A kind of experimental system for measuring the sealing aerodynamic parameters of multi-disc cavity gill air system

Abstract

This invention relates to the field of aero-engine air system technology, and more particularly to an experimental system for measuring the aerodynamic parameters of a multi-cavity grating air system seal. It includes a horizontally positioned experimental platform, with a hollow shaft at the front end connected to a motor via a coupling, and a slip ring actuator at the rear end. The platform is also equipped with an oil supply system, an air supply system, and a measurement and control system. The oil supply system employs a one-supply, two-return oil supply mode to ensure smooth oil supply and return to each bearing cavity. A clearance displacement sensor is used to address the challenge of high-frequency, high-resolution dynamic measurement of grating seal geometric deviations, enabling real-time display of the radial clearance of each grating seal. Pressure and temperature sensors are installed to accurately understand the physical state at the grating clearance and the flow state of fluid passing through the grates. The system has the function of real-time acquisition of physical parameters such as pressure, temperature, and grating radial clearance.

Description

Technical Field

[0001] This invention relates to the field of aero-engine air system technology. Background Technology

[0002] Currently, aero engines are rapidly developing towards higher thrust-to-weight ratios, lower fuel consumption, and higher reliability. However, with the increasing turbine inlet gas temperature year by year, the required cooling airflow is also increasing to ensure reliable and stable engine operation. This places extremely high demands on the stability and reliability of the air system. Therefore, an effective and reliable air system is needed to ensure stable engine operation. Geometric deviation is a significant factor affecting the air system; therefore, studying the impact of geometric deviation on the air system and accurately measuring the various aerodynamic parameters within the air system has important theoretical and engineering application value.

[0003] Air grates are one of the most important components in an air sealing system. They effectively reduce leakage, improve engine thrust-to-weight ratio, reduce fuel consumption, and increase overall engine efficiency. Therefore, many researchers have conducted extensive studies on air grates. However, research on air grates consisting of multiple grates and their cavities is relatively limited. Current research on multi-stage air grates primarily focuses on numerical simulation analysis, with one-dimensional network simulation being the most prevalent and already applied in engineering. Two-dimensional network simulation is also gradually developing, while three-dimensional network simulation is currently extremely rare, costly to implement, and computationally time-consuming. Therefore, it is necessary to conduct experimental research on air grates consisting of multiple grates.

[0004] In addition, most current measurements for grating experiments involve measuring the inlet and outlet pressures and leakage of the grating. The flow state inside the grating is mostly obtained through numerical simulation, lacking real internal parameters of the grating. Therefore, it is necessary to design a suitable measurement system to measure the internal parameters of the grating.

[0005] Furthermore, to investigate the impact of detailed geometric deviations on the internal air system, these deviations are broken down into three parts: process deviation, axial displacement deviation, and wind resistance / thermal deformation deviation. Therefore, it is necessary to design grate discs of different sizes and modify their operating environment to assess their effects on the air system.

[0006] Finally, different grate structures have different sealing effects on the sealed air system. According to scholars' research, stepped grate has a better sealing effect than straight-through grate. Among stepped grate, the divergent stepped grate has the best sealing effect, followed by the general stepped grate, and finally the convergent stepped grate.

[0007] Therefore, this invention designs an experimental system that can replace different types of sieve teeth, consists of a disc cavity and a sieve disc, and measures the parameters of the sieve teeth and the internal parameters of each cavity. Summary of the Invention

[0008] The purpose of this invention is to overcome the shortcomings of the prior art and provide an experimental system for measuring the aerodynamic parameters of a multi-cavity comb air system seal. The system measures in real time the pressure, temperature, and gap at the gap corresponding to different geometric deviations caused by different comb seals, the surface temperature of the comb disc in the comb seal, and the pressure of each cavity through a measurement and control system. It is suitable for scenarios where various physical parameters of an air system are measured under various geometric deviations.

