An experimental platform for simulating gas path faults and electrostatic monitoring of aeroengines

Abstract

The present invention discloses an experimental platform for simulating gas path faults and electrostatic monitoring of an aero-engine, which includes an experimental platform. The experimental platform mainly includes a test bench, on which an air compression system is installed. The air compression system is sequentially connected to an air heating device, a rotor rubbing device, a micro turbojet engine, a fuel supply device, and a nozzle through a gas path pipeline; the outlet of the nozzle is connected to a turbine simulation device; a particulate injection device is also provided on the gas path pipeline between the air compression system and the air heating device and on the gas path pipeline between the micro turbojet engine and the nozzle; electrostatic sensors are provided on each section of the gas path pipeline. The present invention can conduct research on the relationship between the electrostatic signals of metal particles and non-metal particles in the gas exhaust of an aero-engine and parameters such as exhaust temperature, pressure, and speed, and conduct research on the damage faults and electrostatic characteristics of turbine components caused by engine combustion carbon deposition or engine block shedding.

Description

Technical Field

[0001] The present invention relates to the field of on-line monitoring and condition-based maintenance of aero-engines, and particularly to a novel aero-engine gas path fault simulation and electrostatic monitoring test platform. Background Art

[0002] An aero-engine is known as the heart of an aircraft and is one of the core components of various military and civilian aircraft. Its reliability is extremely important for flight safety. Among all the components of an aero-engine, the gas path components are the most critical ones to ensure the normal operation of the engine. The gas path components of the engine are in a high-temperature and high-pressure working environment for a long time, and their failure rate has been staying high. The gas path component failure is one of the main inducements for serious engine accidents. The common faults of the aero-engine gas path components mainly include foreign object ingestion, combustion chamber carbon deposition, blade-casing rubbing, component ablation and chipping, blade cracks and spalling of turbine components, etc. According to statistics, the faults caused by the aero-engine gas path component failures account for about ninety percent of the total engine failures. Therefore, monitoring the state of the engine gas path components is of great significance for the overall engine state monitoring and fault diagnosis.

[0003] Currently, the fault diagnosis methods actually applied in the aero-engine industry are mainly off-line condition detection and fault diagnosis. However, in the actual operation process, only when the engine fault reaches a certain level can it be detected. Off-line condition monitoring cannot extract the information in the initial stage of the fault and provide early warning. In recent years, the on-line electrostatic monitoring technology of aero-engines has developed greatly. This technology realizes the real-time monitoring of the working components of the engine gas path by monitoring the charge level in the gas path channel of the engine. Based on the monitored data, further analysis and processing are carried out on the working condition, performance and future development trend of the engine, so as to provide early warning information for the faults of the engine gas path components and realize the on-line monitoring and real-time fault diagnosis of the engine working state. In view of the strong demand of the aero-engine health management system for new state monitoring technologies such as the gas path electrostatic monitoring technology, the on-line state monitoring and fault diagnosis of aero-engines based on electrostatic sensors have become a research hotspot.

[0004] The gas path electrostatic monitoring technology requires a large number of fault simulation tests to construct a sample database and study related mechanisms. This technology has problems such as high economic costs for simulating engine faults and a long full life cycle of test runs, making it difficult to capture fault information in a timely manner. At present, the types of engine test benches used to simulate faults in engine gas path components in China are single. After the construction of the test bench is completed, it can generally only simulate one or several common faults in the engine gas path, and there are defects such as a large difference between the fault simulation conditions and the actual aeroengine test conditions, incomplete fault simulation states, insufficient testable and collectible data, and the need to build different types of test benches to simulate all tests, resulting in high costs for the test benches. Therefore, it is very necessary to design a new type of test bench with high cost performance and the ability to simulate various fault tests in the actual aeroengine test environment. Summary of the Invention

[0005] To solve the deficiencies of the existing technology, the present invention provides an aeroengine gas path fault simulation and electrostatic monitoring test platform, aiming to simulate various types of faults in the actual aeroengine test environment through independent or combined tests in the split structure test section, and use electrostatic monitoring technology to achieve real-time online monitoring and diagnostic research on aeroengine faults.

