Device and method for measuring leakage rate of end face sealing device of rotor engine

Abstract

The invention discloses a leakage rate measuring device and method for a rotor engine end face sealing device. The leakage rate measuring device comprises a pressure stabilizing air source unit, a rotating mechanical unit, an air tightness testing unit and an oil way unit. The air tightness testing unit is used for providing a pressure stabilizing air source with consistent peak pressure in the working process of the rotor machine under the actual working condition; the oil way unit is used for spraying lubricating oil into the rotor cavity; the rotary mechanical unit simulates the relative movement of the rotor engine end face and the end face sealing piece; the measurement of a rotor cavity in the air tightness test unit is equivalent to rotor end face leakage, and the force of the rotor cavity acting on a rotating flat plate can be adjusted by adjusting a one-way manual lifting platform. The acting force is equivalent to the elastic force of a spring of the end face sealing device, and the gas leakage amount is obtained by measuring the pressure drop of the surge tank or through a gas flow meter during the gas tightness test. In the sealing performance test of the sealing oil film, the oil injection quantity to the rotor cavity is continuously changed, and an incidence relation curve between the lubricating oil injection quantity and the sealing leakage quantity of the oil film can be dynamically established.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of dynamic sealing of a rotor engine, in particular to a leakage measurement device and method for an end face sealing device of a rotor engine. BACKGROUND

[0002] In the working process of an engine, in-cylinder swirl has an important influence on the formation of the mixture and the combustion process. A suitable swirl ratio can promote the thorough mixing of fuel and air, speed up the combustion process, improve combustion efficiency, reduce fuel consumption and harmful gas emissions. At present, although there are some technical solutions for variable swirl ratio, most of them are complex in structure, high in cost and limited in control accuracy. For example, some methods that change the shape of the intake port or add additional swirl generating devices not only increase the structural complexity and manufacturing cost of the engine, but also may affect the intake efficiency to some extent. In addition, the traditional single intake port and single valve control mode cannot accurately adjust the swirl ratio according to different engine operating conditions, and cannot fully meet the optimization requirements of the combustion process of the engine under different loads and speeds. Therefore, it is of great practical significance to develop an intake technology that is simple in structure, low in cost and can effectively realize variable swirl ratio.

[0003] With the continuous progress and development of engine technology, especially in the field of rotor engines, the requirements for sealing performance are increasingly stringent. As a new type of internal combustion engine, the rotor engine has significant advantages in high efficiency and miniaturization due to its unique working principle and structural design. One of the core components of the rotor engine is the end face sealing device, which plays a role in preventing gas leakage and ensuring the effective sealing of the gas inside the combustion chamber to improve the combustion efficiency and power performance of the engine. However, the existing end face sealing device of the rotor engine still faces technical difficulties such as unstable sealing effect and inaccurate measurement of leakage. The end face sealing structure of the rotor engine usually relies on the elastic force of the sealing spring to maintain sealing, but the elastic force of the sealing spring, the design of the end face sealing structure and the working environment of the engine (such as in-cylinder pressure, speed, etc.) will have an important influence on the sealing effect. This makes it necessary to find the best match between multiple factors for the optimization of sealing performance, and traditional design methods often fail to do so. Moreover, the elastic force of the sealing spring cannot be increased indefinitely, as excessive elastic force applied to the end face sealing plate will affect the oil film thickness between the sealing plate and the rotor engine rigid body and the frictional resistance between the sealing plate and the rotor engine rigid body, reducing output power and easily causing the phenomenon of cylinder pulling.

[0004] Furthermore, current leakage measurement technologies are relatively limited, often only able to estimate sealing effectiveness through static or indirect methods. Due to the complex dynamic characteristics of rotary engines during operation, existing measurement methods struggle to accurately capture leakage changes under different operating conditions, especially at high speeds and high pressures where leakage variations are more pronounced. Therefore, real-time and accurate leakage measurement, along with adjustments to the sealing structure and sealing springs based on varying operating conditions, is crucial for improving the sealing performance of rotary engines.

[0005] Therefore, there is an urgent need in this field to develop a method and apparatus that can accurately measure the leakage of end-face sealing devices under dynamic operating conditions. Summary of the Invention

[0006] This invention addresses the shortcomings of existing technologies by providing a leakage measurement device and method for the end-face sealing device of a rotary engine. By matching different sealing spring forces, end-face sealing structures, cylinder pressures, and rotational speeds to approximately simulate the end-face sealing environment during the actual operation of a rotary engine, this invention can accurately measure leakage under various operating conditions and adjust sealing parameters in real time based on the measurement results, thereby improving the engine's sealing performance, combustion efficiency, and power performance. This technology not only solves the accuracy problem of traditional measurement methods but also provides technical support for further optimization of rotary engines.

