Device and method for testing rotation friction torque of valve clack of high-temperature aviation pneumatic butterfly valve

Abstract

The invention belongs to the field of tribology application, and particularly designs a device and a method for testing the rotating friction torque of a valve clack of a high-temperature aviation pneumatic butterfly valve, and the testing method is used for simulating the friction torque of the valve clack of the high-temperature aviation pneumatic butterfly valve under different pressures, different temperatures, different flows and different opening angles. Accurate measured data are provided for a high-temperature aviation pneumatic butterfly valve clack rotation friction torque model. The testing device comprises a servo motor, a speed reducer, a torque sensor, a photoelectric encoder, a heating box and a controller. Wherein the servo motor provides power for the whole testing device and is used for working of the valve clack assembly; the speed reducer is used for speed reduction transmission and torque transmission between the servo motor and the air entraining valve assembly. The torque sensor is used for testing the torque of the bleed valve assembly in the rotating process; the photoelectric encoder is used for recording the rotating position of the valve assembly; the controller is used for data acquisition and control of the test system. Through the test method provided by the invention, decoupling of the friction torque and the aerodynamic torque of the valve clack in a high-temperature variable flow field can be realized, online test data of the friction torque can be obtained, and the problem of lack of an online test method for the friction torque of the valve clack is solved.

Description

Technical Field

[0001] The invention discloses a testing device and method for the rotation friction torque of a high-temperature aviation pneumatic butterfly valve disc, belonging to the field of tribology application. Background Art

[0002] The high-temperature aviation pneumatic butterfly valve is a key regulating device of the aircraft air source system. It is installed at the front end of the aircraft air source system and has the function of regulating and shutting off the system bleed air pressure. Once a high-temperature aviation pneumatic butterfly valve fails, it will cause the air source system to fail, which will in turn cause the aircraft air conditioning system and anti-icing system to fail to work properly, affecting the safety of the aircraft. The high-temperature aviation pneumatic butterfly valve is one of the key components to ensure the flight safety of the aircraft and protect life safety.

[0003] The disc assembly is the mechanism for high-temperature aviation air butterfly valve to perform pressure regulation and shutoff. When working, the disc is subjected to high-temperature and high-pressure air, and is coupled with aerodynamic torque and disc friction torque. All friction torques of the disc have an important influence on the adjustment accuracy and switching characteristics of the butterfly valve. Therefore, it is of great significance to measure the friction torque of the disc. Due to its coupling with the flow field, as the disc opening changes, the flow field changes accordingly, and under the action of high temperature and high pressure, the test is more complicated and difficult to test directly. It is urgent to propose a disc friction torque test method. Summary of the invention

[0004] The main purpose of the present invention is to provide a testing method and device suitable for the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc, so as to simulate and test the friction torque of a high-temperature aviation pneumatic butterfly valve disc under different working conditions, and solve the problem of online testing method for friction torque of a valve disc without a valve disc.

[0005] Technical solution: In order to achieve the above-mentioned purpose, the present invention proposes a test device for the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation, which comprises: a servo motor, a reducer, a torque sensor, a photoelectric encoder, a heating box, and a controller;

[0006] Among them, the servo motor provides power for the entire test device and is used for the operation of the valve flap assembly; the reducer is used for speed reduction transmission and torque transmission between the servo motor and the air intake valve assembly; the torque sensor is used to test the torque during the rotation of the air intake valve assembly; the photoelectric encoder is used to record the rotation position of the valve assembly; and the controller is used for test system data acquisition and control.

[0007] Furthermore, the valve flap assembly includes a channel, a valve flap and a valve flap shaft; the valve flap is fixed on the valve flap shaft, and the valve flap is arranged in the channel, there is a certain angle between the valve flap shaft and the channel cross section, and the channel flow control is achieved by controlling the rotation of the valve flap shaft.

[0008] Furthermore, the valve flap and the channel form a friction pair, and the friction torque is generated by the relative rotation between the valve flap and the channel. At the same time, the valve flap is subjected to the high temperature and high pressure flow field during operation, and is further subjected to the aerodynamic torque.

[0009] Furthermore, the high temperature box is used to simulate the ambient temperature to which the valve flap assembly is subjected, or as a heat insulation device to prevent the influence of high temperature on the test equipment.

[0010] Furthermore, during the test, the valve flap assembly is passed through a channel with high temperature and high pressure air to simulate actual working conditions, and the air regulation and shutoff control are achieved by changing the valve flap angle.

[0011] Furthermore, the valve flap opening angle is measured by the photoelectric encoder.

