Multi-sensor fusion aero-engine blade vibration testing device

Abstract

The utility model discloses a multi-sensor fusion aero-engine blade vibration testing device, which comprises a plate group and a motor assembly, and is characterized in that the motor assembly comprises a servo motor, motor square tube racks, a motor supporting transverse plate and a motor transverse plate supporting frame, the servo motor is fixedly connected between at least two symmetrical motor square tube racks, and the motor transverse plate supporting frame is fixedly connected with the motor square tube racks; a motor square tube rack is fastened on an optical aluminum bread bottom plate through corner fittings, a motor supporting transverse plate is fastened with the motor square tube rack through a motor transverse plate supporting frame, and a servo motor is hung, fastened and installed on a supporting plate. A blade assembly; a displacement assembly; the sensing assembly comprises a microwave sensor, a laser sensor and a photoelectric sensor; the energy assembly comprises an experimental power box; according to the invention, three sensors with different principles are used as the detection sensors, so that the vibration testing precision of the turbine blade is greatly improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of testing, and in particular relates to a multi-sensor fusion aero-engine blade vibration testing device. Background Art

[0002] Nowadays, in recent years, aircraft engines are increasingly developing towards high load, high efficiency and high reliability. High load causes the engine blades to bear high centrifugal load, aerodynamic load and vibration alternating load during operation, which is very prone to failure. Flutter is a form of blade vibration, and many blade breakage accidents are caused by flutter. Flutter is an abnormal state that needs to be avoided during the operation of turbine machinery such as aircraft engines and gas turbines. This phenomenon will cause high-frequency vibration of the blades and even cause blade breakage in a short time. Once blade flutter occurs, the large and violent vibration will cause the blades to break in a short time, which is extremely destructive. As the engine develops towards high performance, the blades become thinner, the stage pressure ratio increases, and the unsteady aerodynamic load increases, resulting in more prominent blade vibration and flutter problems, which seriously threaten the operation safety and reliability of the equipment. Using a simulation test device to detect vibration signals is the most commonly used research and analysis method. Therefore, the development of efficient, scientific and intelligent mechanical systems has important engineering and practical significance for the early aircraft engine blade vibration fault monitoring and diagnosis technology.

[0003] Although some aircraft engine blade vibration test devices have appeared, the existing aircraft engine blade vibration test devices still have some shortcomings. On the one hand, they cannot simulate the impact of aircraft engine blade defects and blade size on vibration very well. On the other hand, the motion state of aircraft engine blades cannot be simulated very well, which is mainly manifested in the following aspects: 1. Vibration conditions of aircraft engine blades of different shapes; 2. Deformation and vibration of aircraft engine blades at different speeds; 3. Single sensor is not accurate enough in measuring blade vibration state; 4. Since the actual internal conditions of aircraft engines are complex and costly, how to optimize the aircraft engine blade vibration test device is the key technical problem that this application project is about to solve.

[0004] In view of this, it is necessary to develop a multi-sensor fusion aero-engine blade vibration test device to solve the above problems. Utility Model Content

[0005] In view of this, the purpose of the utility model is to provide a multi-sensor fusion aircraft engine blade vibration test device to solve the problem of single simulated aircraft engine blade vibration test and inaccurate measurement data.

[0006] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0007] A multi-sensor fusion aero-engine blade vibration test device, comprising:

[0008] A plate assembly, which includes an optical aluminum bread bottom plate, an acrylic baffle plate perpendicular to the bottom plate, a top acrylic cover plate, and an aluminum profile square tube frame for connecting and reinforcing the bottom plate and the baffle plate;

[0009] A motor assembly, comprising a servo motor, a motor square tube frame, a motor support cross plate, and a motor cross plate support frame, wherein the servo motor is fastened between at least two symmetrical motor square tube frames, the motor square tube frame is fastened to the optical aluminum bread bottom plate through angle pieces, and the motor support cross plate is fastened to the motor square tube frame through the motor cross plate support frame;