[0007] The first aspect of the present invention is to provide a leakage measurement device for a rotary engine end face sealing device, comprising a pressure stabilizing gas source unit, a rotating machinery unit, and an airtightness testing unit;

[0008] The pressure-stabilizing air source unit is used to provide a pressure-stabilized air source, and the air source pressure is consistent with the peak pressure during the actual working process of the rotor machine.

[0009] The rotating mechanical unit includes a servo drive motor, a coupling, and a helical planetary support reducer. The input end of the helical planetary support reducer is fixedly connected to the output shaft of the servo drive motor via the coupling. The housing of the helical planetary support reducer is mounted on a test bench via a reducer mounting plate. The output shaft of the helical planetary support reducer is connected to a rotating plate. The servo drive motor drives the helical planetary support reducer, which in turn drives the rotating plate to rotate around its output shaft, simulating the relative movement between the rotor engine end face and the end face sealing plate. The other side surface of the rotating plate abuts against the rotor cavity to be tested. The rotating plate simulates the rotor engine end face.

[0010] The airtightness testing unit includes a rotor cavity, a one-way manual lifting platform, and a guide rail slider assembly. The rotor cavity is used to simulate the rotor to be tested, and measuring the leakage of the rotor cavity is equivalent to leakage at the rotor end face. The oil film between the rotor cavity and the rotating plate is equivalent to the oil film between the actual rotor engine end face sealing plate and the engine end face.

[0011] The rotor cavity is detachably connected to a one-way manual lifting platform, which is slidably connected to the guide rail slider assembly. It can drive the rotor cavity to move along the guide rail of the guide rail slider assembly, thereby changing the relative position and contact state between the rotor cavity and the rotating plate in the rotating mechanical unit. The magnitude of the force exerted by the rotor cavity on the rotating plate can be adjusted by adjusting the one-way manual lifting platform. The force is equivalent to the spring force of the end face sealing device, and the force is determined by a pressure sensor located between the one-way manual lifting platform and the rotor cavity fixing plate.

[0012] Furthermore, the airtightness testing unit also includes a bench fixing plate, the bottom surface of which is fixed to the guide rail slider assembly, and a one-way manual lifting platform is provided on its top surface.

[0013] Furthermore, the leakage measurement device also includes a frame unit for supporting the leakage measurement device, including a reducer fixing plate, side viewing windows, a servo motor fixing plate, and a base plate; the base plate is an L-shaped frame plate, including a first base plate parallel to the worktable and a second base plate perpendicular to the first base plate; the reducer fixing plate and the servo motor fixing plate are both vertically fixed on the first base plate of the base plate, and the servo motor fixing plate is used to fix the end of the servo drive motor away from the helical planetary support reducer; the first base plate of the base plate has vertically and symmetrically arranged side viewing windows on both sides, and the side viewing windows are fixedly connected to the sides of the first base plate and the second base plate of the base plate respectively.

[0014] A second aspect of the present invention is to provide a test method for the leakage measurement device in an airtightness test, comprising:

[0015] Pre-charge step: Inflate the pressure stabilizing tank with air until its internal pressure reaches a preset pressure equivalent to the peak operating pressure of the rotary engine;

[0016] Equivalent loading steps: Apply pressure to the contact surface between the rotor cavity and the rotating plate by adjusting the one-way manual lifting platform, and monitor the pressure by the pressure sensor. The difference between the pressure sensor value before and after the change is the magnitude of the pressure applied by the rotor cavity to the rotating plate, which is equivalent to the spring force of the rotor end face sealing device during the actual operation of the rotor engine; and the initial value of the applied pressure is 0, and the final value is equivalent to the spring force of the target rotor end face sealing device.

[0017] Equivalent motion steps: Control the helical planetary support reducer to drive the rotating plate to rotate, and make its maximum linear velocity in the contact area with the rotor cavity consistent with the maximum relative linear velocity between the rotor end face and the cylinder in a real engine;

[0018] Leakage measurement steps: While performing the equivalent motion, the leakage is measured: when the leakage is small, the leakage flow rate is calculated by measuring the pressure drop of the pressure stabilizing tank per unit time; when the leakage is large, the leakage flow rate is read directly by the gas flow meter.

