering projectiles;

The thermal environment module is arranged on the platform module to provide an adjustable high temperature test environment;

The basic excitation module is arranged on the platform module and is used to provide single degree of freedom vibration to the clamping module;

The measurement module is used to measure the vibration magnitude, projectile trajectory and impact force.
The experimental device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 1, wherein the adjustable angle impact module includes: barrel support, light gas gun, infrared sight, ball Screw mechanism, hydraulic cylinder, servo motor, barrel clamp and barrel fixing seat;

The barrel support is L-shaped and consists of a long fixing plate and a short fixing plate. The long fixing plate is arranged on the platform module; the barrel tail of the light gas gun is arranged on the short fixing plate through the barrel fixing seat The upper part can realize two degrees of freedom rotation. The front end of the light gas gun barrel is equipped with an infrared sight. The clamping piece clamps and fixes the barrel and is connected to the piston rod of the lower hydraulic cylinder through two rotating pairs. The nut of the ball screw mechanism is fixedly connected, and the servo motor drives the screw of the ball screw mechanism to rotate to drive the nut and the hydraulic cylinder to move linearly; the end of the barrel of the light air gun is equipped with an air inlet, and the end of the barrel of the light air gun is provided There is a projectile loading port.
The test device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 2, wherein one end of the barrel fixing seat is connected to the short fixed plate through a thrust bearing, and the other end is connected to the short fixed plate through a rotating pair. The barrel tail of the light gas gun is connected by rotation.
The test device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 1, wherein the thermal environment module includes a hot box, a plurality of heating tubes and sensors arranged on the inner wall of the hot box Feedback circuit; the top of the hot box is closed by a heat-insulating upper box cover, the front side of the hot box is provided with a projectile impact entrance, the projectile impact entrance is covered with a heat-resistant light-transmitting soft film, and the two side walls of the box body are equipped with heat-resistant glass Observation window, the back wall of the hot box is equipped with four axial movement conduction sleeve holes, the inner wall of the sleeve hole is provided with a plurality of balls, the bottom surface of the hot box is a funnel-shaped inclined surface, the center of the bottom surface is provided with an opening and connected with the recovery pipeline, and the opening is provided Electromagnetic relay control door.
The test device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 4, wherein the clamping module includes a vibrating table with a through hole in the center, and a plurality of evenly arranged around the through hole The clamp base is connected to the vibrating table through vibration springs arranged at four corners. The clamp base is provided with a clamping body for fixing the blade specimen. The vibrating table is provided with four conductive rods. The conductive rods are from the heat box After the axial movement conduction sleeve hole on the rear wall is penetrated, it is connected with the basic excitation module arranged on the rear side of the hot box.
The test device for service reliability of composite blades under shock, vibration, and high temperature excitation according to claim 4, wherein the projectile recovery module includes a support plate, a buffer box, and fine sand arranged in the buffer box. The support plate is fixed in the hot box behind the clamping module. The buffer box is fixed on the support plate. The front side of the buffer box is provided with a projectile receiving port and is covered with a heat-resistant soft film. The sand gate is opened on the side and the opening and closing is controlled by an electromagnetic relay. The four corners of the support plate are also provided with axial movement conductive sleeve holes for the conductive rod to pass through.
The experimental device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 1, wherein the basic excitation module includes: a guide rail slider mechanism, a vibration spring, a vibration base, a gear box, and an AC regulator Speed motor and coupling; the guide rail slider mechanism is fixed on the platform module, the vibration base is connected with the slider of the guide rail slider mechanism to move linearly along the guide rail, the gear box is arranged on the vibration base, inside the gear box There are two identical and mutually meshing gears. Each gear is rotatably connected to the gear box through a gear shaft and bearings at both ends of the gear shaft. The AC speed regulating motor is fixed on the vibration base and is connected to one of them through a coupling. The gear shafts are connected to drive two gears that mesh with each other to rotate. Each gear shaft is provided with an eccentric block, and the two eccentric blocks move in opposite phases.
The test device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 1, wherein the power supply module is a movable integrated high-pressure gas cylinder, which is connected to a light gas gun barrel through a hose The air inlet at the rear is connected to provide compressed gas.
The experimental device for service reliability of composite blades under impact, vibration, and high temperature excitation according to claim 1, wherein the measurement module includes a high-speed camera, a laser vibrometer, and a force sensor arranged in the projectile.