[0009] To achieve the above objectives, the technical solution adopted by the present invention is as follows: an experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system, characterized in that it includes a horizontally set experimental platform body, the hollow shaft at the front end of the experimental platform body is connected to a motor through a coupling, the rear end of the experimental platform body is connected to a slip ring actuator, and an oil supply system, an air supply system and a measurement and control system are also set around the experimental platform body. The main body of the experimental platform includes a hollow shaft, a tooth seal composed of a toothed housing and a toothed disc, an outer housing, a front bearing, a rear bearing, a front bearing seat, and a rear bearing seat; the hollow shaft, the tooth seal composed of the toothed housing and the toothed disc, the front bearing, and the rear bearing constitute a rotor system. The aforementioned tooth housing is equipped with pressure sensors and temperature sensors for measuring the cavity pressure and temperature of the sealing cavity, annular cavity, and rotating disk cavity of the tooth seal. The data measured by the pressure sensors and temperature sensors, as well as the data transmitted via the slip ring actuator, are all entered into the measurement and control system through the data acquisition unit. The main body of the experimental platform is mounted on the front rotor support assembly and the rear rotor support assembly.

[0010] Furthermore, the main body of the experimental platform forms 4 sealed cavities, 1 annular cavity, 2 bearing cavities, and 4 rotating disk cavities; the sealed cavities include a first sealed cavity, a second sealed cavity, a third sealed cavity, and a fourth sealed cavity; the annular cavity is one; the bearing cavities include a front bearing cavity and a rear bearing cavity; and the rotating disk cavities include a first rotating disk cavity, a second rotating disk cavity, a third rotating disk cavity, and a fourth rotating disk cavity. The aforementioned tooth seal includes a first tooth seal, a second tooth seal, and a third tooth seal, and the tooth housings corresponding to the tooth seals are the first tooth housing, the second tooth housing, and the third tooth housing, respectively; the corresponding tooth discs are the first tooth disc, the second tooth disc, and the third tooth disc, respectively.

[0011] Furthermore, the first grate plate of the first grate sealing has oblique teeth and a stepped tooth type. The second grate plate of the second grate sealing has oblique teeth and a stepped tooth type. The number of grate steps is less than that of the first grate sealing. The third grate plate of the third grate sealing has trapezoidal teeth and a straight tooth type. The grate radii of the first, second, and third grate sealing decrease sequentially.

[0012] Furthermore, the front bearing cavity is the bearing cavity where the front bearing is located, and the rear bearing cavity is the bearing cavity where the rear bearing is located; the first sealing cavity is on the front side of the front bearing cavity, the second sealing cavity is on the rear side of the front bearing cavity, the third sealing cavity is on the front side of the rear bearing cavity, and the fourth sealing cavity is on the rear side of the rear bearing cavity; the first rotating disk cavity is located on the front side of the first toothed seal, the second rotating disk cavity is located between the first toothed seal and the second toothed seal, the third rotating disk cavity is located between the second toothed seal and the third toothed seal, and the fourth rotating disk cavity is located on the rear side of the third toothed seal.

[0013] Furthermore, the first, second, and third grate housings are equipped with pressure sensors and temperature sensors for measuring the pressure and temperature between the teeth of each grate in the grate seal; the pressure sensors are used to capture the pressure pulsation of the leaking airflow between each grate tooth, and the temperature sensors are used to monitor the temperature distribution of the airflow between each grate tooth.

[0014] The first grate housing is equipped with 10 pressure sensors arranged according to the stepped grate structure to measure the pressure between the teeth of the first grate sealing, and 15 temperature sensors are arranged to measure the fluid temperature between the teeth of the first grate sealing. The second grate housing is equipped with 4 pressure sensors arranged according to the stepped grate structure to measure the pressure between the teeth of the first grate sealing, and 9 temperature sensors are arranged to measure the fluid temperature between the teeth of the second grate sealing. The third grate housing is equipped with 9 pressure sensors arranged according to the straight-through grate structure to measure the pressure between the teeth of the first grate sealing, and 10 temperature sensors to measure the fluid temperature between the teeth of the third grate sealing. Surface mounting is used for the first, second, and third grate housings. Temperature sensors are used to collect the surface temperature of the toothed gear housing. Temperature sensors are mounted on the surfaces of the first, second, and third toothed gear discs to collect the surface temperature of the toothed gears, reflecting the temperature of the toothed gears. The temperature sensors measuring the surface temperature of the toothed gears extend into a hollow shaft, and their extension lines are connected to the data lines of the data acquisition unit via brushes on a slip ring actuator. The data acquisition unit transmits the collected temperature signals to the measurement and control system. Data from the temperature sensors measuring the fluid temperature between each toothed gear, the temperature sensors measuring the surface temperature of the toothed gear housing, the pressure sensors measuring the pressure between each toothed gear, and the data transmitted via the slip ring actuator are all fed into the measurement and control system through the data acquisition unit.