[0019] Furthermore, the device also includes an oil circuit unit for injecting lubricating oil into the rotor cavity. The oil circuit unit includes a pump oil tank, a third check valve, and a liquid flow meter connected by pipelines; the end of the oil circuit unit is connected to the rotor cavity.

[0020] A third aspect of the present invention is to provide a test method for the leakage measurement device in the sealing performance test of a sealing oil film, comprising:

[0021] Pre-charge: Inflate the pressure stabilizing tank with air until its internal pressure reaches a preset pressure equivalent to the peak operating pressure of the rotary engine;

[0022] Oil injection: Adjust the opening of the third check valve to adjust the amount of lubricating oil injected to a target value, and monitor the liquid flow meter in real time to ensure that the amount of oil injected is stable;

[0023] Oil film seal leakage measurement: Under the condition of stable oil injection quantity, the gas in the pressure stabilizing tank is introduced into the rotor cavity, and the gas leakage quantity is measured by the gas flow meter at the same time. The gas leakage quantity characterizes the sealing effect of the oil film under the current oil injection quantity.

[0024] Dynamic performance analysis: The opening of the third one-way valve is changed to adjust to different oil injection quantities. For each different oil injection quantity, the steps of oil injection and oil film seal leakage measurement are repeated. Each oil injection quantity and its corresponding gas leakage quantity are recorded to dynamically establish the correlation curve between the lubricating oil injection quantity and the oil film seal leakage quantity, so as to realize the quantitative analysis of the oil film sealing performance.

[0025] The beneficial effects of this invention are as follows:

[0026] 1. The experimental platform of this invention can simulate the complex environment of high speed and high pressure in the actual operation of a rotary engine, overcoming the limitations of existing testing methods in dynamic testing. Through real-time monitoring and data feedback, it can accurately capture leakage changes in the end-face sealing device, especially under high speed and high load conditions, the test results are closer to actual operating conditions. In addition, by adjusting parameters such as the relative speed of sealing contact, sealing structure, and spring force, the system can optimize sealing performance under different operating conditions, ensuring that the engine maintains the best sealing state under various loads and operating conditions, thereby improving overall power output and combustion efficiency.

[0027] 2. The innovation of this invention in sealing performance testing lies in its real-time data feedback mechanism. This mechanism not only provides accurate leakage measurement in dynamic experiments but also provides direct data for the design and adjustment of sealing devices. Engineers can flexibly adjust the matching between the sealing sheet and the sealing spring under different operating conditions based on experimental data, avoiding over-reliance on traditional fixed design methods and ensuring the long-term stability and reliability of the seal. Simultaneously, precise adjustment of the sealing spring force can avoid problems such as increased frictional resistance and insufficient oil film thickness caused by excessive force, thereby extending the service life of the sealing components.

[0028] 3. The present invention features a compact structure, is easy to integrate and disassemble, and significantly reduces costs compared to traditional testing equipment. The modular design of the test bench makes the experimental device more flexible and user-friendly, adaptable to different testing needs. Furthermore, by separating the human and machine operations through viewing windows at key locations and the airtightness detection system, the test platform boasts high reliability and safety, reducing maintenance and accident risks, and further enhancing the feasibility and economy of the equipment. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the pressure-stabilizing air source unit of the leakage measurement device for the rotor engine end face sealing device;

[0030] Figure 2 This is a schematic diagram of the rotating mechanical unit of the leakage measurement device for the rotor engine end face sealing device;

[0031] Figure 3 This is a schematic diagram of the airtightness test unit of the leakage measurement device for the rotor engine end face sealing device;

[0032] Figure 4 This is a schematic diagram of the rotating mechanical unit, airtightness testing unit, and moving unit of the leakage measurement device for the rotor engine end face sealing device.

[0033] Figure 5This is a schematic diagram showing the positional relationship between the rotor cavity and the rotating plate;

[0034] Figure 6 This is a schematic diagram of the connection pipeline between the lubricating oil and the dynamic measurement of leakage.