[0010] The blade assembly is arranged and installed above the motor, and the turbine blades are fastened by flanges and bolts and nuts, and the flange is fastened to the rotating shaft of the servo motor by set screws; it is convenient to replace turbine blades with different blade morphologies;

[0011] A displacement assembly, which includes an electrically controlled displacement platform, which is fastened to the optical aluminum breadboard by screws and is controlled by a motor controller, and a three-axis displacement platform is fastened to the electrically controlled displacement platform;

[0012] An energy component, which includes an experimental power supply box;

[0013] The sensing component includes a microwave sensor, a laser sensor and a photoelectric sensor. The microwave sensor is fastened to the three-axis displacement platform through a microwave sensor bracket, the laser sensor is fastened to the laser sensor bracket, and the laser sensor bracket is fastened to the optical aluminum panel bottom plate through screws; the photoelectric sensor is fixed to the end connecting rod of the three-axis four-link support frame, and the angle can be adjusted by a knob shaft;

[0014] Among them, the three-axis displacement platform is adjusted to fine-tune the position of the microwave sensor, the motor controller is used to control the smooth and precise movement of the electric-controlled displacement platform, and the height of the laser sensor bracket and the angle backplane connected are adjusted to ensure that the laser sensor works within a reliable working range.

[0015] Furthermore, the three-axis displacement platform is fixedly connected to a movable seat at one end of the electric-controlled displacement platform, and the three-axis displacement platform is adjusted through a rotating axis to include micro displacements up and down, front and back, and left and right;

[0016] The laser sensor bracket has a slide groove in the vertical direction, which can realize up and down movement, and the three-axis four-link support frame can realize free movement within a certain space range.

[0017] Furthermore, the microwave sensor bracket is fastened to the microwave sensor by bolts and nuts, and has multiple height adjustment options, and the bracket is fastened to the three-axis displacement platform by screws.

[0018] Furthermore, the laser sensor is connected to the laser sensor bracket via an angle back plate, and the angle back plate can adjust the angle measured by the laser sensor so that it works in a stable test range.

[0019] Furthermore, the three-axis four-link support frame is hinged to achieve free adjustment of its spatial position. The base of the three-axis four-link support frame has sufficient mass, the photoelectric sensor is fastened to one end of the three-axis four-link, and the three axes have knob axes that can adjust the angle.

[0020] Furthermore, the servo motor is suspended and fastened to the motor supporting cross plate through bolts and nuts.

[0021] Furthermore, the experimental power supply box outputs multiple channels of stabilized DC power supplies that do not interfere with each other.

[0022] Furthermore, the angled back plate allows a certain inclination angle to exist between the laser sensor and the horizontal center of the turbine blade, so as to better test the blade vibration data.

[0023] Furthermore, the sensing assembly includes a microwave sensor, a laser sensor and a photoelectric sensor, and the signal transmitting ends of the three are always horizontally aligned with the center of the turbine blade.

[0024] Furthermore, the plate group includes an optical aluminum bread base plate, an aluminum profile square tube frame, a front baffle, a rear baffle, a side baffle and a bottom cover plate, and each baffle has a U-shaped groove on the edge; the aluminum profile square tube frame, the frame and the base plate are fastened with screws, the frame and the baffle are fastened with blind rivets, and the cover plate is not connected to the frame.

[0025] Furthermore, the rear baffle and the front baffle each have a plurality of through holes with a certain diameter.

[0026] Furthermore, the side baffles are perpendicular to the front and rear baffles and are connected with plastic corner pieces.

[0027] Furthermore, the size of the cover plate is slightly larger than the size of the frame.

[0028] Furthermore, the servo motor is vertically suspended and fastened on the motor support cross plate, and is located at the center of the two motor square tube frames.

[0029] Furthermore, the axis of the screw rod of the electric-controlled displacement platform is perpendicular to the axis of the motor support plate, and the foot of the vertical rod falls on the center of the servo motor shaft.

