A Measuring Device and Method for Wear Amount of a Graphite Sealing Structure under Temperature-Gas Coupling

Abstract

The present invention relates to a device for measuring the wear amount of a graphite sealing structure under the coupling of temperature and gas, comprising: a sealing cavity part, a gas supply device, and a rotation speed control device; the gas supply device is used to supply gas into the sealing cavity part; wherein, the sealing cavity part includes a front chamber cover, a rear cover, and a middle cavity; the middle cavity is provided with a graphite sealing structure; the sealing cavity part is provided with a hollow shaft; the hollow shaft penetrates out of the sealing cavity part and is connected to the rotation speed control device; the graphite sealing structure is fitted on the side of the hollow shaft; a clamping device is arranged in the middle cavity, and the clamping device cooperates with the graphite sealing structure to adjust the contact force with the side of the hollow shaft.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and particularly relates to a device and method for measuring the wear amount of a graphite sealing structure under thermo-gas coupling. Background Art

[0002] "An aero-engine is the 'heart' of an aircraft. It is an extremely complex and precise thermal machine that can provide power for the aircraft to fly, representing the country's comprehensive strength and scientific and technological level. An aero-engine needs to withstand high loads and heat shocks and is very prone to failure. Therefore, the requirements for the performance of an aero-engine are very high. In recent years, the requirements for aero-engines have become increasingly high, and the performance requirements for some components are very strict. Reducing the flow of the secondary flow of an aero-engine, that is, reducing the leakage of high-temperature and high-pressure gases, is one of the means to improve the performance of an aero-engine. According to research data, good sealing measures can improve the performance of an aero-engine by 1%-2%.

[0003] The improvement of the performance of an aero-engine is inseparable from the development and application of sealing technology. The sealing mechanism has also developed from non-contact seals such as labyrinth seals and comb seals to contact seals such as brush seals and graphite seals. Graphite has the advantages of good heat conduction and wear resistance and is widely used. At present, the good sealing technology of aero-engines, graphite seals, has the advantages of low air leakage, good heat conduction, wear resistance, corrosion resistance, etc. Since graphite seals belong to contact seals and have a certain contact force, there must be wear in graphite seals. Graphite seals effectively reduce the leakage amount, but there is also a wear amount. As the wear amount increases, when it reaches a certain limit, the graphite seal will fail. Therefore, how to accurately measure the wear amount of graphite seals is an effective method for evaluating the failure of graphite seal structures. At present, the wear measurement of graphite seal structures is generally carried out on a high-temperature material wear testing machine or a graphite wear tester at room temperature. There is still a large gap from the actual working environment of the graphite seal structure, so the measurement error is still very large. And how to simulate the working environment of the graphite seal structure under high temperature and high pressure of an aero-engine, which is similar to the actual environment of an aero-engine, is a problem that needs to be solved for the current graphite seal experiment. Summary of the Invention

[0004] Regarding the problem of the measurement method for the wear characteristics of the graphite seal structure in an aeroengine under high temperature and high pressure, the key lies in how to simulate the high temperature and high pressure working environment of the graphite seal structure to be consistent with the internal environment of the aeroengine. Generally, the graphite seal structure of an aeroengine seals the low-pressure end and the high-pressure end of the aeroengine. The compressor rotor does work on the airflow under high-speed rotation, greatly increasing the pressure and temperature of the airflow. Since the compressor has multiple stages, there must be gaps between the rotor and the casing, and the shaft. The graphite seal structure is arranged here, so the graphite seal structure is affected by high temperature and high pressure gases. How to simulate this working environment in detail is the key problem to be solved by the present invention.