[0035] Among them, 1: gas storage tank; 2: pressure reducing valve; 3: pressure stabilizing tank; 4: pressure gauge; 5: gas flow meter; 22: first check valve; 23: second check valve; 6: drive motor base; 7: reducer mounting plate; 8: servo drive motor; 9: coupling; 10: helical planetary support reducer; 11: rotating plate; 12: pressure sensor; 13: one-way manual lifting platform; 14: rotor cavity; 15: rotor cavity mounting plate; 16: guide column; 17: platform mounting plate; 18: viewing window; 19: guide rail slider assembly; 20: servo motor mounting plate; 21: base plate; 24: pump oil tank; 25: third check valve; 26: liquid flow meter. Detailed Implementation

[0036] To make the objectives, technical solutions, beneficial effects, and significant advancements of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings provided in the examples of the present invention. Obviously, all the described embodiments are only some embodiments of the present invention, and not all embodiments. 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.

[0037] In the description of this application, unless otherwise expressly specified and limited, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; the term "multiple" refers to two or more; unless otherwise specified or explained, the terms "connected," "fixed," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, an integral connection, or an electrical connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0038] A leakage measurement device for a rotary engine end face sealing device includes a pressure-stabilized air source unit, a rotating machinery unit, an airtightness testing unit, and a frame unit.

[0039] A rotor cavity 14 is prepared in advance, mimicking the shape and size of the rotor to be tested; and a rotating plate 11 is prepared according to the end face of the rotor engine for subsequent testing.

[0040] like Figure 1As shown, the pressure-stabilizing gas source unit includes a gas storage tank 1, a pressure reducing valve 2, a pressure-stabilizing tank 3, a first branch gas path, and a rotor chamber 14 of an airtightness testing unit, which are connected in sequence via pipelines. A first one-way valve 22 and a gas flow meter 5 are connected in series on the first branch gas path; and a second branch gas path is also connected between the pressure-stabilizing tank 3 and the rotor chamber 14, with a second one-way valve 23 installed on the second branch gas path; the first branch gas path and the second branch gas path are connected in parallel.

[0041] The gas storage tank 1 stores high-pressure nitrogen gas, which serves as the gas source for the entire testing system and provides the gas medium for leakage measurement.

[0042] The pressure reducing valve 2 is connected to the outlet of the gas storage tank 1 and is used to reduce the pressure of high-pressure nitrogen gas, ensuring the pressure safety of subsequent gas circuit components and realizing the initial adjustment of gas source pressure.

[0043] The pressure stabilizing tank 3 has a volume of 1L and is connected to the outlet of the pressure reducing valve 2. It can stabilize the gas pressure at approximately 3MPa. A pressure gauge is installed on the tank for real-time pressure monitoring, ensuring a stable output of the gas source pressure and providing a basis for accurate measurement of leakage. Furthermore, the outlet of the pressure stabilizing tank is divided into a first branch gas path and a second branch gas path.

[0044] The gas flow meter 5 monitors the gas flow parameters in real time, with a range of 0.02-2 L / min, and can accurately measure the gas flow rate entering the rotor cavity.

[0045] The first one-way valve 22 and the second one-way valve 23 control the opening and closing of the air intake.

[0046] like Figure 2 As shown, the rotating mechanical unit includes a servo drive motor 8, a coupling 9, and a helical planetary support reducer 10. The input end of the helical planetary support reducer 10 is fixedly connected to the output shaft of the servo drive motor 8 via the coupling 9 to achieve coaxial transmission. The housing of the helical planetary support reducer 10 is rigidly mounted on the frame unit via a reducer fixing plate 7 to ensure stability during transmission. The output shaft of the helical planetary support reducer 10 is connected to a rotating plate 11, thereby transmitting power to the rotating plate 11 and driving it to rotate. The other side surface of the rotating plate 11 is used to abut against the rotor cavity 14 to be tested. Since the helical planetary support reducer 10 can withstand a load exceeding 400N, it can effectively support the rotating plate 11 and ensure that the rotating plate does not tilt when subjected to different axial forces. Driven by the servo drive motor 8, the rotating plate 11 rotates around the output shaft, replacing the rotor end of the rotor engine. The rotation of the rotating plate 11 replaces the relative movement between the rotor engine end face and the end face sealing plate.

[0047] like Figure 3As shown, the airtightness testing unit includes a rotor cavity 14, a one-way manual lifting platform 13, a guide rail slider assembly 19, and a platform fixing plate 17.

[0048] The rotor cavity 14 is used to simulate the working environment of the oil film seal of the rotor under test. It is the core cavity for forming the lubricating oil film and measuring the gas leakage. By measuring the leakage of the rotor cavity, the leakage of the rotor end face is equivalent to that of the rotor end face. The rotor cavity creates the moment when the pressure is the greatest during the actual operation of the rotor engine. The oil film between the rotor cavity and the rotating plate is equivalent to the oil film between the end face seal of the actual rotor engine and the end face of the engine.

