Device and method for testing the rotational friction torque of valve disc in high-temperature aero-pneumatic butterfly valves.

Abstract

The application discloses a testing device and method for the rotating friction torque of a high-temperature aviation aerodynamic butterfly valve disc, and belongs to the field of tribology, and provides accurate measured data for the rotating friction torque model of the high-temperature aviation aerodynamic butterfly valve disc. The testing device comprises a servo motor, a speed reducer, a torque sensor, a photoelectric encoder, a heating box and a controller. The servo motor provides power for the whole testing device and is used for the operation of the valve disc assembly. The speed reducer is used for the speed reduction transmission between the servo motor and the bleed air valve assembly and the transmission of the torque. The torque sensor is used for testing the torque in the rotating process of the bleed air valve assembly. The photoelectric encoder is used for recording the rotating position of the valve assembly. The controller is used for the data acquisition and control of the testing system. Through the testing method, the friction torque and the aerodynamic torque of the valve disc can be decoupled in the high-temperature variable flow field, the online testing data of the friction torque can be obtained, and the problem of lacking the online testing method of the valve disc friction torque is solved.

Description

Technical Field

[0001] This invention discloses a testing device and method for the rotational friction torque of valve discs in high-temperature aero-pneumatic butterfly valves, belonging to the field of tribology applications. Background Technology

[0002] High-temperature aviation pneumatic butterfly valves are critical regulating devices in aircraft air supply systems. Installed at the very beginning of the system, they regulate and shut off bleed air pressure. A malfunction of this valve can cause the air supply system to fail, leading to the inability of the aircraft's air conditioning and anti-icing systems to function properly, thus compromising aircraft safety. Therefore, high-temperature aviation pneumatic butterfly valves are essential components for ensuring flight safety and protecting lives.

[0003] The valve disc assembly is the mechanism for pressure regulation and shut-off in high-temperature aviation air butterfly valves. During operation, the valve disc is subjected to the action of high-temperature and high-pressure air, and is affected by the coupling effect of aerodynamic torque and valve disc friction torque. All friction torques of the valve disc have a significant impact on the regulating accuracy and switching characteristics of the butterfly valve. Therefore, measuring the friction torque of the valve disc is of great importance. Due to its coupling with the flow field, the flow field changes with the valve disc opening, and the high temperature and pressure make testing more complex, and direct testing is difficult. Therefore, there is an urgent need to propose a method for testing the valve disc friction torque. Summary of the Invention

[0004] The main objective of this invention is to provide a testing method and apparatus for the rotational friction torque of the valve disc of a high-temperature aero-pneumatic butterfly valve, so as to simulate and test the friction torque of the valve disc under different operating conditions and solve the problem of online testing method for friction torque without valve disc.

[0005] Technical solution: In order to achieve the above objectives, the present invention proposes a testing device for the rotational friction torque of a high-temperature aero-pneumatic butterfly valve disc. The testing device for the rotational friction torque of a high-temperature aero-pneumatic butterfly valve disc includes: a servo motor, a reducer, a torque sensor, a photoelectric encoder, a heating chamber, and a controller.

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

[0007] Furthermore, the valve assembly includes a channel, a valve disc, and a valve disc shaft; the valve disc is fixed on the valve disc shaft and positioned within the channel, with a certain angle between the valve disc shaft and the channel cross-section, and the channel flow control is achieved by controlling the rotation of the valve disc shaft.

[0008] Furthermore, the valve disc and the channel combine to form a friction pair, and the frictional torque is generated by the relative rotation between the valve disc and the channel. Simultaneously, the valve disc is subjected to a high-temperature, high-pressure flow field during operation, and thus experiences aerodynamic torque.

[0009] Furthermore, the high-temperature chamber is used to simulate the ambient temperature experienced by the valve assembly, or as a heat insulation device to prevent high temperatures from affecting the test equipment.

[0010] Furthermore, during testing, high-temperature, high-pressure air is introduced into the valve assembly channel to simulate actual working conditions. Air conditioning and shut-off control are achieved by changing the valve angle.