[0030] Furthermore, the three-axis displacement platform and the electric-controlled displacement platform are horizontally fastened by screws, and the ground of the three-axis displacement platform is parallel to the optical aluminum breadboard bottom plate.

[0031] Compared with the prior art, the beneficial effects of the utility model are: 1. The detection sensors in the present application use three sensors with different principles, which greatly improve the accuracy of turbine blade vibration testing; 2. The present application adopts a replaceable aircraft engine blade module, which can simulate the vibration of turbine blades of different shapes during operation; 3. The servo motor in the present application is vertically suspended on the support plate, which effectively avoids the influence of gravity on the vibration parameters of the blade's own weight; 4. The motor in the present application uses a servo motor, which can simulate turbine blade vibration failures at different speeds, expanding the scope of use; 5. The plate group in the present application can replace baffles of different thicknesses and materials, which effectively ensures the safety during the experiment and makes the device safe and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0033] Figure 1 It is a structural schematic diagram of a multi-sensor fusion aero-engine blade vibration testing device proposed according to one embodiment of the utility model;

[0034] Figure 2 This is a front view of a multi-sensor fusion aero-engine blade vibration testing device proposed according to one embodiment of the utility model;

[0035] Figure 3 The present invention is a top view of an aero-engine blade vibration testing device with multi-sensor fusion proposed according to one embodiment of the present invention.

[0036] Reference numerals and component descriptions in the drawings:

[0037] 1-Acrylic baffle; 2-Aluminum profile square tube rack; 3-Optical aluminum bread bottom plate; 4-Experimental power box; 5-Motor controller; 6-Electric control displacement platform; 7-Laser controller; 8-Laser sensor bracket; 9-Angle back plate; 10-Laser sensor; 11-Angle piece; 12-Motor square tube rack; 13-Motor support cross plate bracket; 14-Motor support cross plate; 15-Flange; 16-Turbine blades; 17-Photoelectric sensor; 18-Three-axis four-link support frame; 19-Three-axis displacement platform; 20-Microwave sensor bracket; 21-Microwave sensor; 22-Servo motor; 23-Set screws. DETAILED DESCRIPTION

[0038] The technical solution of the utility model will be clearly and completely described below through specific implementation methods. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of them. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0039] refer to Figures 1 to 3 A multi-sensor fusion aviation engine blade vibration test device includes a plate group, a motor assembly, a blade assembly, a displacement assembly, a sensor assembly and an energy assembly.

[0040] The plate group includes acrylic plates 1 of several sizes, an aluminum square tube frame 2 and an optical aluminum bread bottom plate 3. The acrylic baffle 1 includes side baffles, front and rear baffles, which are assembled and installed perpendicular to the optical aluminum bread bottom plate 3. The top view shows a rectangle. The right angles between the plates are connected by plastic corner pieces. The plates are fastened to the aluminum square tube frame by blind rivets. The top cover can cover the entire test device horizontally and seamlessly.

[0041] Preferably, the optical aluminum bread bottom plate 3 has threaded holes at a certain interval, and the aluminum profile square tube frame 2 is fastened to the optical aluminum bread bottom plate 3 by screws. At the same time, the optical aluminum bread bottom plate 3 is easy to install on a horizontal test bench, which improves the overall experimental test accuracy.