[0049] The bottom surface of the frame fixing plate 17 is fixed to the guide rail slider assembly 19, and a one-way manual lifting platform 13 is provided on its top surface. The one-way manual lifting platform 13 is detachably connected to the rotor cavity 14. By adjusting the one-way manual lifting platform 13, the magnitude of the force exerted by the rotor cavity 14 on the rotating plate 11 can be controlled to achieve a small deformation. Different small deformations can achieve different forces, which can be equivalent to the spring force of the end face sealing device. The specific value is determined by measuring the pressure sensor 12 located between the one-way manual lifting platform 13 and the rotor cavity fixing plate 15, thereby realizing the airtightness test of the spring force of the rotor end face sealing device at different times.

[0050] The rotor cavity 14 is detachably fixed to the rotor cavity fixing plate 15 by bolts. One end of each of the four guide posts 16 is fixed to the four sides of the rotor cavity fixing plate 15 on the side away from the rotor cavity 14 by mounting bolts, and the other end of each guide post 16 is fixedly connected to the frame fixing plate 17 and the guide rail slider assembly 19, respectively.

[0051] The bottom of the guide rail slider assembly 19 is fixedly mounted on the bottom wall of the frame unit, and the top of the guide rail slider assembly 19 has a slide rail and a slider (the movement direction of the slide rail is perpendicular to the movement of the first base plate of the base plate 21). The guide post 16 and the platform fixing plate 17 are sequentially and fixedly connected to the slider of the guide rail slider assembly 19 by bolts, so that the rotor cavity 14 can move vertically up and down along the slide rail. By moving up and down, the relative position and contact state between the rotor cavity 14 and the rotating plate 11 in the rotating machinery unit can be changed, thereby realizing different airtightness tests.

[0052] like Figure 4As shown, the frame unit includes a reducer fixing plate 7, side viewing windows 18, a servo motor fixing plate 20, and a base plate 21. The base plate 21 is an L-shaped frame plate, including a first base plate parallel to the workbench and a second base plate perpendicular to the first base plate. The reducer fixing plate 7 and the servo motor fixing plate 20 are both vertically fixed to the first base plate of the base plate 21. The servo motor fixing plate 20 is used to fix the end of the servo drive motor 8 away from the helical planetary support reducer 10. The reducer fixing plate 7 has through holes for passing through and fixing the body of the helical planetary support reducer 10. Side viewing windows 18 are vertically and symmetrically arranged on both sides of the first base plate of the base plate 21. The side viewing windows 18 are fixedly connected to the sides of the first and second base plates of the base plate 21, respectively. The side viewing windows are made of acrylic sheets, allowing clear observation of the contact between the rotor cavity 14 and the rotating plate 6. The frame unit prevents the entire platform from tilting.

[0053] The leakage measurement device of the rotor engine end face sealing device is used in the rotor end face sealing device of an elliptical rotor engine, which includes a cylinder block, an elliptical rotor, an end face sealing device, and a spark plug. The end face sealing device includes an end sealing plate and a spring. End face sealing grooves are formed on both end faces of the elliptical rotor, and the cross-section of the end face sealing grooves is rectangular. The end face sealing plate is confined within the end face sealing groove, and the outer contour of the end face sealing plate is adapted to the cross-sectional shape of the end face sealing groove, allowing it to slide slightly within the end face sealing groove in a direction perpendicular to the rotor end face (i.e., axial direction). The spring is disposed in a blind hole or groove within the rotor to provide a continuous clamping force to the end face sealing plate.

[0054] The specific working process of the leakage measurement device for the rotary engine end face sealing device in the airtightness test is as follows:

[0055] 1. Pre-inflation provides a stable air supply.

[0056] Before testing the leakage of the rotor end face sealing device, it is necessary to fill the pressure tank 3 with gas in advance. The pressure inside the tank is displayed by the pressure gauge 4 on the pressure tank 3. The size of the tank is determined according to the actual amount of gas leakage at the rotor end face. It is preferred to use a gas storage tank as a pressure tank. The specific filling pressure is consistent with the peak pressure during the actual working process of the rotor machine. After all the equipment is debugged, open the pressure reducing valve 2 and the second one-way valve 23 to start filling. After reaching the set pressure requirement, open the first one-way valve 22 and close the second one-way valve 23. The gas flow meter 5 starts to test the flow rate.