[0012] The purpose of the present invention is to test the friction torque between the valve disc and the channel. The present invention can realize the friction torque test at different temperatures, gas pressures, valve disc rotation angles and rotation speeds. At the same time, the present invention also proposes a test method for the friction torque of the valve disc rotation of a high-temperature aviation pneumatic butterfly valve. The test method adopts the test device as described above. During the test, the channel is connected to the high-temperature and high-pressure air, and the servo motor and the reducer are controlled by the controller to rotate the valve disc to a specific angle and fix it. After the gas flow field inside the channel is stable, the valve disc is rotated clockwise and counterclockwise by the same small angle. At this time, the torque sensor measures torques T1 and T2 respectively; when the valve disc rotates, its torque contribution comes from the aerodynamic torque T p (torque generated by the force of high temperature and high pressure gas acting on the valve disc) and friction torque T f (Friction torque generated by relative motion in the contact area between the valve disc and the channel); It is considered here that ① when the valve disc rotates clockwise and counterclockwise at a certain angle, the change in friction torque can be ignored. Since the direction of friction torque is opposite to the direction of motion, the friction torque has the same magnitude but opposite direction; ② the valve disc moves at a small angle, close to quasi-steady state. Near a certain angle, the change in aerodynamic torque can be ignored and the direction does not change. The aerodynamic torque T at this point can be calculated by the following formulas: p and friction torque T f :

[0013] T p =(T1+T2) / 2

[0014] T f =(T1-T2) / 2

[0015] When the pressure and temperature of the incoming air change, the friction torque under the corresponding temperature and pressure conditions can be tested. By changing the rotation speed and position of the valve disc, the friction torque of the valve disc at different speeds and positions can be obtained.

[0016] Beneficial technical effects: The present invention designs a testing method and device suitable for the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc, so as to simulate and test the friction torque of a high-temperature aviation pneumatic butterfly valve disc under different working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the structure of the testing device of the present invention. Figure 2 Schematic diagram of the valve disc assembly structure.

[0018] Among them, 1-valve disc assembly, 2-servo motor, 3-reducer, 4-torque sensor, 5-photoelectric encoder, 6-heating box, 7-coupling, 8-controller; 11-channel, 12-valve disc, 13-valve disc shaft. DETAILED DESCRIPTION

[0019] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] Embodiment 1:

[0021] The present invention provides a method and device for testing the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation, so as to simulate and test the friction torque of high-temperature aviation pneumatic butterfly valve disc under different working conditions and provide online measured data for the friction torque model. Figure 1 A specifically designed test device for the friction torque of a high-temperature aviation pneumatic butterfly valve disc rotation includes: a disc assembly 1, a servo motor 2, a reducer 3, a torque sensor 4, a photoelectric encoder 5, an insulation box 6, a coupling 7, and a controller 8; the disc assembly 1 includes a channel 11, a disc 12 and a disc shaft 13, the disc 12 is fixed on the disc shaft 13, and the disc 12 is arranged in the channel 11, and the channel flow control is realized by controlling the rotation of the disc shaft; there is a certain inclination angle between the disc shaft and the channel.

[0022] The servo motor drives the bleed air valve disc to rotate forward and reversely, and the torque sensor measures the forward and reverse torque under different working conditions. The friction torque of the bleed air valve disc can be obtained by calculation. The specific steps include:

[0023] (1) The controller is connected to the servo motor, the torque sensor and the photoelectric encoder, and controls the rotation angle of the valve disc 12 by controlling the rotation speed of the servo motor, and simultaneously collects the position signal and torque signal of the valve disc assembly;

[0024] (2) One end of the reducer is connected to the motor shaft, and the other end is connected to the torque sensor through a coupling;

[0025] (3) The torque sensor is connected to the valve disc assembly shaft through a coupling;

[0026] (4) A photoelectric encoder is connected to the other end of the valve disc assembly shaft to detect the rotation angle of the valve disc 12;

[0027] (5) The servo motor and valve disc assembly are fixed on the test bench to ensure that the servo motor, valve disc assembly and coupling are coaxial;

[0028] (6) The coupling adopts a flexible coupling to compensate for the angular deviation of the servo motor, torque sensor and valve disc shaft 13 different axis products to avoid the introduction of measurement errors;

[0029] (7) The ambient temperature of the valve disc assembly is controlled by an insulation box to simulate the working environment temperature, while isolating the high-temperature air to prevent heat radiation to the test device. On the other hand, the insulation box is controlled to open a hole at the shaft connection to reduce the leakage of hot air along the shaft direction and protect the test equipment;

[0030] (8) Connect the valve disc assembly to a high-temperature and high-pressure gas source and adjust the temperature and gas pressure to the values ​​under different working conditions.

[0031] Let it stand for 10 minutes to ensure that the temperature in the channel 11 is uniform;

[0032] (9) The controller controls the servo motor to rotate the valve disc to a certain angle, maintains it for 10 seconds to stabilize the flow field in channel 11, and records the position parameters of the photoelectric encoder at this time;

[0033] (10) Using a servo motor to control the valve disc 12 to rotate 1° clockwise based on step (3), and recording the rotation speed v of the valve disc 12 and the torque value T1 collected by the torque sensor during the process;

[0034] (11) Using a servo motor to control the valve disc to return to the position of step (3), after standing for 10 seconds, rotate 1° counterclockwise at the same speed v as step (4), and record the torque value T2 collected by the torque sensor during this process;

[0035] (12) The friction torque of the bleed air valve disc under this condition can be expressed as T f =(T1-T2) / 2;

[0036] (13) When the controller detects that the angle data of the photoelectric encoder is inconsistent with the angle data calculated by controlling the servo motor, it is considered that slippage has occurred and the test data is invalid;

[0037] (14) Modify the air source temperature, air pressure, valve disc rotation speed and angle, and test the friction torque under different conditions;

[0038] (15) According to the friction torque data under the above-mentioned different working conditions, the friction torque model of the air induction valve disc-channel friction pair can be established.