[0005] The above technical objectives of the present invention are achieved through the following technical solutions:

[0006] In one aspect of the present disclosure, a device for measuring the wear amount of a graphite seal structure under temperature-gas coupling is disclosed, including:

[0007] A seal cavity part, a gas supply device, and a speed control device;

[0008] The gas supply device is used to supply gas into the seal cavity part;

[0009] Among them, the seal cavity part includes a front chamber cover, a rear cover, and a middle cavity;

[0010] The middle cavity is provided with a graphite seal structure;

[0011] The seal cavity part is provided with a hollow shaft; the hollow shaft penetrates out of the seal cavity part and is connected to the speed control device;

[0012] The graphite seal structure is fitted on the side of the hollow shaft;

[0013] A clamping device is arranged in the middle cavity, and the clamping device cooperates with the graphite seal structure to adjust the contact force with the side of the hollow shaft.

[0014] Further, the clamping device includes a pressing ring, a force transmission column, an adjusting bolt, and a thrust sensor;

[0015] The pressing ring is fitted on the outside of the graphite seal structure. By adjusting the adjusting bolt, the pressing degree of the force transmission column on the pressing ring changes, and the thrust sensor is used to detect the pressing force.

[0016] Further, a partition medium is arranged in the middle of the hollow shaft.

[0017] Further, the gas supply device includes an air compressor, a gas storage tank, a stop valve, a heater, a pipeline, and a pressure regulating valve;

[0018] The air compressor, the gas storage tank, the stop valve, and the heater pressure regulating valve are all connected to the pipeline.

[0019] Further, the speed control device includes a frequency converter, a motor, a heat-insulating coupling, a first bearing housing, a second bearing housing, and a speed sensor;

[0020] The heat-insulating coupling, the motor, and the frequency converter are sequentially connected to the end of the hollow shaft;

[0021] The first bearing housing and the second bearing housing are arranged in the middle of the hollow shaft;

[0022] The speed sensor is used to detect the speed of the hollow shaft.

[0023] Further, a temperature sensor is arranged in the middle cavity;

[0024] The front chamber cover is provided with a temperature and pressure sensor.

[0025] In another aspect of the present disclosure, a method for measuring the wear amount of a graphite sealing structure under thermogas coupling is disclosed. Using the measuring device according to any one of claims 1-6, it is characterized by including the following steps:

[0026] Step 1: Assemble the measuring device according to the experimental requirements, debug and operate it normally, and measure the initial weight G of the graphite sealing structure 1 ;

[0027] Step 2: Inflate and pressurize the gas storage tank, and control the pressure to be not less than 1.5 times the experimental required pressure, and set it according to the specific rated pressure of the gas storage tank;

[0028] Step 3: Set the speed of the hollow shaft to zero. At this time, the hollow shaft is in a static state. Adjust the clamping device of the graphite sealing structure to zero contact force; open the stop valve, open the heater to set the experimental gas temperature T 1 , adjust the pressure regulating valve to the lowest experimental pressure P 1 , and heat the air in the sealing cavity;

[0029] Step 4: Observe the temperature value of the graphite sealing structure by the temperature sensor. After the temperature of the graphite sealing structure reaches the same as the inlet air temperature and the temperature change range meets the experimental accuracy requirements; start the frequency converter to control the shaft speed and reach the first experimental speed;

[0030] Step 5: Rotate the adjusting bolt to adjust the contact force of the graphite sealing structure to the predetermined pressure N 1 , and conduct the experiment for the first experimental cycle. The experimental time is set according to the experimental requirements;

[0031] Step 6: Adjust the contact force of the graphite sealing structure to zero, shut down the frequency converter, and turn off the heater; however, the gas flow is not shut off, and the heater and the internal components of the sealing cavity are cooled; record parameters such as the gas pressure, temperature, graphite sealing structure pressure, and rotational speed, disassemble the graphite sealing structure, and measure its weight as G 2 ;

[0032] Step 7: Install the graphite sealing structure, etc., and conduct the next working condition experiment; according to Steps 3 to 6, set different experimental parameters according to the requirements of the experimental outline, and complete the wear performance experiment of the graphite sealing structure under all working conditions;

[0033] Step 8: According to the experimental measurement data, conduct data processing, and the wear amount of the graphite sealing structure varying with the rotational speed under different air pressures can be obtained at the same temperature and the same graphite sealing contact force; the wear amount of the graphite sealing structure varying with the rotational speed under different temperatures can be obtained at the same graphite sealing contact force and the same gas pressure; the wear amount varying with the rotational speed under different graphite sealing structure contact forces can be obtained at the same temperature and gas pressure; and the wear characteristics of the graphite sealing structure under multi-parameter coupling can be obtained.

