An aeroengine seal test apparatus

Abstract

The application provides an aero-engine sealing test device, which at least comprises a mechanical main body, a lubricating system, a gas supply and air extraction system, a test system, a control system, an operating platform, a low-temperature simulation system, an oil mist treatment system and a monitoring system; the mechanical main body comprises a high-speed motor, a high-speed adapter section and a dynamic attitude test bench; the high-speed adapter section transmits power of the high-speed motor to a sealing test piece; and the dynamic attitude test bench adjusts the attitude changes of pitch and roll required by the test; the lubricating system is in bidirectional communication with the high-speed adapter section, so that lubricating oil can circulate in the lubricating system and the high-speed adapter section; the gas supply and air extraction system is in communication with the high-speed adapter section and is used for providing a high-temperature, high-pressure or vacuum environment; the aero-engine sealing test device can simulate full working condition conditions of aero-engine pitch, roll and other attitudes, and can facilitate the leakage, friction, wear and life test under the variable working condition conditions through the coordinated control of multiple parameters such as rotating speed, temperature, pressure difference and attitude; and the test results are more real and reliable compared with the fixed parameter test results.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engines, and particularly relates to a sealing test device for an aero-engine. BACKGROUND

[0002] The sealing device of an aero-engine is a relatively complex working system, and its performance, including leakage, friction, wear and life, is not only related to the structure of the sealing device itself, but also closely related to external working conditions such as rotating speed, temperature, pressure difference and attitude. At present, the influence of various factors on the sealing performance is usually studied through engine sealing tests, and the objective actual situation of the sealing device in working is comprehensively reflected.

[0003] Figure 1 The bearing cavity sealing test device shown is a common sealing tester in the prior art, mainly composed of a tester main body, an oil system, an air system, an electrical control, a test, a data acquisition and a monitoring system. At present, the sealing tester can only fix parameters such as temperature, pressure and attitude, and then adjust the rotating speed to carry out leakage, friction and wear and life tests, and cannot carry out sealing tests with coordinated changes of various parameters simulating actual working conditions of the engine. In fact, the working conditions of the aero-engine are various, including take-off, air slow, ground slow and cruising, and different working states may correspond to different rotating speeds, temperatures, pressures and attitudes. Research shows that the abnormal leakage and wear of the sealing device of the aero-engine mainly occur in the changing process of rotating speed, temperature, pressure and attitude. Therefore, there is a certain gap between the test results and the actual situation, and in addition, the sealing test device cannot simulate sealing tests in high-cold environments. SUMMARY

[0004] In view of the above problems, the present application provides an aero-engine sealing test device, which can simulate sealing tests under full working conditions of the aero-engine in attitudes such as pitching and rolling, and carry out leakage, friction, wear and life tests under variable working conditions through coordinated control of various parameters such as rotating speed, temperature, pressure difference and attitude. The aero-engine sealing test device can simulate the start-up test of the sealing device in high-cold environments, so that the sealing test results are closer to the actual situation, and the test range is effectively expanded.

[0005] According to one aspect of the present application, an aero-engine sealing test device is provided for a sealing test piece, and the aero-engine sealing test device at least comprises:

[0006] a mechanical main body, the mechanical main body comprising a high-speed motor, a high-speed adapter section and a dynamic attitude test bench, wherein the high-speed adapter section transmits power of the high-speed motor to the sealing test piece, and the dynamic attitude test bench adjusts the attitude changes of pitching and rolling required by the test;

[0007] A lubrication system in bidirectional communication with the high-speed adapter section, so that lubricating oil can circulate in the lubrication system and the high-speed adapter section;

[0008] A gas supply and extraction system in communication with the high-speed adapter section for providing a high-temperature (maximum temperature 300℃), high-pressure (normal pressure ~ 2.5 MPa) or vacuum environment (0 ~ -0.042 MPa);

[0009] A test system including a vibration test analysis system for performing vibration test analysis, a hydrodynamic pressure seal test analysis system for performing hydrodynamic pressure seal test, and a data acquisition test system;

[0010] A control system including at least a dynamic attitude test bench control system for controlling a dynamic attitude test bench, and a variable frequency speed drive control system for controlling a high-speed motor;

[0011] A console outputting control instructions, which are received by the control system and sent to corresponding control terminals to automatically change the attitude of the test bench, the gas supply temperature, the gas supply pressure, etc. with the test speed.

[0012] According to an embodiment of the present disclosure, the high-speed adapter section is composed of a gear box and an adapter section.

[0013] According to an embodiment of the present disclosure, the dynamic attitude test bench includes a swing platform, the high-speed motor and the high-speed adapter section are placed on the swing platform, and the test pipeline enters the swing platform from the left and right rotating shaft center holes of the swing platform, respectively.