[0006] An aeroengine gas path fault simulation and electrostatic monitoring test platform includes a test platform. An air compression system is installed on the test platform. The air compression system is sequentially connected to an air heating device, a rotor rubbing device, a micro turbojet engine, a fuel supply device, and a nozzle through a gas path pipeline; the outlet of the nozzle is connected to a turbine simulation device;

[0007] A particulate injection device is provided on the gas path pipeline between the air compression system and the air heating device and on the gas path pipeline between the micro turbojet engine and the nozzle; electrostatic sensors are provided on each section of the gas path pipeline.

[0008] Preferably, the test platform further includes a control system, which is electrically connected to the air compression system, the air heating device, the particulate injection device, the rotor rubbing device, the micro turbojet engine, and the fuel supply device.

[0009] Preferably, the test platform further includes a signal acquisition system for acquiring signals, and the signal acquisition system is electrically connected to the air heating device, the micro turbojet engine, and the electrostatic sensors.

[0010] Preferably, the air compression system includes an air compressor, a gas storage tank, a blow-off valve, a gate valve, a filter, a pressure regulating valve, and a quick valve that are sequentially connected through a gas path pipeline.

[0011] Preferably, the turbine simulation device includes a hollow cylindrical casing barrel, a rotating shaft system is provided at the center of the casing barrel, and the rotating shaft system is connected to the inner wall surface of the casing barrel through a shaft system fixing connecting rod; centering on the rotating shaft system, a turbine stator and a turbine rotor are distributed around the rotating shaft system; an electrostatic sensor mounting hole is provided on the wall surface of the casing barrel.

[0012] Preferably, the rotating shaft system includes a fixed bolt assembly, a front-end bearing, a rotating shaft and a rear-end bearing connected in sequence; the front-end bearing and the rotating shaft are connected through the fixed bolt assembly, and the front-end bearing is fixed on the rotating shaft; the rear-end bearing and the rotating shaft are connected through a circlip fixing assembly, and the rear-end bearing is fixed on the rotating shaft.

[0013] Preferably, the electrostatic sensor includes the first to seventh electrostatic sensors, which are respectively installed through threaded pipes. The first electrostatic sensor is installed on the first gas pipeline between the air compression system and the air heating device, the second electrostatic sensor is installed on the second gas pipeline between the air heating device and the rotor rubbing device, the third electrostatic sensor is installed on the third gas pipeline between the rotor rubbing device and the micro turbojet engine, the fourth and fifth electrostatic sensors are installed at both ends of the fuel test pipeline in the fuel supply device, the sixth electrostatic sensor is installed at one end of the turbine simulation device near the nozzle, and the seventh electrostatic sensor is installed on the exhaust pipeline.

[0014] The present invention has the following beneficial effects:

[0015] (1) The gas path fault simulation and electrostatic monitoring test platform of the aero-engine of the present invention adopts a segmented combined design. Through different combinations, various aero-engine fault simulations and electrostatic tests can be carried out, greatly increasing the number of types of fault simulations, and improving the types and sample numbers of the tested and collected data, thereby improving the general applicability of electrostatic monitoring research to the fault diagnosis types of aero-engines;

[0016] (2) Through the combined design of the quick valve, vent valve, gate valve and filter in the air compression system of the present invention, the safety of the test operators behind the gas source can be effectively protected, and the overall test safety is improved; through the combined design of the gas storage tank, pressure regulating valve and quick valve, the stability and controllability of the high-speed air flow in the test are increased, and the test accuracy is improved;