[0034] Further, in Step 3: The flow path of the hot air is as follows: First, the hot air leaks into the rear cavity of the sealing cavity along the gap of the graphite sealing structure and flows out from the shaft gap. The hot air heats the graphite sealing structure; Second, the hot air flows into from the hollow shaft. A porous medium is provided in the hollow shaft to restrict the air flow. Only a small amount of air flows out from the porous medium, which plays a role in maintaining the pressure of the sealing cavity. The leaked air is discharged to the atmosphere along the shaft pores to preheat the hollow shaft.

[0035] The beneficial effects of the present invention include:

[0036] Due to the particularity of the internal environment of an aeroengine, the experiments on aeroengine components should also be similar to the working conditions of a real aeroengine. The present invention simulates the working conditions of the graphite sealing mechanism of an aeroengine in a real environment.

[0037] The heating of the experimental cavity in the present invention is carried out by using high-temperature and high-pressure air flow, which is similar to the heat transfer of the graphite sealing structure by the aeroengine, improving the accuracy of the experimental measurement results.

[0038] The present invention can realize the experimental study on the wear characteristics of the graphite sealing structure under multi-parameter coupling, and can also conduct conventional experiments under normal temperature and pressure or variable rotational speed experiments, etc., broadening the experimental conditions for the wear characteristics of the graphite sealing of the aeroengine, enriching the experimental content, and ensuring the reliability of the operation of the aeroengine.

[0039] The wear measurement device for the graphite seal structure of an aero-engine under thermogas coupling can measure the leakage of the graphite seal structure under normal temperature and pressure, or the leakage of other seal structures, achieving multiple uses with one method, effectively saving resources and avoiding duplicate construction. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a schematic structural diagram of a wear measurement device for a graphite seal structure under thermogas coupling;

[0041] Figure 2 It is a schematic structural diagram of the seal cavity part.

[0042] In the figure: 1, air compressor; 2, gas storage tank; 3, stop valve; 4, heater; 5, pipeline; 6, pressure regulating valve; 7, front chamber cover; 8, temperature and pressure sensor; 9, adjusting bolt; 10, middle cavity; 11, force transmission column; 12, thrust sensor; 13, hollow shaft; 14, graphite seal structure; 15, clamping ring; 16, temperature sensor; 17, rear cover; 18, partition medium; 19, first bearing seat; 20, second bearing seat; 21, heat insulation coupling; 22, rotational speed sensor; 23, motor; 24, frequency converter. DETAILED DESCRIPTION OF THE INVENTION

[0043] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0044] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0045] To make the objectives, technical solutions, and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are merely exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0046] As Figure 1-2 shown, a wear measurement device for a graphite sealing structure under temperature-gas coupling includes:

[0047] a sealing cavity part, a gas supply device, and a rotational speed control device;

[0048] The gas supply device is used to supply gas into the sealing cavity part;

[0049] Among them, the sealing cavity part includes a front chamber cover 7, a rear cover 17, and a middle cavity 10;

[0050] The middle cavity 10 is provided with a graphite sealing structure 14;

[0051] The sealing cavity part is provided with a hollow shaft 13; the hollow shaft 13 extends out of the sealing cavity part and is connected to the rotational speed control device;

[0052] The graphite sealing structure 14 is fitted on the side of the hollow shaft 13;

[0053] A clamping device is arranged in the middle cavity 10, and the clamping device cooperates with the graphite sealing structure 14 to adjust the contact force with the side of the hollow shaft 13.