[0014] According to an embodiment of the present disclosure, an auxiliary oil return cavity is arranged below the high-speed adapter section.

[0015] According to an embodiment of the present disclosure, an oil baffle is installed at the four corners of the oil tank of the high-speed adapter section.

[0016] According to an embodiment of the present disclosure, an oil baffle is installed on the inner wall of the high-speed adapter section.

[0017] According to an embodiment of the present disclosure, a low-temperature simulation system for providing a low-temperature environment required for the test is further included, which leads out a high-temperature gas to adjust the bearing temperature.

[0018] According to an embodiment of the present disclosure, the lowest refrigeration temperature of the low-temperature simulation system is -55℃.

[0019] According to an embodiment of the present disclosure, the pitch control range of the dynamic attitude test bench is -55° ~ +55°, and the roll control range is -55° ~ +55°.

[0020] According to an embodiment of the present disclosure, the air supply flow rate of the aero-engine sealing test device is 0-200 g / s, the maximum air pressure is 2.5 MPa, the air pressure difference control range is-0.042 MPa-1.5 MPa, and the air temperature control range is room temperature-300 DEG C.

[0021] The aero-engine sealing test device of the present application adopts a dynamic attitude test bench, can simulate the attitudes such as pitching and rolling of an aero-engine, and facilitates the sealing test under full working conditions. Through the setting of the air supply and air extraction system in combination with the test system, the sealing test under variable working conditions can be carried out on the coordinated control of various parameters such as rotating speed, temperature, pressure difference and attitude. Through the setting of a low-temperature simulation system, the start-up test of the sealing device can be carried out in a high-cold environment. Compared with the sealing test in the prior art which can only realize the sealing test of fixed temperature, pressure and attitude parameters, the aero-engine sealing test device of the present application is comprehensive in function, accurate in test result and closer to the real situation.

[0022] Additional features and advantages of the application will be set forth in the description that follows, and in part will be apparent from the description, or can be learned by practice of the application. The objectives and other advantages of the application will be realized and attained by the structure particularly pointed out in the description and claims. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0024] Figure 1 It is a common bearing cavity sealing test equipment in the prior art;

[0025] Figure 2 It is a schematic diagram of the sealing test device in the embodiment of the present application;

[0026] Figure 3 It is a schematic diagram of the mechanical main body in the embodiment of the present application;

[0027] Figure 4 It is a schematic diagram of the high-speed transfer section in the embodiment of the present application;

[0028] Figure 5 It is a schematic diagram of the pipeline layout in the embodiment of the present application;

[0029] Figure 6 It is a schematic diagram of the auxiliary oil return cavity and the four-way check valve in the embodiment of the present application;

[0030] Figure 7 Figure is a schematic diagram of the high-speed adapter section inner wall oil baffle plate in the embodiment of the present application.

[0031] In the figure, 1 is a high-speed motor, 2 is a high-speed adapter section, 3 is a gear box, 4 is an adapter section, 5 is a left rotating shaft, 6 is a right rotating shaft, 7 is a swing platform, 8 is an auxiliary oil return cavity, 9 is a one-way valve, 10 is an oil baffle plate, and 11 is a dynamic attitude test bench. DETAILED DESCRIPTION

[0032] To make the purpose, technical solutions and advantages of the embodiment of the present application clearer, the technical solutions in the embodiment of the present application will be clearly and completely explained below in combination with the drawings in the embodiment of the present application. Obviously, the described embodiment is a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the present application.

[0033] Figure 1 The bearing cavity sealing test equipment shown is a common sealing tester in the prior art, mainly composed of a tester main body, an oil system, an air system, an electrical control, a test, a data acquisition and a monitoring system. The present example embodiment provides an aero-engine sealing test device for a sealing test piece, such as Figure 2 As shown, the aero-engine sealing test device at least includes a mechanical main body, a lubrication system, a gas supply and extraction system, a test system, a control system, a console, a low-temperature simulation system, an oil mist treatment system and a monitoring system.

[0034] Referring to Figure 3 The mechanical main body includes a high-speed motor 1, a high-speed adapter section 2 and a dynamic attitude test bench 11, wherein the high-speed adapter section 2 transmits power of the high-speed motor 1 to the sealing test piece, and the dynamic attitude test bench 11 adjusts the pitch and roll attitude changes required by the test; the lubrication system is in bidirectional communication with the high-speed adapter section, so that the oil can circulate in the lubrication system and the high-speed adapter section; the gas supply and extraction system is in communication with the high-speed adapter section, for providing a high-temperature, high-pressure or vacuum environment; the test system includes a vibration test analysis system for vibration test analysis, a hydrodynamic pressure sealing test analysis system for hydrodynamic pressure sealing test and a data acquisition test system; the control system at least includes a dynamic attitude test bench control system for controlling the dynamic attitude test bench and a variable frequency speed regulation drag control system for controlling the high-speed motor; the console outputs control instructions, the control instructions are received by the control system and control parameters are sent to corresponding control terminals, so as to realize automatic changes of the bench attitude, gas supply temperature, gas supply pressure and the like with the test rotating speed.