[0015] The gap between the grate discs and the grate housing of the first, second, and third grate seals is measured using a gap displacement sensor. The gap displacement sensor calculates the rotor-stator gap by the time difference between emitting and receiving infrared lasers within the gap. The gap displacement sensor is fixed by a special probe bracket. The data measured by the gap displacement sensor and the data transmitted via the slip ring actuator are both entered into the measurement and control system through a data acquisition unit.

[0016] Furthermore, the oil supply system includes an oil tank, an oil supply pump, two return oil pumps, and pipelines connected to the bearing cavities on both sides of the main body of the experimental platform. After the oil tank is connected to the oil supply pumps through pipelines, it is divided into two lines and connected to the front bearing cavity oil supply pipeline and the rear bearing cavity oil supply pipeline of the front bearing cavity and the rear bearing cavity oil supply pipeline of the main body of the experimental platform. The front bearing cavity return oil pipeline and the rear bearing cavity return oil pipeline of the front bearing cavity and the rear bearing cavity return oil outlet are respectively connected to the return oil pumps through pipelines, and then connected to the oil tank. The front bearing cavity is also provided with a front bearing cavity exhaust port.

[0017] Furthermore, the gas supply system includes a gas source, a pneumatic solenoid valve, an air heater, a flow meter, a gas supply system pressure sensor, and pipelines connected to the sealing cavity and rotating disk cavity of the main body of the experimental platform; the gas supply system is divided into two branches, one of which is a gas supply branch for the sealing cavity and the other is a gas supply branch for the rotating disk cavity.

[0018] The air supply branch of the sealing cavity, after exiting the air source, divides the air supply pipeline into four lines. These four lines are respectively connected to the air supply inside the front bearing cavity sealing cavity, the air supply outside the front bearing cavity sealing cavity, the air supply inside the rear bearing cavity sealing cavity, and the air supply outside the rear bearing cavity sealing cavity. Each line is equipped with a pneumatic solenoid valve and an air supply system pressure sensor. The air supply branch of the rotating disk cavity, after exiting the air source and connecting to the pneumatic solenoid valve, is connected to the inlet of the air heater. The air heater is a vertical heater. The air heater outlet pipeline is divided into two lines, which are then divided into two air supply pipelines. These pipelines are equipped with pneumatic solenoid valves, flow meters, and air supply system pressure sensors, and are respectively connected to the first rotating disk cavity and the third rotating disk cavity through holes H1 and H3. The air supply inside the front bearing cavity seal is connected to the second sealing cavity; the air supply outside the front bearing cavity seal is connected to the first sealing cavity; the air supply inside the rear bearing cavity seal is connected to the third sealing cavity; the air supply outside the rear bearing cavity seal is connected to the fourth sealing cavity; except for the sealing air leaking from the toothed seal, the remaining air is discharged from the rear bearing cavity exhaust.

[0019] The pressure sensors, pneumatic solenoid valves, and flow meters in the gas supply system are integrated and controlled by a PLC, which can adjust the gas pressure and temperature of each gas path and control the gas flow rate of the main path in real time.

[0020] The beneficial effects of this invention are as follows: The experimental system for measuring the sealing pneumatic parameters of a multi-cavity grating air system has a two-way air supply system. One way is dedicated to sealing the bearing cavities, ensuring the normal operation of the experimental platform. The sealing pressure is adjusted to prevent lubricating oil leakage from the bearing cavities. The other air supply system is connected to a heater to heat the incoming air and adjust the temperature at the inlet of the experimental platform. The oil supply system adopts a one-supply, two-return oil supply and return mode, which can smoothly ensure that each bearing cavity can be supplied and returned smoothly. In the event of an emergency, if one bearing cavity cannot return oil, it will not affect the normal return of oil to the other bearing cavity. A gap displacement sensor is used to solve the difficulty of high-frequency, high-resolution dynamic measurement of the geometric deviation of the grating seal, and can display the radial gap of the grating corresponding to each grating seal in real time. By installing pressure and temperature sensors, the physical state at the grating gap and the flow state of the fluid passing through the grating can be accurately understood. It has the function of real-time acquisition of physical parameters such as pressure, temperature, and grating radial gap. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the isometric structure of the present invention; Figure 3 This is a schematic diagram of the rear view structure of the present invention; Figure 4 This is a cross-sectional structural diagram of the present invention; Figure 5 This is a schematic diagram of the probe support structure of the gap displacement sensor of the present invention.