[0054] Specifically, a sealing cavity is formed inside the front chamber cover 7 and the rear cover 17 to ensure the stable effect after the hot air flow enters and the preheating of the hollow shaft 13 and the graphite sealing structure 14. The graphite sealing structure 14 is installed through the middle cavity 10. The graphite sealing structure 14 is axially limited in the middle cavity 10 of the sealing cavity and can only adjust the contact force of pressing along the radial direction through the clamping device. The gas supply device can supply gas with adjustable temperature and pressure into the sealing cavity part, and the rotational speed control device can adjust the rotational speed of the hollow shaft 13. The flow path of the hot air is as follows: First, the hot air flow leaks into the rear cavity of the sealing cavity along the gap of the graphite sealing structure and flows out from the shaft gap, and the hot air flow heats the graphite sealing structure; Second, the hot air flow flows into the hollow shaft, and a partition medium is arranged inside the hollow shaft to limit the flow of the air flow. Only a small amount of air flow flows out from the porous medium, which plays a role in maintaining the pressure of the sealing cavity. The leaked air flow is discharged to the atmosphere along the shaft pores, thereby preheating the hollow shaft. Through the above settings, it is possible to simulate the graphite sealing structure 14 in a high-temperature and high-pressure environment.

[0055] In some embodiments, the clamping device includes a pressing ring 15, a force transmission column 11, an adjusting nut 9, and a thrust sensor 12;

[0056] The pressing ring 15 is fitted outside the graphite sealing structure 14. By adjusting the adjusting nut 9, the pressing degree of the force - transmitting column 11 on the pressing ring 15 is changed, and the thrust sensor 12 is used to detect the pressing force.

[0057] Adopting the above - mentioned technical solution, the adjusting nut 9 applies a contact force perpendicular to the axis rotation center line to the pressing ring 15 through the force - transmitting column 11. After adjusting the adjusting nut 9, the pressing degree of the force - transmitting column 11 on the pressing ring 15 is changed, so that the contact force between the graphite sealing structure 14 and the hollow shaft 13 is changed.

[0058] In some embodiments, a partition medium 18 is provided in the middle of the hollow shaft 13.

[0059] Adopting the above - mentioned technical solution, by setting the partition medium 18, the part of the hollow shaft 13 located in the sealing cavity is sealed. After the gas is introduced into the sealing cavity, part of the gas will enter the inside of the hollow shaft 13, and the hollow shaft 13 is also heated.

[0060] In some embodiments, the gas supply device includes an air compressor 1, a gas storage tank 2, a stop valve 3, a heater 4, a pipeline 5, and a pressure - regulating valve 6;

[0061] The air compressor 1, the gas storage tank 2, the stop valve 3, the heater 4, and the pressure - regulating valve 6 are all connected to the pipeline 5, and the gas flows through the pipeline 5.

[0062] Adopting the above - mentioned technical solution, the air compressor 1 can pump air into the gas storage tank 2 to ensure the air pressure required for the experiment; the stop valve 3 is used to control the cut - off flow of the air flow; the heater 4 pre - heats the air flow, and the high - temperature and high - pressure gas is adjusted to the required pressure for the experiment by the pressure - regulating valve 6, and the air flow is supplied to the sealing cavity.

[0063] In some embodiments, the speed control device includes a frequency converter 24, a motor 23, a heat - insulating coupling 21, a first bearing seat 19, a second bearing seat 20, and a speed sensor 22;

[0064] The heat - insulating coupling 21, the motor 23, and the frequency converter 24 are connected to the end of the hollow shaft 13 in sequence;

[0065] The first bearing seat 19 and the second bearing seat 20 are arranged in the middle of the hollow shaft 13;

[0066] The speed sensor 22 is used to detect the rotational speed of the hollow shaft 13.