[0035] Among them, Figure 4The structure diagram of the high-speed adapter section is shown. Since the sealing test device of the application needs to simulate working conditions including pitch and roll, in order to prevent abnormal vibration of the sealing device during the test and affect the accuracy of the test, the application adopts a form of "motor + high-speed adapter section" different from the common form of "motor + gear box + adapter section" in the prior art, and the high-speed adapter section 2 is set by the gear box 3 and the adapter section 4, which can not only reduce the number of transmission chains, simplify the structure and improve the transmission efficiency, but also take into account the functions of the gear box and the adapter section, and has the functions of speed increasing and mounting the sealing device.

[0036] Specifically as Figure 1 shown, during the test, the test piece is installed on the dynamic attitude test bench 11, which realizes the attitude change required by the pitch and roll of the attitude test, and is used to make the test attitude of the test piece the same as the actual attitude of the test piece in the aero-engine. The high-speed motor 1 transmits power to the sealing test piece through the high-speed adapter section 2, and runs to the required rotating speed of the test. The lubrication system is in bidirectional communication with the high-speed adapter section, so that the lubricating oil can circulate in the lubrication system and the high-speed adapter section, and is used to simulate the oil mist environment in the test cavity, and can also lubricate the test adapter section and the gear box. In actual application, an oil pump can be arranged between the lubrication system and the high-speed adapter section to deliver lubricating oil, or a radiator can be arranged to cool the lubricating oil, which all belong to the contents well known in the art and will not be described here.

[0037] The gas supply and exhaust system supplies or exhausts gas with different temperatures and pressures into the inside of the test adapter section, simulating the high-temperature, high-pressure or vacuum environment required by the test. Since a large amount of oil mist will be generated during the high-speed operation of the test piece during the test, in order to avoid the oil mist from leaking into the environment and causing waste and pollution of the lubricating oil, the oil mist is treated through the oil mist treatment system.

[0038] The low-temperature simulation system is used to simulate the low-temperature environment in severe cold regions, and can provide the required temperature for the test. In order to protect the adapter section bearing from low-temperature damage when the multifunctional sealing test device starts in severe cold regions, a thermocouple is welded on the outer ring of the bearing to monitor the bearing temperature in real time, and a high-temperature gas (normal temperature ~ 80℃) is introduced from the gas supply and exhaust system according to the bearing temperature to automatically adjust the bearing temperature, prevent the bearing from being damaged by low temperature, and improve the safety and reliability of the operation of the test device.

[0039] The test system accurately measures the key performance parameters of the fluid dynamic pressure sealing test piece in real time during the test, and collects, records and monitors, and performs over-limit protection on the entire test device.

[0040] The present application is based on the speed change adjustment test section of temperature, pressure and attitude to realize multi-parameter coordinated control. The control system is a distributed structure, and the test piece speed, test bench attitude, gas supply temperature, gas supply pressure, etc. are controlled by the PLC of each system. The multi-parameter coordinated control coordinates the automatic control instructions of each PLC through the host computer test spectrum, and the control parameters are sent to each control terminal at a specific time and requirement through TCP / IP communication between the PLCs, so as to realize the automatic change of the test bench attitude, gas supply temperature, gas supply pressure, etc. with the test speed.

[0041] In the test, power lines, test lines, oil inlet pipes, oil pipes and many other pipelines will be used, and the high-speed adapter section 2 is installed on the swing platform 7 and will perform two-degree-of-freedom pitching and rolling with the swing test bench, which will increase the possibility of pipeline winding. Referring to Figure 5 , in order to prevent pipeline winding during the test, all pipelines are divided into two categories and enter the swing platform 7 from the center holes of the left rotating shaft 5 and the right rotating shaft 6, which can effectively reduce the risk of pipeline winding.

[0042] As shown in Figure 6 , an auxiliary oil return cavity 8 is added below the high-speed adapter section 2, so that when the high-speed adapter section 2 is installed on the swing platform 7 and performs two-degree-of-freedom pitching and rolling with the swing test bench, problems such as poor oil return, bearing or gear box oil stirring and air extraction are avoided, so that the lubricating oil of the lubricated gear and bearing will not flow back to the gear and bearing during the test bench pitching and rolling; in order to further improve the effect of preventing oil backflow, four one-way valves 9 are installed at the four corners of the oil tank to prevent the oil in the pipeline from flowing back and extracting air during the test bench pitching and rolling. As shown in Figure 7 , an oil baffle 10 is installed on the inner wall of the high-speed adapter section 2, which can also prevent oil from collecting at the bottom of the tank during the test bench pitching and rolling. Through the above measures, the problems of poor oil return, gear box oil stirring and air extraction of the oil return pump during the test bench pitching and rolling are avoided.