[0057] 2. Adjust the spring force of the equivalent rotor end face sealing device.

[0058] After fixing the rotating plate and rotor cavity, the rotor cavity 14 is pressed onto the rotating plate 11 by adjusting the height of the one-way manual lifting platform 13. The pressure sensor 12 changes its measurement value as the one-way manual lifting platform 13 is adjusted. The lifting of the one-way manual lifting platform 13 stops when the pressure reaches the target requirement. The difference between the pressure sensor 12 value before and after the change is the pressure exerted by the rotor cavity 14 on the rotating plate 11, equivalent to the spring force of the rotor end face sealing device during actual rotor engine operation. The initial value of the pressure sensor 12 is set to 0, meaning no force is applied initially. The final value is obtained when the pressure reaches the preset value (equivalent to the spring force of the rotor end face sealing device during actual rotor engine operation).

[0059] 3. Adjust the relative speed of the equivalent rotor end faces

[0060] In the actual design of the rotor profile, a Cartesian coordinate system is established with the center of the rotor profile as the origin. The coordinates of the points on the rotor profile are set as (x0, y0). An envelope is formed by a rotation angle v, where v∈[0-6π]. The equation of the rotor profile is:

[0061]

[0062]

[0063] Where e is the eccentricity, m; R is the creation radius, m; and a is the translation distance, m.

[0064] like Figure 5 As shown, in order to ensure that the contact state between the rotor end face and the rotating plate 11 is more consistent with the contact state between the rotor end face and the cylinder block during the actual operation of the rotary engine, it is necessary to ensure that the maximum linear velocity v0 of the contact part between the rotor cavity 14 and the rotating plate 11 is consistent with the relative maximum linear velocity v1 between the rotor end face and the cylinder block during the actual operation of the rotary engine. The maximum linear velocity v0 is expressed by the formula:

[0065]

[0066] Where L is the distance between the output shaft center of the helical planetary gear reducer 10 and the rotor profile center, in meters; ω is the output shaft speed of the helical planetary gear reducer 10, in rpm.

[0067] The maximum linear velocity v1 can be expressed by the formula:

[0068]

[0069] 4. Calculation of leaked gas flow rate

[0070] Because the leakage of this device is relatively small when the spring force of the bellows in the rotor engine end-face sealing device is large (i.e., when the pressure applied by the one-way manual lifting platform 13 to the rotor cavity 14 onto the rotating plate 11 is large), the leakage is small. Therefore, the gas flow meter 5 may have a large error when the gas flow rate is low. In this case, it is necessary to observe the reading of the pressure gauge 4 installed on the pressure stabilizing tank 3, and calculate the leaked gas flow rate Q by recording the pressure difference ΔP at the beginning and end of the experiment and the total experimental time, thereby verifying the measurement value of the gas flow meter 5.

[0071]

[0072] Where P0 is the initial pressure of the pressure stabilizing tank, MPa; V is the volume of the pressure stabilizing tank, L; and t is the experimental duration, s.

[0073] When the pressure applied by the one-way manual lifting platform 13 to the rotor cavity 14 is small, the leakage is large. At this time, the leakage gas flow rate can be measured by the gas flow meter 5.

[0074] The test method for the leakage measurement device in the sealing performance test of the sealing oil film includes:

[0075] like Figure 6 As shown, when dynamically measuring lubricating oil and leakage, it is necessary to... Figure 1 An oil circuit unit is added to the leakage measurement device of the rotor engine end face sealing device shown. The oil circuit unit includes a hydraulic integrated pump oil tank 24, a third one-way valve 25, and a liquid flow meter 26 connected by pipelines. The end of the oil circuit unit is connected to the rotor cavity 14, allowing lubricating oil to be sprayed into the rotor cavity to form an oil film sealing structure. The oil pressure of the oil circuit is adjustable within the range of 0-10MPa to meet the testing requirements of oil film sealing performance under different oil pressure conditions.

[0076] The hydraulic integrated pump oil tank 24 is used to store lubricating oil and has a high-pressure lubricating oil output function, which can drive lubricating oil into the oil circuit to provide high-pressure lubricating oil for the formation of oil film.

[0077] The third check valve 25 is connected to the outlet end of the hydraulic integrated pump oil tank. By matching different check valve openings, it can achieve precise control of the amount of lubricating oil injected, thereby adjusting the formation state of the oil film in the rotor cavity.