[0022] In the diagram: 1. Motor; 2. Main body of the experimental platform; 3. Oil supply system; 4. Air supply system; 5. Data acquisition unit; 6. Measurement and control system; 7. Slip ring actuator; 8. Hollow shaft; 9. Coupling; 10. Front bearing; 11. Rear bearing; 12. Front bearing housing; 13. Rear bearing housing; 14. Temperature sensor; 15. Pressure sensor; 16. Clearance displacement sensor; 17. Rear bearing cavity return oil pipeline; 18. Outer side of the rear bearing cavity seal. 19. Rear bearing cavity oil supply line; 20. Rear bearing cavity exhaust; 21. Rear bearing cavity sealed inner air supply; 22. Front bearing cavity exhaust port; 23. Front bearing cavity oil supply line; 24. Front rotor support assembly; 25. Rear rotor support assembly; 26. H1 hole; 27. Front bearing cavity sealed inner air supply; 28. Front bearing cavity sealed outer air supply; 29. ​​Front bearing cavity oil return line; 30. H4 hole; 31. H3 hole; 32. H2 hole; 33, rear bearing cavity; 34, third grate seal; 35, second grate seal; 36, first grate seal; 37, front bearing cavity; 38, rotor structure; 39, outer casing; 40, first rotating disk cavity; 41, second rotating disk cavity; 42, third rotating disk cavity; 43, fourth rotating disk cavity; 44, first sealing cavity; 45, second sealing cavity; 46, annular cavity; 47, third sealing cavity; 48, fourth sealing cavity; 301. Oil tank; 302. Oil supply pump; 303. Oil return pump; 401. Air source; 402. Pneumatic solenoid valve; 403. Air heater; 404. Flow meter; 405. Air supply system pressure sensor; 3401. Third grate housing; 3402. Third grate disc; 3501. Second grate housing; 3502. Second grate disc; 3601. First grate housing; 3602. First grate disc; 1601. Probe bracket. Detailed Implementation

[0023] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0024] To achieve the above objectives, the present invention provides the following specific embodiments: Figure 1-5As shown, the experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system includes a horizontally arranged experimental platform body 2. The hollow shaft 8 at the front end of the experimental platform body 2 is connected to the motor 1 through a coupling 9. The rear end of the experimental platform body 2 is connected to the slip ring actuator 7. An oil supply system 3, an air supply system 4, and a measurement and control system 6 are also arranged around the experimental platform body 2. The main body 2 of the experimental platform includes a hollow shaft 8, a toothed seal composed of a toothed housing and a toothed disc, an outer housing 39, a front bearing 10, a rear bearing 11, a front bearing seat 12, and a rear bearing seat 13; the hollow shaft 8, the toothed seal composed of the toothed housing and the toothed disc, the front bearing 10, and the rear bearing 11 form a rotor system 38; The toothed gear housing is equipped with pressure sensors and temperature sensors for measuring the cavity pressure and temperature of the sealing cavity, annular cavity and rotating disk cavity of the toothed gear sealing. The data measured by the pressure sensors and temperature sensors, as well as the data transmitted via the slip ring actuator 7, are all entered into the measurement and control system 6 through the data acquisition unit 5. The experimental platform body 2 is mounted on the front rotor support assembly 24 and the rear rotor support assembly 25.

[0025] Furthermore, the main body 2 of the experimental platform forms 4 sealing cavities, 1 annular cavity, 2 bearing cavities, and 4 rotating disk cavities; the sealing cavities include a first sealing cavity 44, a second sealing cavity 45, a third sealing cavity 47, and a fourth sealing cavity 48; the annular cavity 46 is a single cavity; the bearing cavities include a front bearing cavity 37 and a rear bearing cavity 33; and the rotating disk cavities include a first rotating disk cavity 40, a second rotating disk cavity 41, a third rotating disk cavity 42, and a fourth rotating disk cavity 43. The aforementioned tooth seal includes a first tooth seal 36, a second tooth seal 35, and a third tooth seal 34, with corresponding tooth housings of a first tooth housing 3601, a second tooth housing 3501, and a third tooth housing 3401; and corresponding tooth discs of a first tooth disc 3602, a second tooth disc 3502, and a third tooth disc 3402.