[0043] The main technical parameters of the sealing test device in the embodiment of the present application include: motor input power 22kW, maximum speed 45000r / min, test platform pitching control range -55°~+55°, test platform rolling control range -55°~+55°, air supply flow rate (0~200)g / s, air maximum pressure 2.5MPa, air pressure difference control range (-0.042~1.5)MPa, air temperature control range room temperature~300℃, and the lowest refrigeration temperature of the low-temperature simulation system is -55℃.

[0044] The aero-engine sealing test device of the embodiment of the application is a multi-parameter coordinated control system based on rotation speed, temperature, pressure, attitude and the like, can more truly simulate working states of an aero-engine such as take-off, air slow, ground slow, cruising, emergency, low-temperature starting and the like, can carry out leakage, friction, wear and tear and life test under variable working conditions, and has the following advantages: the high-speed switching section of the gear box and the switching section in two-in-one form can reduce the number of transmission chains, simplify the structure, improve transmission efficiency, and also has the functions of increasing speed and installing a sealing device; the low-temperature simulation system can simulate high-cold environments, facilitate starting test of the sealing device, and automatically adjust bearing temperature through one high-temperature gas outlet to prevent low-temperature damage to the bearing; through the setting of the auxiliary oil return cavity, the one-way valve and the oil baffle, oil return of the gear box can be facilitated and backflow can be prevented when the pitch and roll attitudes are changed.

[0045] Although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features can be replaced by equivalents, and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the application.

Claims

1. An aero-engine sealing test device for a sealing test piece, characterized in that: The aero-engine sealing test device at least comprises: A mechanical body, comprising a high-speed motor, a high-speed transfer section, and a dynamic attitude test bench, wherein the high-speed transfer section transmits power from the high-speed motor to the sealed test piece, and the dynamic attitude test bench adjusts the pitch and roll attitude changes required for the test; a lubrication system, the lubrication system being in bidirectional communication with the high-speed transfer section so that lubricating oil can circulate in the lubrication system and the high-speed transfer section; An air supply and exhaust system, which is connected to the high-speed transfer section and is used to provide a high-temperature, high-pressure or vacuum environment. The air supply and exhaust system draws out a path of high-temperature gas to regulate the bearing temperature during the low-temperature simulation test; A test system, comprising a vibration test and analysis system for performing vibration test and analysis, a fluid dynamic pressure seal test and analysis system for performing fluid dynamic pressure seal test, and a data acquisition test system; A control system, the control system comprising at least a dynamic attitude test bench control system for controlling a dynamic attitude test bench and a variable frequency speed regulation drag control system for controlling a high-speed motor; The control panel outputs control instructions, which are received by the control system and sent to the corresponding control terminal to realize the automatic change of the test bench attitude, air supply temperature and air supply pressure along with the test speed.

2. The aircraft engine sealing test device according to claim 1, characterized in that: The high-speed transfer section is composed of a gear box and a transfer section.

3. The aircraft engine sealing test device according to claim 2, characterized in that: The dynamic attitude test bench includes a rocking platform, a high-speed motor and a high-speed adapter section are placed on the rocking platform, and test pipelines enter the rocking platform from the center holes of the left and right rotating shafts of the rocking platform respectively.

4. The aircraft engine sealing test device according to claim 2, characterized in that: An auxiliary oil return chamber is provided below the high-speed transfer section.

5. The aircraft engine sealing test device according to claim 2, characterized in that: Oil baffles are installed at the four corners of the oil tank of the high-speed transfer section.

6. The aircraft engine sealing test device according to claim 2, characterized in that: An oil baffle is installed on the inner wall of the high-speed transfer section.

7. The aircraft engine sealing test device according to claim 1, characterized in that: It also includes a low temperature simulation system for providing the low temperature environment required for the test.

8. The aircraft engine sealing test device according to claim 7, characterized in that: The refrigeration temperature of the low-temperature simulation system is from room temperature to -55°C.

9. The aircraft engine sealing test device according to claim 1, characterized in that: The dynamic attitude test bench has a pitch control range of -55° to +55°, and a roll control range of -55° to +55°.

10. The aircraft engine sealing test device according to claim 1, characterized in that: The air supply flow rate in the aero-engine sealing test device is 0-200 g / s, the air pressure is 0-2.5 MPa, the air pressure difference control range is -0.042 MPa-1.5 MPa, and the air temperature control range is room temperature-300°C.

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