[0067] Adopting the above - mentioned technical solution, the rotational speed of the hollow shaft 13 is controlled by the motor 23 and the frequency converter 24, and at the same time, the speed sensor 22 is used for real - time rotational speed detection. The first bearing seat 19 and the second bearing seat 20 can ensure the stable rotation of the hollow shaft 13.

[0068] In some embodiments, a temperature sensor 16 is provided in the middle cavity 10;

[0069] The front chamber cover 7 is provided with a temperature and pressure sensor 8.

[0070] With the above technical solutions, the temperature sensor 16 measures the temperature of the graphite sealing structure 14 as a control signal; the temperature and pressure sensor 8 detects the temperature and pressure in the sealing cavity part to facilitate the adjustment in the gas supply device.

[0071] The present invention also discloses a method for measuring the wear amount of a graphite sealing structure under the coupling of temperature and gas, including the following steps:

[0072] Step 1: Assemble the measuring device according to the experimental requirements, debug and operate it normally, and measure the initial weight G of the graphite sealing structure 1 ;

[0073] Step 2: Inflate and pressurize the gas storage tank, and control the pressure to be not less than 1.5 times the experimental required pressure, which is set according to the specific rated pressure of the gas storage tank;

[0074] Step 3: Set the rotational speed of the hollow shaft to zero. At this time, the hollow shaft is in a static state, and adjust the clamping device of the graphite sealing structure to zero contact force; open the stop valve, turn on the heater to set the experimental gas temperature T 1 , adjust the pressure regulating valve to the lowest experimental pressure P 1 , and heat the air in the sealing cavity;

[0075] Step 4: Observe the temperature value of the graphite sealing structure by the temperature sensor of the graphite sealing structure. After the temperature of the graphite sealing structure reaches the same as the inlet air temperature and the temperature change range meets the experimental accuracy requirements; turn on the frequency converter to control the shaft rotational speed to reach the first experimental rotational speed;

[0076] Step 5: Rotate the adjusting bolt to adjust the contact force of the graphite sealing structure to the predetermined pressure N 1 , and conduct the experiment for the first experimental cycle. The experimental time is set according to the experimental requirements;

[0077] Step 6: Adjust the contact force of the graphite sealing structure to zero, turn off the frequency converter, and turn off the heater; but do not turn off the air flow, and cool the heater and the internal components of the sealing cavity; record parameters such as the pressure and temperature of the gas, the pressure of the graphite sealing structure, and the rotational speed, disassemble the graphite sealing structure, and measure its weight as G 2 ;

[0078] Step 7: Install the graphite sealing structure, etc., and conduct the experiment for the next working condition; according to steps 3 to 6, set different experimental parameters according to the experimental outline requirements to complete the wear performance experiment of the graphite sealing structure under all working conditions;

[0079] Step 8: According to the experimental measurement data, data processing is carried out, and the wear amount of the graphite seal structure varying with the rotational speed under the same temperature and the same graphite seal contact force but different air pressures can be obtained; the wear amount of the graphite seal structure varying with the rotational speed under the same graphite seal contact force and the same gas pressure but different temperatures; the wear amount of the graphite seal structure varying with the rotational speed under different graphite seal structure contact forces under the same temperature and gas pressure; and the wear characteristics of the graphite seal structure under multi-parameter coupling are obtained.

[0080] Further, in Step 3: The flow path of the hot air is as follows: First, the hot air leaks into the inner cavity of the seal chamber along the gap of the graphite seal structure and flows out from the shaft gap, and the hot air heats the graphite seal structure; Second, the hot air flows into the hollow shaft, and a partition medium is arranged in the hollow shaft to restrict the flow of the air. Only a small amount of air flows out from the porous medium, which plays a role in maintaining the pressure of the seal chamber. The leaked air is discharged to the atmosphere along the shaft pores to preheat the hollow shaft.