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

[0012] The purpose of this invention is to test the frictional torque between the valve disc and the channel. This invention can test the frictional torque under different temperatures, gas pressures, valve disc rotation angles, and rotation speeds. Simultaneously, this invention also proposes a testing method for the rotational frictional torque of a high-temperature aero-pneumatic butterfly valve disc. This testing method uses the testing device described above. During testing, the channel is connected to high-temperature, high-pressure air. A controller controls a servo motor and a reducer to rotate the valve disc to a fixed specific angle. After the gas flow field inside the channel stabilizes, the valve disc is rotated clockwise and counterclockwise by the same small angle, respectively. At this time, torque sensors measure torques T1 and T2, respectively. During valve disc rotation, the torque contribution comes from the aerodynamic torque T. p (The torque generated by the force of high-temperature, high-pressure gas acting on the valve disc) and frictional torque T f (The frictional torque generated by the relative motion between the valve disc and the passage); Here, it is assumed that ① at a certain angle where the valve disc rotates clockwise and counterclockwise by a small angle, the change in frictional torque can be ignored, and since the direction of the frictional torque is opposite to the direction of motion, the magnitude of the frictional torque is the same but the direction is opposite; ② the valve disc moves at a small angle, close to a quasi-steady state, and 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 using the following formula. p and frictional 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 frictional torque can be tested under the corresponding temperature and pressure conditions. By changing the rotation speed and position of the valve disc, the frictional torque of the valve disc at different speeds and positions can be obtained.

[0016] Beneficial technical effects: This invention designs a test method and device for the rotational friction torque of the valve disc of a high-temperature aero-pneumatic butterfly valve, so as to simulate and test the friction torque of the valve disc of a high-temperature aero-pneumatic butterfly valve under different operating conditions. Attached Figure Description

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

[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 Implementation

[0019] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Example 1:

[0021] This invention provides a method and apparatus for testing the rotational friction torque of a high-temperature aero-pneumatic butterfly valve disc, to simulate and test the friction torque of the valve disc under different operating conditions, providing online measured data for the friction torque model. See appendix. Figure 1 The specifically designed testing device for the rotational friction torque of a high-temperature aero-pneumatic butterfly valve disc includes: a valve 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 valve disc assembly 1 includes a channel 11, a valve disc 12, and a valve disc shaft 13. The valve disc 12 is fixed on the valve disc shaft 13 and is set in the channel 11. The flow control of the channel is achieved by controlling the rotation of the valve disc shaft; the valve disc shaft and the channel are at a certain inclination angle.

[0022] A servo motor drives the bleed air valve disc to rotate in both directions. A torque sensor measures the torque in each direction under different operating conditions, and the frictional torque of the bleed air valve disc can then be calculated. Specific steps include:

[0023] (1) The controller is connected to the servo motor, torque sensor and photoelectric encoder. By controlling the rotation speed of the servo motor, the rotation angle of valve disc 12 is controlled, and the position signal and torque signal of valve disc assembly are collected at the same time.

[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 via a coupling;

[0026] (4) The 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 different shaft products of servo motor, torque sensor and valve disc shaft 13, and avoid introducing measurement error;

[0029] (7) By controlling the ambient temperature of the valve assembly through the heat preservation box, the working environment temperature is simulated. At the same time, it isolates the high-temperature air to prevent heat radiation to the test device. On the other hand, it controls the opening of the heat preservation box 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 assembly to a high-temperature and high-pressure gas source and adjust the temperature and pressure to values ​​under different working conditions.

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

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

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

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

[0035] (12) The frictional torque of the bleed air valve disc under this operating 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 gas source temperature, gas pressure, valve disc rotation speed and angle, and test the friction torque under different conditions;

[0038] (15) Based on the friction torque data under different working conditions, the friction torque model of the air intake valve disc-channel friction pair can be established.

[0039] Example 2:

[0040] This invention provides a testing method and apparatus for the rotational friction torque of a high-temperature aero-pneumatic butterfly valve disc, to simulate and test the friction torque of the valve disc under different operating conditions, providing online measured data for the friction torque model. (The appendix has been removed.) Figure 1 The photoelectric encoder specifically includes: valve disc assembly 1, servo motor 2, reducer 3, torque sensor 4, insulation box 6, coupling 7, and controller 8.