[0026] Furthermore, the first toothed plate 3602 of the first toothed seal 36 has oblique teeth and a stepped tooth type. The second toothed plate 3502 of the second toothed seal 35 has oblique teeth and a stepped tooth type. The number of tooth steps is less than that of the first toothed seal 36. The third toothed plate 3402 of the third toothed seal 34 has trapezoidal teeth and a straight tooth type. The tooth radii of the first toothed seal 36, the second toothed seal 35, and the third toothed seal 34 decrease sequentially.

[0027] Furthermore, the front bearing cavity 37 is the bearing cavity where the front bearing 10 is located, and the rear bearing cavity 33 is the bearing cavity where the rear bearing 11 is located; the first sealing cavity 44 is on the front side of the front bearing cavity 37, the second sealing cavity 45 is on the rear side of the front bearing cavity 37, the third sealing cavity 47 is on the front side of the rear bearing cavity 33, and the fourth sealing cavity 48 is on the rear side of the rear bearing cavity 33; the first rotating disk cavity 40 is located on the front side of the first toothed seal 36, the second rotating disk cavity 41 is located between the first toothed seal 36 and the second toothed seal 35, the third rotating disk cavity 42 is located between the second toothed seal 35 and the third toothed seal 34, and the fourth rotating disk cavity 43 is located on the rear side of the third toothed seal 34.

[0028] Furthermore, the first toothed housing 3601, the second toothed housing 3501, and the third toothed housing 3401 are equipped with pressure sensors 15 and temperature sensors 14 for measuring the pressure and temperature between the teeth of each tooth in the toothed sealing process; the pressure sensors 15 are used to capture the pressure pulsation of the leaking airflow between the teeth of each tooth, and the temperature sensors 14 are used to monitor the temperature distribution of the airflow between the teeth of each tooth.

[0029] The first grate housing 3601 is equipped with 10 pressure sensors 15 arranged according to the stepped grate structure to measure the pressure between the teeth of the first grate seal 36, and 15 temperature sensors 14 arranged to measure the fluid temperature between the teeth of the first grate seal 36. The second grate housing 3501 is equipped with 4 pressure sensors 15 arranged according to the stepped grate structure to measure the pressure between the teeth of the first grate seal 35, and 9 temperature sensors 14 arranged to measure the fluid temperature between the teeth of the first grate seal 35. Sensor 14 measures the fluid temperature between the teeth of each tooth in the second grate seal 35; nine pressure sensors 15 are arranged on the third grate housing 3401 according to the straight-through grate structure to measure the pressure between the teeth of each tooth in the first grate seal 35, and ten temperature sensors 14 are arranged to measure the fluid temperature between the teeth of each tooth in the third grate seal 34; the first grate housing 3601, the second grate housing 3501, and the third grate housing 340... A surface-mount temperature sensor 14 is used to collect the surface temperature of the toothed gear housing. The surface-mount temperature sensors 14 on the first toothed gear disc 3602, second toothed gear disc 3502, and third toothed gear disc 3402 are used to collect the surface temperature of the toothed gear discs, reflecting the temperature of the toothed gears. The temperature sensor 14 measuring the surface temperature of the toothed gear disc extends into the hollow shaft 8. The extension line of the temperature sensor 14 is connected to the data line of the data acquisition unit 5 through the brush on the slip ring actuator 7. The data acquisition unit 5 transmits the collected temperature signal to the measurement and control system 6. The measurement data from the temperature sensor 14 measuring the fluid temperature between each toothed gear, the measurement data from the temperature sensor 14 measuring the surface temperature of the toothed gear housing, the measurement data from the pressure sensor 15 measuring the pressure between each toothed gear, and the data transmitted via the slip ring actuator 7 are all entered into the measurement and control system 6 through the data acquisition unit 5.

[0030] The gap between the toothed discs and the toothed housing of the first toothed seal 36, the second toothed seal 35, and the third toothed seal 34 is measured by a gap displacement sensor 16. The gap displacement sensor 16 calculates the rotor-stator gap by the time difference between emitting and receiving infrared lasers within the gap. The gap displacement sensor 16 is fixed by a special probe bracket 1601. The data measured by the gap displacement sensor 16 and the data transmitted via the slip ring actuator 7 are both entered into the measurement and control system 6 through the data acquisition unit 5.