[0081] Taking the experimental process of one working condition as an example:

[0082] The diameter D of the hollow shaft of the seal chamber is 200 mm, and the rotational speed range is 0 - 6000 n / rpm. One of the experimental conditions required by the experimental outline of a certain graphite seal structure test piece is: rotational speed 3000 n / rpm, air flow temperature 400 K, air flow pressure 0.25 Mpa. The contact force of the graphite seal structure does not exceed 300 g, and the duration of one experiment is not less than 30 minutes.

[0083] According to the requirements of the experimental outline, the experimental pressure is 0.25 Mpa, and the air storage tank needs to be pressurized to more than 1.5 * 0.25 = 0.375 Mpa. Therefore, the air storage tank is pressurized to the atmosphere to 0.4 Mpa. Measure the weight G of the graphite seal structure 1 = 125.457 g.

[0084] Install the graphite seal structure. Adjust the contact force to zero, open the stop valve, turn on the heater, set the temperature of the heater to 400 K, adjust the air flow pressure to 0.25 Mpa, and use the room temperature pressure sensor in front of the seal chamber as the control data for observation. The hot air starts to heat the hollow shaft and the graphite seal structure. At this time, the graphite seal temperature sensor monitors the temperature change of the graphite seal structure. When the temperature reaches 400 K within the range of ±5°, it is considered that the preheating of the experimental system is completed.

[0085] Set the motor rotational speed to 3000 n / rpm, control the motor with a frequency converter, monitor the rotational speed sensor. After the rotational speed is stable, apply a contact force to the graphite seal structure, which is set to 200 g according to the experimental requirements. Start timing, and the experimental time is 30 minutes.

[0086] When the experimental time is up, adjust the graphite seal contact force to zero, turn off the frequency converter, stop the motor from rotating, turn off the heater, cool and ventilate the system, observe the temperature sensor, and wait until the temperature is close to room temperature before disassembling the graphite seal device.

[0087] Measure the weight G2 = 125.4523 g. Therefore, record the experimental data table as shown in Table 1 below:

[0088]

[0089] Table 1

[0090] It should be understood that the above specific embodiments of the present invention are only used for exemplary illustration or explanation of the principle of the present invention, and do not constitute a limitation on the present invention. Therefore, any modifications, equivalent replacements, improvements, etc. made without departing from the spirit and scope of the present invention shall be included within the protection scope of the present invention. In addition, the appended claims of the present invention are intended to cover all changes and modification examples that fall within the scope and boundary of the appended claims, or equivalent forms of such scope and boundary.

Claims

1. A measuring device for the wear amount of a graphite sealing structure under the coupling of temperature and gas, characterized in that, it includes: a sealing cavity part, a gas supply device, and a rotation speed control device; the gas supply device is used to supply gas into the sealing cavity part; wherein, the sealing cavity part includes a front chamber cover (7), a rear cover (17), and a middle cavity (10); the middle cavity (10) is provided with a graphite sealing structure (14); the sealing cavity part is provided with a hollow shaft (13); the hollow shaft (13) penetrates out of the sealing cavity part and is connected to the rotation speed control device; the graphite sealing structure (14) is fitted on the side of the hollow shaft (13); a clamping device is arranged in the middle cavity (10), and the clamping device cooperates with the graphite sealing structure (14) to adjust the contact force with the side of the hollow shaft (13); the gas supply device includes an air compressor (1), a gas storage tank (2), a stop valve (3), a heater (4), a pipeline (5), and a pressure regulating valve (6); the air compressor (1), the gas storage tank (2), the stop valve (3), the heater (4), and the pressure regulating valve (6) are all connected to the pipeline (5); the rotation speed control device includes an inverter (24), a motor (23), a heat-insulating coupling (21), a first bearing seat (19), a second bearing seat (20), and a rotation speed sensor (22); the heat-insulating coupling (21), the motor (23), and the inverter (24) are sequentially connected to the end of the hollow shaft (13); the first bearing seat (19) and the second bearing seat (20) are arranged in the middle of the hollow shaft (13); the rotation speed sensor (22) is used to detect the rotation speed of the hollow shaft (13); a temperature sensor (16) is arranged in the middle cavity (10); the front chamber cover (7) is provided with a temperature and pressure sensor (8); the clamping device includes a pressing ring (15), a force transmission column (11), an adjusting bolt (9), and a thrust sensor (12); the pressing ring (15) is fitted on the outside of the graphite sealing structure (14). By adjusting the adjusting bolt (9), the pressing degree of the force transmission column (11) on the pressing ring (15) changes, and the thrust sensor (12) is used to detect the pressing force.