[0017] (3) The present invention provides a research on the relationship between the electrostatic signals of metal particles and non-metal particles in the gas exhaust of an aero-engine and parameters such as exhaust temperature, exhaust pressure, and exhaust speed, which is beneficial to carry out basic research on the relationship between the electrostatic signals of metal particles and non-metal particles and parameters such as exhaust temperature, exhaust pressure, and exhaust speed under low-cost conditions;

[0018] (4) The present invention provides a study on the simulation of blade crack and spalling faults and electrostatic characteristics of a turbine component. By using a nozzle to accelerate the high-temperature exhaust gas flow of a micro turbojet engine to a specified Mach number, it can effectively simulate the impact and burning of the high-speed exhaust gas flow of an aeroengine tail flame on the high-temperature ceramic coating of the turbine blade, resulting in spalling faults of the ceramic coating;

[0019] (5) The present invention provides a turbine simulation device. This device has a simple structure, is convenient to process, and has a low cost. Compared with directly using a micro turbojet engine for turbine fault tests, it can greatly reduce the test cost;

[0020] (6) When the present invention conducts research on the simulation of blade-casing rubbing faults and electrostatic characteristics, it uses an air heating device to simulate the high temperature of the aeroengine tail flame, eliminating the need to use a micro turbojet engine as a heat source in traditional rubbing tests, reducing the wear and tear of the micro turbojet engine, lowering the cost, and improving the safety of the test;

[0021] (7) The air heating device and the micro turbojet engine of the present invention can simulate relatively real aeroengine test conditions at a low cost. With a segmented combined design, various aeroengine fault simulations and electrostatic tests can be carried out through different combinations, reducing the cost compared with separately building different test benches, and having a high comprehensive cost performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Schematic diagram of the overall composition of the aeroengine gas path fault simulation and electrostatic monitoring test platform according to an embodiment of the present invention;

[0023] Figure 2 Schematic diagram of the composition of the air compression system according to an embodiment of the present invention;

[0024] Figure 3 Schematic diagram of the structure of the turbine simulation device according to an embodiment of the present invention;

[0025] Figure 4 Schematic diagram of the structure of the rotating shaft system according to an embodiment of the present invention;

[0026] Figure 5 Partial schematic diagram of the turbine simulation device according to an embodiment of the present invention;

[0027] Figure 6 Front view of the turbine simulation device according to an embodiment of the present invention;

[0028] Figure 7 Rear view of the turbine simulation device according to an embodiment of the present invention;

[0029] Figure 8 Front side view of the turbine simulation device according to an embodiment of the present invention;

[0030] Figure 9 Rear view of the turbine simulation device according to an embodiment of the present invention.

[0031] Reference numerals:

[0032] 1 Air compression system, 101 Air compressor, 102 Gas storage tank, 103 Relief valve, 104 Gate valve, 105 Filter,

[0033] 106 Pressure regulating valve, 107 Quick valve, 2 Air heating device, 3 Particulate injection device, 301 Particulate injection device, 302 Particulate injection device, 4 Control system, 5 Rotor rubbing device, 6 Micro turbojet engine, 7 Fuel supply device, 701 Fuel injection device, 702 Fuel test pipeline, 8 Nozzle, 9 Turbine simulation device, 901 Casing cylinder, 902 Rotating shaft system, 903 Shaft system fixing connecting rod, 904 Turbine stator, 905 Turbine rotor, 906 Electrostatic sensor mounting hole, 902a Fixing screw, 902b Front bearing, 902c Rotating shaft, 902d Snap ring fixing assembly, 902e Rear bearing, 902f Compression bolt, 10 Exhaust pipeline, 11 Exhaust valve, 12 Electrostatic sensor, 1201 First electrostatic sensor, 1202 Second electrostatic sensor, 1203 Third electrostatic sensor, 1204 Fourth electrostatic sensor,

[0034] 1205 Fifth electrostatic sensor, 1206 Sixth electrostatic sensor, 1207 Seventh electrostatic sensor, 13 Signal acquisition system, 14 Gas pipeline, 1401 First gas pipeline, 1402 Second gas pipeline,