[0039] Embodiment 2:

[0040] The present invention provides a method and device for testing the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation, so as to simulate and test the friction torque of high-temperature aviation pneumatic butterfly valve disc under different working conditions and provide online measured data for the friction torque model. Figure 1 The photoelectric encoder specifically includes: a valve flap assembly 1, a servo motor 2, a reducer 3, a torque sensor 4, an insulation box 6, a coupling 7, and a controller 8.

[0041] In this embodiment, the coupling connection torque is increased to avoid rotation slip, and the valve disc movement angle is calculated by the servo motor, and the rest of the test method is the same as that of embodiment 1. When the torque does not change with the angle, the controller considers slippage and the data is invalid.

[0042] The above specific implementation methods or cases are only used to explain the technical solutions of the present invention, and are not intended to limit the present invention. Any parts not described in detail are regarded as conventional technical means in the art. A person of ordinary skill in the art should understand that based on the design concept of the present application, the technical solutions described in the aforementioned implementation methods should be adaptively modified, or some or all of the technical features therein should be replaced by equivalents. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A device for testing the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation, characterized in that: The testing device comprises: a servo motor, a reducer, a torque sensor, a photoelectric encoder, and a controller; Among them, the servo motor provides power for the entire test device and is used for the operation of the valve flap assembly; the reducer is used for speed reduction transmission and torque transmission between the servo motor and the air intake valve assembly; the torque sensor is used to test the torque during the rotation of the air intake valve assembly; the photoelectric encoder is used to record the rotation position of the valve assembly; and the controller is used for test system data acquisition and control.

2. A device for testing the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation as claimed in claim 1, characterized in that: The valve flap assembly includes a channel, a valve flap and a valve flap shaft. The valve flap is fixed on the valve flap shaft and is arranged in the channel. There is a certain angle between the valve flap shaft and the channel cross section. The channel flow control is achieved by controlling the rotation of the valve flap shaft.

3. A device for testing the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc as claimed in claim 2, characterized in that: The valve flap and the channel form a friction pair, and the friction torque is generated by the relative rotation between the valve flap and the channel; the valve flap is subjected to the high temperature and high pressure flow field and the aerodynamic torque during operation.

4. A device for testing the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc as claimed in claim 1, characterized in that: The testing device also includes: a heating box, The heating box is used to simulate the ambient temperature to which the valve flap assembly is subjected, or as a heat insulation device to prevent high temperature from affecting the test equipment.

5. A device for testing the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc as claimed in claim 4, characterized in that: During the test of the valve disc assembly, high-temperature and high-pressure air is passed into the channel to simulate the actual working conditions, and air regulation and shut-off control are achieved by changing the valve disc angle.

6. A device for testing the friction torque of high-temperature aviation pneumatic butterfly valve disc rotation as claimed in claim 1, characterized in that: The valve flap opening angle is measured by the photoelectric encoder.

7. A method for testing the friction torque of a high-temperature aviation pneumatic butterfly valve disc, using a testing device as described in any one of claims 1 to 6 to implement friction torque testing at different temperatures, gas pressures, disc rotation angles and rotation speeds, characterized in that: During the test, the channel is connected to high-temperature and high-pressure air, and the controller controls the servo motor and reducer to rotate the valve disc to a specific angle and fix it. After the gas flow field inside the channel is stable, the valve disc is rotated clockwise and counterclockwise by the same small angle. At this time, the torque sensor measures torques T1 and T2 respectively; when the valve disc rotates, its torque contribution comes from the aerodynamic torque T p and friction torque T f ; ① When the valve disc rotates clockwise or counterclockwise at a small angle, the change in friction torque can be ignored. Since the direction of friction torque is opposite to the direction of movement, the friction torque has the same magnitude but opposite direction. ② The valve disc movement angle is small, close to quasi-steady state. Near a certain angle, the change in aerodynamic torque can be ignored and the direction does not change. The aerodynamic torque T at this point can be calculated by the following formula p and friction torque T f : T p =(T1+T2) / 2 T f =(T1-T2) / 2 When the incoming air pressure and temperature change, the friction torque is tested under the corresponding temperature and pressure conditions.

8. A method for testing the rotational friction torque of a high-temperature aviation pneumatic butterfly valve disc as claimed in claim 7, characterized in that: By changing the rotation speed and position of the valve disc, the friction torque of the valve disc at different speeds and positions can be obtained.

Images