[0041] In this embodiment, the coupling connection torque is increased to prevent rotational slippage. The valve disc movement angle is calculated using a servo motor, and the remaining testing methods are the same as in Embodiment 1. When the torque does not change with the angle, the controller considers it slippage, and the data is invalid.

[0042] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present invention. Parts not described in detail are considered as conventional technical means in the art. Those skilled in the art should understand that, based on the design concept of this application, it is possible to make adaptive modifications to the technical solutions described in the foregoing embodiments or to make equivalent substitutions for some or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A device suitable for testing the friction torque of the valve disc rotation of a high-temperature aeronautical pneumatic butterfly valve, characterized by, The test device comprises a servo motor, a reducer, a torque sensor, a photoelectric encoder and a controller. The servo motor provides power for the whole test device and is used for valve assembly work; the reducer is used for speed reduction transmission and torque transmission between the servo motor and the bleed air valve assembly; the torque sensor is used for testing the torque during the rotation of the bleed air valve assembly; the photoelectric encoder is used for recording the rotation position of the valve assembly; and the controller is used for data acquisition and control of the test system. During the test, the channel is connected to high temperature and high pressure air, the valve disc is rotated to a specific angle and fixed by the servo motor and the reducer controlled by the controller, and after the gas flow field in the channel is stable, the valve disc is rotated clockwise and counterclockwise by the same small angle, at which time the torque T1 and T2 are measured by the torque sensor respectively; when the valve disc is rotated, the torque is contributed by the aerodynamic torque T p and the friction torque T f ; when the air pressure and temperature change, the friction torque is tested under the corresponding temperature and pressure conditions.

2. A device for testing the friction torque of the valve disc of a high-temperature aeronautical aerodynamic butterfly valve according to claim 1, characterized in that, The valve assembly comprises a channel, a valve and a valve shaft, the valve is fixed on the valve shaft and arranged in the channel, and there is a certain angle between the valve shaft and the channel section; the rotation of the valve shaft is controlled to realize the flow control of the channel.

3. A device for testing the friction torque of the valve disc of a high-temperature aeronautical pneumatic butterfly valve according to claim 2, characterized in that, The valve and the channel form a friction pair, and the friction torque is generated by the relative rotation between the valve and the channel; the valve is subjected to the action of high-temperature and high-pressure flow field and aerodynamic torque during work.

4. A device for testing the friction torque of the valve disc of a high-temperature aeronautical butterfly valve according to claim 1, characterized in that, The test device further comprises a heating box, The heating box is used to simulate the environmental temperature to which the valve assembly is subjected, or as a heat insulation device to avoid the influence of high temperature on the test equipment.

5. A device for testing the friction torque of the valve disc of a high-temperature aeronautical pneumatic butterfly valve according to claim 4, characterized in that, The channel of the valve assembly is connected to high-temperature and high-pressure air during the test, which is used to simulate the actual working condition, and the air is adjusted and shut off by changing the angle of the valve.

6. A device for testing the friction torque of the valve disc of a high-temperature aeronautical butterfly valve according to claim 1, characterized in that, The opening angle of the valve is measured by the photoelectric encoder.

7. A test method suitable for the rotation friction torque of a high-temperature aviation aerodynamic butterfly valve valve, using the test device of any one of claims 1-6 to realize the friction torque test at different temperatures, gas pressures, valve rotation angles and rotation speeds, characterized in that, ① At a certain angle of the valve, the friction torque changes a small angle clockwise and counterclockwise, the change of the friction torque can be ignored, the direction of the friction torque is opposite to the direction of the movement, so the size of the friction torque is the same and the direction is opposite; ② The movement angle of the valve is small, which is close to quasi-steady state, near a certain angle, the change of the aerodynamic torque can be ignored, and the direction does not change; the aerodynamic torque T p and the friction torque T f at this place can be calculated respectively by the following formula: T p = (T1+T2) / 2 T f = (T1-T2) / 2.

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

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