[0035] 1403 Third gas pipeline, 15 Test bench. Detailed implementation manners

[0036] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0037] The present invention provides a new type of aeroengine gas path fault simulation and electrostatic monitoring test platform with small differences between test conditions and actual aeroengine test run conditions, multiple types of faults that can be simulated, sufficient data testing and acquisition, and high comprehensive cost performance. The purpose is to simulate various types of faults in the actual test run environment of an aeroengine through independent or combined tests in a split structure test section, and use electrostatic monitoring technology to achieve real-time online monitoring and diagnostic research on aeroengine faults.

[0038] This test platform can be used to study the relationship between the electrostatic signals of metal particles and non-metal particles in the gas exhaust of aero-engines and parameters such as exhaust temperature, exhaust pressure, and exhaust velocity. It can simulate typical gas path faults such as foreign object ingestion, combustion chamber carbon deposition, blade-casing rubbing, and component ablation and blockage in the engine, study the characteristics of electrostatic signals during fault occurrence, and simulate the damage faults of turbine components caused by engine combustion carbon deposition or engine blockage and study their electrostatic characteristics.

[0039] As Figure 1 shown, a new type of aero-engine gas path fault simulation and electrostatic monitoring test platform includes a test platform, which mainly includes a test bench 15. An air compression system 1, an air heating device 2, a particulate injection device 3, a control system 4, a rotor rubbing device 5, a micro turbojet engine 6, a fuel supply device 7, a nozzle 8, a turbine simulation device 9, an exhaust pipe 10, an exhaust valve 11, an electrostatic sensor 12, a signal acquisition system 13, and a gas path pipe 14 are installed on the test bench 15.

[0040] The gas path pipe 14 includes a first gas path pipe 1401, a second gas path pipe 1402, and a third gas path pipe 1403. The air compression system 1 is connected to the air heating device 2 through the first gas path pipe 1401, the air heating device 2 is connected to the rotor rubbing device 5 through the second gas path pipe 1402, and the rotor rubbing device 5 is connected to the micro turbojet engine 6 through the third gas path pipe 1403. The micro turbojet engine 6 is connected to the inlet of the nozzle 8 through the fuel supply device 7, the outlet of the nozzle 8 is connected to the inlet of the exhaust pipe 10 through the turbine simulation device 9, and an exhaust valve 11 is provided at the outlet of the exhaust pipe 10.

[0041] The particulate injection device 3 includes a first particulate injection device 301 and a second particulate injection device 302, which are respectively installed on the first gas path pipe 1401 and the fuel test pipe 702 in the fuel supply device 7. The fuel supply device 7 further includes a fuel injection device 701, which is installed on the fuel test pipe 702.

[0042] The static electricity sensor 12 is installed on the air path pipeline 14, fuel injection device 701, turbine simulation device 9 and exhaust pipeline 10 through a threaded pipeline. Specifically, the static electricity sensor 12 includes the first to seventh static electricity sensors. The first static electricity sensor 1201 is installed on the first air path pipeline 1401 between the air compression system 1 and the air heating device 2. The second static electricity sensor 1202 is installed on the second air path pipeline 1402 between the air heating device 2 and the rotor rubbing device 5. The third static electricity sensor 1203 is installed on the third air path pipeline 1403 between the rotor rubbing device 5 and the micro turbojet engine 6. The fourth static electricity sensor 1204 and the fifth static electricity sensor 1205 are installed at both ends of the fuel test pipeline 702 in the fuel supply device 7. The sixth static electricity sensor 1206 is installed at one end of the turbine simulation device 9 near the nozzle 8. The seventh static electricity sensor 1207 is installed at the entrance of the exhaust pipeline 10.