[0031] Furthermore, the oil supply system 3 includes an oil tank 301, an oil supply pump 302, two return oil pumps 303, and pipelines connected to the bearing cavities on both sides of the main body 2 of the experimental platform. After the oil tank 301 is connected to the oil supply pump 302 through the pipeline, it is divided into two lines and connected to the front bearing cavity oil supply pipeline 23 and the rear bearing cavity oil supply pipeline 19 at the oil supply inlet of the front bearing cavity 37 and the rear bearing cavity 33 of the main body 2 of the experimental platform. The front bearing cavity return oil pipeline 29 and the rear bearing cavity return oil pipeline 17 at the oil return outlet of the front bearing cavity 37 and the rear bearing cavity 33 are respectively connected to the return oil pump 303 through the pipeline, and then connected to the oil tank 301. The front bearing cavity 37 is also provided with a front bearing cavity exhaust port 27.

[0032] Furthermore, the gas supply system 4 includes a gas source 401, a pneumatic solenoid valve 402, an air heater 403, a flow meter 404, a gas supply system pressure sensor 405, and pipelines connected to the sealing cavity and the rotating disk cavity of the main body 2 of the experimental platform; the gas supply system 4 is divided into two branches, one of which is a gas supply branch for the sealing cavity and the other is a gas supply branch for the rotating disk cavity.

[0033] The air supply branch of the sealing cavity, after exiting from the air source 401, divides the air supply pipeline into four lines. The four air supply pipelines are respectively connected to the air supply 27 inside the sealing cavity of the front bearing cavity, the air supply 28 outside the sealing cavity of the front bearing cavity, the air supply 21 inside the sealing cavity of the rear bearing cavity, and the air supply 18 outside the sealing cavity of the rear bearing cavity. Each pipeline is equipped with a pneumatic solenoid valve 402 and an air supply system pressure sensor 405. The air supply branch of the rotating disk cavity, after exiting from the air source 401 and connecting to the pneumatic solenoid valve 402, is connected to the inlet of the air heater 403. The air heater 4 is a vertical heater. The outlet pipeline of the air heater 4 is divided into two lines, which are then divided into two air supply pipelines. The pipelines are equipped with a pneumatic solenoid valve 402, a flow meter 404, and an air supply system pressure sensor 405, and are respectively connected to the first rotating disk cavity 40 and the third rotating disk cavity 42 through the H1 hole 26 and the H3 hole 31. The air supply 27 on the inner side of the front bearing cavity seal is connected to the second sealing cavity 45; the air supply 28 on the outer side of the front bearing cavity seal is connected to the first sealing cavity 44; the air supply 21 on the inner side of the rear bearing cavity seal is connected to the third sealing cavity 47; the air supply 18 on the outer side of the rear bearing cavity seal is connected to the fourth sealing cavity 48; except for the sealing air leaking from the toothed seal, the remaining air is discharged from the exhaust 20 of the rear bearing cavity.

[0034] The pressure sensors, pneumatic solenoid valves and flow meters on the gas supply system 4 are integrated and controlled by a PLC, which can adjust the gas supply pressure and temperature of each gas path, and can also control the gas supply flow of the main path in real time.

[0035] The main body 2 of the experimental platform is divided into 11 cavities. The flow paths of the two sealed cavities are the same under the conditions of one inlet and one outlet and two inlet and two outlet. The difference lies in the flow path of the middle rotating disk cavity.

[0036] 1) Under the condition of one inlet and one outlet, the gas enters the first rotating disk cavity 40 from the H1 hole 26, and splits into two paths. One path enters the annular cavity 46; the other path enters the second rotating disk cavity 41, passes through three grate teeth for sealing and four rotating disk cavities, and exits from the H2 hole 32.

[0037] 2) Under the condition of two inlets and two outlets, the gas enters from hole H1 26 and hole H3 31. The flow path of hole H1 26 is also divided into two paths, one of which enters the annular cavity 46; the other enters the second rotating disk cavity 41 and exits from hole H4 30. The flow path of hole H3 31 is divided into two paths, which flow out from the grate seals on both sides, one of which exits from hole H2 32 and the other exits from hole H4 30.