[0042] The remaining components including the motor component, the blade component, the displacement component, and the sensor component are all placed on the optical aluminum bread bottom plate 3. The energy component is adjacent to the optical aluminum bread bottom plate 3. The motor component and the blade component are arranged and installed at the center position of the optical aluminum bread bottom plate 3. The motor component and the blade component include a motor controller 5, an angle piece 11, a motor square tube frame 12, a motor cross plate support frame 13, a motor support cross plate 14, a flange 15, a turbine blade 16, a servo motor 22, and a set screw 23. The motor square tube frame 12 is vertically installed on both sides around the center position. Each motor square tube frame 12 is fastened by four angle pieces 11 and screws, and is strictly kept vertical to the optical aluminum bread bottom plate 3. The connecting line between the two is horizontal to one side of the optical aluminum bread bottom plate 3. The motor cross plate support frame 13 is fastened to the motor square tube frame 12, and the motor cross plate support frames 13 on both sides are kept at the same height. The motor support cross plate 14 is installed on the motor cross plate support frame 13 and is kept horizontal to the optical aluminum bread bottom plate 3. Then install the servo motor 22 and hang it between the motor support horizontal plate 14 and the optical aluminum bread bottom plate 3. The turbine blade 16 is connected to the servo motor 22 through the flange 15. The turbine blade 16 and the flange 15 are fastened with bolts and nuts, and the servo motor 22 and the flange 15 are fastened with set screws 23. There is a groove in the motor square tube frame 12, so that the height of the motor horizontal plate support frame 14 can be adjusted.

[0043] Specifically, the motor controller 5 can control the operating speed of the servo motor 22. In order to make the overall structure more stable and suitable for higher rotation speeds, the distance between the bottom of the servo motor 22 and the optical aluminum bread base 3 is as small as possible within a reasonable and safe range, which helps to lower the center of gravity of the system and improve the stability of the system.

[0044] As mentioned above, the displacement assembly includes an electrically controlled displacement platform 6, a three-axis displacement platform 19, a three-axis four-link support frame 18 and a laser sensor bracket 8. During installation, the center of the turbine blade 16 is used as the standard, and the displacement platform where the microwave sensor 21 is located is directly opposite the center of the turbine blade 16 to avoid affecting the test accuracy of the microwave sensor. When the laser sensor 10 and the photoelectric sensor 17 are installed, they cannot block the direction of the transmitting end of the microwave sensor 21.

[0045] As mentioned above, the energy component includes an experimental power supply box 4, which supplies power to the sensor components including the laser sensor 10, the microwave sensor 21 and the photoelectric sensor 17 through multiple non-interfering DC voltage outputs, and sets a protective limiting current on each path to protect the sensor components to a certain extent.

[0046] During the test, the turbine blade 16 is simply moved to adjust the displacement assembly to ensure that the sensor works in a safe and appropriate initial position. After ensuring that all components are safe, the motor controller 5 parameters are adjusted to output a speed range of 0-3000r / min. The motor controller 5 controls the servo motor 22 to output different speeds, simulating the operation of the turbine blade 16 under different conditions, and detecting its vibration through multiple sensors.

[0047] It is worth noting that the turbine blades 16 and the sensor groups (10, 17, 21) can be selected and replaced, so that the vibration detection of different aircraft engine blades can be simulated and their vibration parameters can be measured in multiple ways.

[0048] Working steps:

[0049] 1. Connect and install each component in sequence;

[0050] 2. Before the experiment of simulating the vibration of the aircraft engine blade, it is necessary to calibrate the centering and balance of the test device, check whether the parts are loose, whether the test device is placed stably, and whether the interfaces are reliable. Before starting the motor controller 5 to drive the servo motor 22, the protective cover of the test bench must be covered to ensure safety;

[0051] 3. The sensor is operated in a suitable test range by adjusting the electric control displacement platform 6, the three-axis displacement platform 19 and the microwave sensor bracket 20; the laser sensor 10 is operated in a suitable and stable test range by adjusting the angle back plate 9 and the laser sensor bracket 8; and the photoelectric sensor 17 is operated in a suitable and stable test range by adjusting the bolts and nuts on the adjustment shaft of the three-axis four-two connecting rod bracket 18;

[0052] 4. Turn on the motor controller 5 and drive the servo motor 22 to rotate the turbine blades 16, and obtain vibration signals of the turbine blades 16 through multiple sensors.

[0053] The above description of the disclosed embodiments enables professionals in the field to implement or use the utility model. Various modifications to these embodiments will be apparent to professionals in the field, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the utility model. Therefore, the utility model will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features disclosed herein.