[0078] Liquid flow meter 26: connected to the outlet end of the third check valve, used to monitor the amount of lubricating oil injected in real time, and to help determine the relationship between the amount of oil injected and the oil film sealing effect.

[0079] The specific working process of the leakage measurement device for the rotary engine end face sealing device in the oil film airtightness test is as follows:

[0080] S1: Pre-inflation provides a stable air supply.

[0081] Before testing the leakage of the rotor end face sealing device, it is necessary to fill the pressure stabilizing tank 3 with gas in advance. The pressure inside the tank is displayed by the pressure gauge 4 on the pressure stabilizing tank 3. The size of the tank is determined according to the actual amount of gas leakage at the rotor end face. It is preferred to use an air storage tank as a pressure stabilizing tank. Observe the pressure gauge on the pressure stabilizing tank. When the pressure stabilizes at about 3MPa, the pre-stabilization process of the air circuit pressure is completed, which provides a stable air source pressure for subsequent leakage measurement.

[0082] Then, the pressure reducing valve 2 and the second check valve 23 are opened to start inflation. After the set pressure requirement is reached, the first check valve 22 is opened and the second check valve 23 is closed. The gas flow rate is measured by the gas flow meter 5 with a range of 0.02-2L / min to obtain the initial leakage reference value, so as to compare the influence of the oil film seal on the leakage rate later.

[0083] S2: Initial recording of fuel injection quantity

[0084] The lubricating oil output from the hydraulic integrated pump oil tank 24 controls the injection quantity by adjusting the opening of the third check valve 25 (the oil pressure in the oil circuit is adjustable within the range of 0-10MPa). The current injection quantity value is monitored and recorded in real time by the liquid flow meter to ensure the accuracy and repeatability of the injection quantity control.

[0085] S3: Measurement of leakage under oil film seal

[0086] When the lubricating oil injection quantity corresponding to a certain opening degree of the third check valve 25 stabilizes, the first check valve 22 is opened and the second check valve 23 is closed, allowing nitrogen gas to enter the rotor chamber through the first check valve 22. At this time, the flow data of the gas flow meter 5 is read in real time. This flow value represents the amount of gas leakage after the oil film seal under the corresponding injection quantity. The smaller the flow, the better the oil film sealing effect under the injection quantity.

[0087] S4: Repeat step S3 under multiple operating conditions. According to the preset oil injection quantity requirements, adjust the third check valve to different opening degrees to obtain different lubricating oil injection quantities. Measure and record the gas flow data corresponding to each oil injection quantity. In this way, dynamically establish the relationship curve between lubricating oil injection quantity and oil film seal leakage (characterized by gas flow). Comprehensively explore the changing law of oil film sealing performance under different oil injection quantities and realize dynamic quantitative analysis of oil film sealing performance.

[0088] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style of the specification is merely for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in the embodiments can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A leakage measurement device for a rotary engine end face sealing device, characterized in that, Includes a pressure-stabilized air source unit, a rotating machinery unit, and an airtightness testing unit; The pressure-stabilizing air source unit is used to provide a pressure-stabilized air source, and the air source pressure is consistent with the peak pressure during the actual working process of the rotor machine. The rotating mechanical unit includes a servo drive motor (8), a coupling (9), and a helical planetary support reducer (10). The input end of the helical planetary support reducer (10) is fixedly connected to the output shaft of the servo drive motor (8) via the coupling (9). The housing of the helical planetary support reducer (10) is mounted on the test bench via a reducer fixing plate (7). The output shaft of the helical planetary support reducer (10) is connected to a rotating plate (11). The servo drive motor (8) is used to drive the helical planetary support reducer (10), and the helical planetary support reducer (10) is used to drive the rotating plate (11) to rotate around the output shaft of the helical planetary support reducer (10), simulating the relative movement between the end face of the rotor engine and the end face sealing plate. The other side surface of the rotating plate (11) abuts against the rotor cavity (14) to be tested. The rotating plate (11) simulates the end face of the rotor engine. The airtightness test unit includes a rotor cavity (14), a one-way manual lifting platform (13), and a guide rail slider assembly (19). The rotor cavity (14) is used to simulate the rotor to be tested. The oil film between the rotor cavity and the rotating plate (11) is equivalent to the oil film between the actual rotor engine end face sealing sheet and the engine end face. The rotor cavity (14) is detachably connected to a one-way manual lifting platform (13), which is slidably connected to the guide rail slider assembly (19). It can drive the rotor cavity (14) to move along the guide rail of the guide rail slider assembly (19) to change the relative position and contact state of the rotor cavity (14) and the rotating plate (11) in the rotating mechanical unit. The magnitude of the force exerted by the rotor cavity (14) on the rotating plate (11) can be adjusted by adjusting the one-way manual lifting platform (13). The force is equivalent to the spring force of the end face sealing device, and the force is determined by the pressure sensor (12) located between the one-way manual lifting platform (13) and the rotor cavity fixing plate (15).