2. The measuring device for the wear amount of a graphite sealing structure under the coupling of temperature and gas according to claim 1, characterized in that: a medium separator (18) is arranged in the middle of the hollow shaft (13).

3. A method for measuring the wear amount of a graphite sealing structure under the coupling of temperature and gas, using the measuring device according to any one of claims 1-2, characterized in that, it includes the following steps: Step 1: Assemble the measuring device according to the experimental requirements, debug and operate it normally, and measure the initial weight G of the graphite sealing structure 1 ; Step two: Inflate and pressurize the gas storage tank, and the pressure is controlled to be not less than 1.5 times the pressure required for the experiment, and it is set according to the specific rated pressure of the gas storage tank; Step 3: Set the rotational speed of the hollow shaft to zero. At this time, the hollow shaft is in a stationary state, and adjust the clamping device of the graphite sealing structure to zero contact force; open the stop valve, turn on the heater, and set the experimental gas temperature T 1 , adjust the pressure regulating valve to the lowest experimental pressure P 1 , and heat the air in the sealing cavity; Step four: Observe the temperature value of the graphite sealing structure through the temperature sensor of the graphite sealing structure. After the temperature of the graphite sealing structure reaches the same as the intake air temperature and the temperature change range meets the experimental accuracy requirements; turn on the inverter to control the shaft rotation speed to reach the first experimental rotation speed; Step 5: Rotate the adjusting bolt (9) to adjust the contact force of the graphite sealing structure until it reaches the predetermined pressure N 1 , and conduct the experiment for the first experimental cycle. The experimental time is set according to the experimental requirements; Step 6: Adjust the contact force of the graphite sealing structure to zero, shut down the frequency converter, and turn off the heater; however, do not turn off the gas flow, and cool the heater and the internal components of the sealing cavity; record the gas pressure, temperature, graphite sealing structure pressure, and rotational speed parameters, disassemble the graphite sealing structure, and measure its weight as G 2 ; Step 7: Install the graphite sealing structure and conduct the next working condition experiment; according to Steps 3 to 6, set different experimental parameters according to the requirements of the experimental outline to complete the wear performance experiment of the graphite sealing structure under all working conditions; Step 8: According to the experimental measurement data, conduct data processing to obtain the wear amount of the graphite sealing structure varying with the rotational speed under different air pressures at the same temperature and the same graphite seal contact force; the wear amount of the graphite sealing structure varying with the rotational speed under different temperatures at the same graphite seal contact force and the same gas pressure; the wear amount of the graphite sealing structure varying with the rotational speed under different graphite seal contact forces at the same temperature and gas pressure; and obtain the wear characteristics of the graphite sealing structure under multi-parameter coupling.

4. A method for measuring the wear amount of a graphite sealing structure under temperature-gas coupling according to claim 3, characterized in that: In Step 3: The flow path of the hot air is as follows: First, the hot air leaks into the inner cavity of the sealing cavity along the gap of the graphite sealing structure and flows out from the shaft gap, and the hot air heats the graphite sealing structure; Second, the hot air flows into the hollow shaft, and a porous medium is arranged in the hollow shaft to restrict the air flow. Only a small amount of air flows out of the porous medium, which plays a role in maintaining the pressure of the sealing cavity. The leaked air flows along the shaft pores to the atmosphere to preheat the hollow shaft.

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