Claims

1. A multi-sensor fusion aero-engine blade vibration test device, characterized in that: include A plate assembly, comprising an optical aluminum bread bottom plate (3), an acrylic baffle plate (1) perpendicular to the bottom plate, an acrylic cover plate on the top, and an aluminum profile square tube frame (2) for connecting and reinforcing the bottom plate and the baffle plate; A motor assembly, comprising a servo motor (22), a motor square tube frame (12), a motor support cross plate (14), and a motor cross plate support frame (13), wherein the servo motor (22) is fastened between at least two symmetrical motor square tube frames (12), the motor square tube frame (12) is fastened to an optical aluminum bread bottom plate (3) through an angle piece (11), and the motor support cross plate (14) is fastened to the motor square tube frame (12) through the motor cross plate support frame (13); A blade assembly is arranged and installed above the motor, and includes a turbine blade (16) which is fastened by a flange (15) and bolts and nuts, and the flange (15) is fastened to the rotating shaft of the servo motor (22) by a set screw (23); It is convenient to replace turbine blades (16) with different blade shapes; A displacement assembly, comprising an electrically controlled displacement platform (6), which is fastened to the optical aluminum breadboard bottom plate (3) by screws and is controlled by a motor controller (5); a three-axis displacement platform (19) is fastened to the electrically controlled displacement platform (6); An energy component, comprising an experimental power supply box (4); The sensing component comprises a microwave sensor (21), a laser sensor (10) and a photoelectric sensor (17); the microwave sensor (21) is fastened to a three-axis displacement platform (19) via a microwave sensor bracket (20); the laser sensor (10) is fastened to a laser sensor bracket (8); and the laser sensor bracket (8) is fastened to an optical aluminum panel bottom plate (3) via screws; the photoelectric sensor (17) is fixed to the end connecting rod of a three-axis four-link support frame (18); and the angle can be adjusted via a knob shaft; The three-axis displacement platform (19) is adjusted to fine-tune the position of the microwave sensor (21), a motor controller (5) is used to control the electric-controlled displacement platform (6) to move smoothly and accurately, and the height of the laser sensor bracket (8) and the connected angle back plate (9) are adjusted to ensure that the laser sensor (10) works within a reliable working range.

2. The multi-sensor fusion aero-engine blade vibration test device according to claim 1, characterized in that: The three-axis displacement platform (19) is fixedly connected to a movable seat at one end of the electric-controlled displacement platform (6), and the three-axis displacement platform (19) is adjusted through a rotating axis to include micro displacements in up and down, front and back, and left and right directions; The laser sensor bracket (8) has a slide groove in the vertical direction, which can realize up and down movement, and the three-axis four-link support frame (18) can realize free movement within a certain spatial range.

3. The multi-sensor fusion aero-engine blade vibration test device according to claim 1, characterized in that: The microwave sensor bracket (20) and the microwave sensor (21) are fastened by bolts and nuts and have multiple height adjustment options. The bracket is fastened to the three-axis displacement platform (19) by screws.

4. The multi-sensor fusion aero-engine blade vibration test device according to claim 2, characterized in that: The laser sensor (10) is connected to the laser sensor bracket (8) via an angle back plate (9), and the angle back plate (9) can adjust the angle measured by the laser sensor (10) so that it works in a stable test range.

5. The multi-sensor fusion aero-engine blade vibration test device according to claim 2, characterized in that: The three-axis four-link support frame (18) is hingedly connected to achieve free adjustment of its spatial position.

6. The multi-sensor fusion aero-engine blade vibration test device according to claim 1, characterized in that: The servo motor (22) is suspended and fastened to the motor supporting horizontal plate (14) via bolts and nuts.

7. The multi-sensor fusion aero-engine blade vibration test device according to claim 1, characterized in that: The experimental power supply box (4) outputs multiple channels of voltage-stabilized direct current power supplies that do not interfere with each other.

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