2. The leakage measurement device for the rotor engine end face sealing device according to claim 1, characterized in that, The air tightness test unit also includes a bench fixing plate (17), the bottom surface of which is fixed on the guide rail slider assembly (19), and a one-way manual lifting platform (13) is provided on its top surface.

3. The leakage measurement device for the rotor engine end face sealing device according to claim 1, characterized in that, The leakage measurement device also includes a frame unit for supporting the leakage measurement device, including a reducer fixing plate (7), a side window plate (18), a servo motor fixing plate (20), and a base plate (21); the base plate (21) is an L-shaped frame plate, including a first base plate parallel to the workbench and a second base plate perpendicular to the first base plate; the reducer fixing plate (7) and the servo motor fixing plate (20) are both vertically fixed on the first base plate of the base plate (21), and the servo motor fixing plate (20) is used to fix the end of the servo drive motor (8) away from the helical planetary support reducer (10); the first base plate of the base plate 21 has vertically and symmetrically arranged side window plates (18) on both sides, and the side window plates (18) are fixedly connected to the sides of the first base plate and the second base plate of the base plate (21) respectively.

4. The test method for the leakage measurement device of the rotor engine end face sealing device according to claim 1 in the airtightness test, characterized in that, include: Pre-charge step: Inflate the pressure stabilizing tank (3) with air so that its internal pressure reaches a preset pressure equivalent to the peak working pressure of the rotary engine; Equivalent loading steps: Apply pressure to the contact surface between the rotor cavity (14) and the rotating plate (11) by adjusting the one-way manual lifting platform (13), and monitor the pressure by the pressure sensor (12). The difference between the pressure sensor (12) before and after the change is the magnitude of the pressure applied by the rotor cavity (14) to the rotating plate (11), which is equivalent to the spring force of the rotor end face sealing device during the actual operation of the rotor engine; and the initial value of the applied pressure is 0, and the final value is equivalent to the spring force of the target rotor end face sealing device. Equivalent motion steps: Control the helical planetary support reducer (10) to drive the rotating plate (11) to rotate, and make its maximum linear velocity in the contact area with the rotor cavity (14) consistent with the maximum relative linear velocity between the rotor end face and the cylinder in the real engine; Leakage measurement steps: While performing the equivalent motion, the leakage is measured: when the leakage is small, the leakage flow rate is calculated by measuring the pressure drop of the pressure stabilizing tank (3) per unit time; when the leakage is large, the leakage flow rate is read directly by the gas flow meter (5).

5. The leakage measurement device for the rotor engine end face sealing device according to claim 1, characterized in that, The device also includes an oil circuit unit for injecting lubricating oil into the rotor cavity (14). The oil circuit unit includes a pump oil tank (24), a third check valve (25), and a liquid flow meter (26) connected by a pipeline. The end of the oil circuit unit is connected to the rotor cavity (14).

6. The test method for measuring the leakage of the rotor engine end face sealing device according to claim 5 in the sealing performance test of the sealing oil film, characterized in that... include: Pre-charge: Inflate the pressure stabilizing tank (3) to make its internal pressure reach a preset pressure equivalent to the peak working pressure of the rotary engine; Oil injection: Adjust the opening of the third check valve (25) to adjust the amount of lubricating oil injected to a target value, and monitor it in real time through the liquid flow meter (26) to ensure that the amount of oil injected is stable; Oil film seal leakage measurement: Under the condition of stable oil injection, the gas in the pressure stabilizing tank (3) is introduced into the rotor cavity (14), and the gas leakage is measured by the gas flow meter (5). The gas leakage represents the sealing effect of the oil film under the current oil injection. Dynamic performance analysis: Change the opening of the third check valve (25) to adjust to different oil injection quantities. For each different oil injection quantity, repeat the steps of oil injection and oil film seal leakage measurement, and record each oil injection quantity and its corresponding gas leakage quantity to dynamically establish the correlation curve between the lubricating oil injection quantity and the oil film seal leakage quantity, so as to realize the quantitative analysis of the oil film sealing performance.

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