[0038] To study the impact of geometric deviation on the air system, it is necessary to control the geometric dimensions of the first grate seal 36, the second grate seal 35, and the third grate seal 34. For ease of operation and convenience, the geometric deviation of the grate seals can be altered by replacing the corresponding grate housings (first grate housing 3601, second grate housing 3501, and third grate housing 3401). During the experiment, firstly, the pneumatic solenoid valve 402 in the rotating disk cavity air supply branch of the air supply system 4 is opened to supply the main airflow, ensuring a suitable pressure is established within the experimental platform. Then, the pneumatic solenoid valves 402 for the four sealing air supply branches in the sealing cavity air supply branch are opened, and the sealing pressure is adjusted to ensure no leakage in the bearing cavity. Next, the oil return and supply functions of the oil supply system 3 are activated to lubricate the main body 2 of the experimental platform. Afterward, motor 1 is started, and its speed is adjusted to a suitable level before operation. Adjust the pneumatic solenoid valve 402 of the air supply branch of the rotating disc cavity to adjust the air supply pressure and flow rate to the required operating conditions. After stabilization, collect and record all measured parameters: pressure, temperature, and gap.

[0039] During the experiment, measurements can be performed under two conditions: one-in-one-out and two-in-two-out. After the required measurement conditions are completed under both conditions, the geometric deviation is accurately injected by replacing the toothed gear housings of different sizes (first toothed gear housing 3601, second toothed gear housing 3501, and third toothed gear housing 3401). The above measurement process is repeated, and the measurement results are compared with the measurement results of the reference model, thereby providing the impact of the geometric deviation on the air system.

[0040] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system, characterized in that, The experimental platform includes a horizontally set experimental platform body. The hollow shaft at the front end of the experimental platform body is connected to the motor via a coupling. The rear end of the experimental platform body is connected to the slip ring actuator. An oil supply system, an air supply system, and a measurement and control system are also set up around the experimental platform body. The main body of the experimental platform includes a hollow shaft, a tooth seal composed of a toothed housing and a toothed disc, an outer housing, a front bearing, a rear bearing, a front bearing housing, and a rear bearing housing; the hollow shaft, the tooth seal composed of the toothed housing and the toothed disc, the front bearing, and the rear bearing constitute the rotor system. The toothed gear housing is equipped with pressure sensors and temperature sensors for measuring the cavity pressure and temperature of the sealing cavity, annular cavity and rotating disk cavity of the toothed gear. The data measured by the pressure sensors and temperature sensors, as well as the data transmitted via the slip ring actuator, are all entered into the measurement and control system through the data acquisition unit. The main body of the experimental platform is mounted on the front rotor support assembly and the rear rotor support assembly.

2. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 1, characterized in that, The main body of the experimental platform forms 4 sealing cavities, 1 annular cavity, 2 bearing cavities, and 4 rotating disk cavities; the sealing cavities include a first sealing cavity, a second sealing cavity, a third sealing cavity, and a fourth sealing cavity; the annular cavity is one; the bearing cavities include a front bearing cavity and a rear bearing cavity; and the rotating disk cavities include a first rotating disk cavity, a second rotating disk cavity, a third rotating disk cavity, and a fourth rotating disk cavity. The tooth seal includes a first tooth seal, a second tooth seal, and a third tooth seal, and the tooth housings corresponding to the tooth seals are the first tooth housing, the second tooth housing, and the third tooth housing, respectively; the corresponding tooth discs are the first tooth disc, the second tooth disc, and the third tooth disc, respectively.

3. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 2, characterized in that, The first grate plate sealed by the first grate has oblique teeth and a stepped tooth type. The second grate plate sealed by the second grate has oblique teeth and a stepped tooth type. The number of grate steps is less than that of the first grate sealing. The third grate plate sealed by the third grate has trapezoidal teeth and a straight tooth type. The grate radii of the first, second, and third grate sealing decrease sequentially. The front bearing cavity is the bearing cavity where the front bearing is located, and the rear bearing cavity is the bearing cavity where the rear bearing is located; the first sealing cavity is on the front side of the front bearing cavity, the second sealing cavity is on the rear side of the front bearing cavity, the third sealing cavity is on the front side of the rear bearing cavity, and the fourth sealing cavity is on the rear side of the rear bearing cavity; the first rotating disk cavity is located on the front side of the first grate seal, the second rotating disk cavity is located between the first grate seal and the second grate seal, the third rotating disk cavity is located between the second grate seal and the third grate seal, and the fourth rotating disk cavity is located on the rear side of the third grate seal.

4. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 2, characterized in that, The first, second, and third grate housings are equipped with pressure sensors and temperature sensors for measuring the pressure and temperature between the teeth of each grate in the grate seal. The pressure sensors are used to capture the pressure pulsation of the leaking airflow between the teeth of each grate, and the temperature sensors are used to monitor the temperature distribution of the airflow between the teeth of each grate.

5. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 4, characterized in that, Ten pressure sensors are installed on the first grate housing according to the stepped grate structure to measure the pressure between the teeth of each grate when the first grate is sealed, and 15 temperature sensors are installed to measure the fluid temperature between the teeth of each grate when the first grate is sealed. Four pressure sensors are installed on the second grate housing according to the stepped grate structure to measure the pressure between the teeth of the first grate sealing each tooth, and nine temperature sensors are installed to measure the fluid temperature between the teeth of the second grate sealing each tooth. Nine pressure sensors are installed on the third grate housing according to the straight-through grate structure to measure the pressure between the teeth of the first grate sealing each tooth, and ten temperature sensors are installed to measure the fluid temperature between the teeth of the third grate sealing each tooth. Temperature sensors for collecting surface temperature data of the first, second, and third sieve housings are mounted on their surfaces; temperature sensors for collecting surface temperature data of the first, second, and third sieve discs are also mounted on their surfaces, reflecting the temperature of the sieves. A temperature sensor that measures the surface temperature of the toothed disc extends into the hollow shaft. The extension line of the temperature sensor is connected to the data line of the data acquisition unit through the brush on the slip ring actuator. The data acquisition unit transmits the acquired temperature signal to the measurement and control system. Temperature sensor data measuring the fluid temperature between each grate tooth, temperature sensor data measuring the surface temperature of the grate housing, pressure sensor data measuring the pressure between each grate tooth, and data transmitted via slip ring actuators are all entered into the measurement and control system through a data acquisition unit. The gap between the grate discs and the grate housing of the first, second, and third grate seals is measured using a gap displacement sensor. The gap displacement sensor calculates the rotor-stator gap by the time difference between emitting and receiving infrared lasers within the gap. The gap displacement sensor is fixed by a special probe bracket. The data measured by the gap displacement sensor and the data transmitted via the slip ring actuator are both entered into the measurement and control system through a data acquisition unit.

6. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 1, characterized in that, The oil supply system includes an oil tank, an oil supply pump, two return oil pumps, and pipelines connected to the bearing cavities on both sides of the main body of the experimental platform. After the oil tank is connected to the oil supply pumps through pipelines, it is divided into two lines that are connected to the oil supply inlets of the front and rear bearing cavities of the main body of the experimental platform. The oil return pipelines of the front and rear bearing cavities are connected to the return oil pumps through pipelines, and then connected to the oil tank. The front bearing cavity is also provided with a front bearing cavity exhaust port.

7. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in any one of claims 1-6, characterized in that, The gas supply system includes a gas source, a pneumatic solenoid valve, an air heater, a flow meter, a gas supply system pressure sensor, and pipelines connected to the sealing cavity and rotating disk cavity of the main body of the experimental platform. The gas supply system is divided into two branches, one of which is a gas supply branch for the sealing cavity and the other is a gas supply branch for the rotating disk cavity.

8. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 7, characterized in that, The air supply branch of the sealing cavity, after exiting the air source, divides the air supply pipeline into four lines. These four lines are respectively connected to the air supply inside the front bearing cavity seal, the air supply outside the front bearing cavity seal, the air supply inside the rear bearing cavity seal, and the air supply outside the rear bearing cavity seal. Each line is equipped with a pneumatic solenoid valve and an air supply system pressure sensor. The air supply branch of the rotating disk cavity, after exiting the air source and connecting to the pneumatic solenoid valve, is connected to the inlet of the air heater. The air heater is a vertical heater. The air heater outlet pipeline is divided into two lines, which are then divided into two air supply pipelines. These pipelines are equipped with pneumatic solenoid valves, flow meters, and air supply system pressure sensors, and are respectively connected to the first and third rotating disk cavities through holes H1 and H3. The air supply inside the front bearing cavity seal is connected to the second sealing cavity; the air supply outside the front bearing cavity seal is connected to the first sealing cavity; the air supply inside the rear bearing cavity seal is connected to the third sealing cavity; the air supply outside the rear bearing cavity seal is connected to the fourth sealing cavity; except for the sealing air leaking from the toothed seal, the remaining air is discharged from the rear bearing cavity exhaust.

9. The experimental system for measuring the sealing aerodynamic parameters of a multi-cavity comb air system as described in claim 7, characterized in that, The pressure sensors, pneumatic solenoid valves, and flow meters of each gas supply system are integrated and controlled by a PLC to adjust the gas supply pressure and temperature of each gas path and control the gas supply flow of the main path in real time.

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