[0043] The test platform further includes a control system 4, and the control system 4 is telecommunication-connected to the air compression system 1, air heating device 2, particulate matter injection device 3, rotor rubbing device 5, micro turbojet engine 6 and fuel supply device 7.

[0044] The test platform further includes a signal acquisition system 13 for acquiring signals. The signal acquisition system 13 is telecommunication-connected to the air heating device 2, micro turbojet engine 6 and static electricity sensor 12.

[0045] In the test platform, the test section is defined as: air compression system 1, air heating device 2, particulate matter injection device 3, rotor rubbing device 5, micro turbojet engine 6, fuel supply device 7, nozzle 8, turbine simulation device 9, exhaust pipeline 10, exhaust valve 11, static electricity sensor 12, air path pipeline 14. The connections between the test sections can be disassembled for combined connection. Each test section is a split structure. After being split, it can be tested separately for independent factor test research; after being disassembled, the test sections can be placed at different positions for combined test for comprehensive test research.

[0046] As Figure 2 shown, the air compression system 1 of a new type of aeroengine air path fault simulation and static electricity monitoring test platform mainly includes devices such as an air compressor 101, an air storage tank 102, a blow-off valve 103, a gate valve 104, a filter 105, a pressure regulating valve 106, a quick valve 107, etc. that are sequentially connected through an air path pipeline.

[0047] The air compression system 1 is mainly used to supply high-speed airflows with stable pressure for the air path fault simulation and electrostatic monitoring tests of aeroengines. Among them, the air compressor 101 is mainly used to compress air and inject the compressed air into the gas storage tank 102; the gas storage tank 102 is mainly used to store gas, and works together with the air compression system 1 to compress the air to the set pressure before subsequent test work can be carried out; the vent valve 103 is mainly used to quickly vent the compressed air in the gas storage tank 102 to the atmospheric environment; the gate valve 104 is mainly used to cut off and open the air flow of the air compression system 1 to the test section system, and this valve should have strong pressure-bearing capacity and reliability to ensure the safety of the test section; the filter 105 is mainly used to filter impurities and particulate matters in the air to exclude interfering substances for the injection of particulate matters in the subsequent test section; the pressure regulating valve 106 is mainly used to regulate and control the air flow and pressure in the test section; the quick valve 107 is mainly used to quickly cut off and open the air passage in the test section to facilitate quick pause and quick start in the test.

[0048] The startup steps of the air compression system are as follows:

[0049] 1) Close the vent valve 103, open the gate valve 104, close the pressure regulating valve 106, and close the quick valve 107;

[0050] 2) Open the air compressor 101 and store the compressed gas in the gas storage tank 102 for pressure accumulation;

[0051] 3) After the pressure in the gas storage tank reaches the specified pressure, open the gas storage tank control valve, and the high-speed air flow flows out and passes through the filter 105 to filter the impurities in the gas and then flows to the pressure regulating valve;

[0052] 4) Open the pressure regulating valve and adjust the gas to the specified pressure;

[0053] 5) Open the quick valve, and the high-speed gas flows out to the first gas path pipeline 1401.

[0054] The shutdown steps of the air compression system are as follows:

[0055] 1) Open the vent valve;

[0056] 2) Close the quick valve;

[0057] 3) Shut down the air compressor;

[0058] 4) Close the pressure regulating valve;

[0059] 5) After the gas in the gas storage tank is emptied, close the gas storage tank;

[0060] 6) Close the vent valve.

[0061] Such as Figures 3 to 9As shown in the figure, there is a turbine simulation device 9, which includes a casing cylinder 901, a rotating shaft system 902, a shaft system fixing link 903, a turbine stator 904, a turbine rotor 905, and an electrostatic sensor mounting hole 906. The casing cylinder 901 is in the shape of a hollow cylinder, and a rotating shaft system 902 is provided at its center. The rotating shaft system 902 is connected to the inner wall surface of the casing cylinder 901 through a shaft system fixing link 903; with the rotating shaft system 902 as the center, the turbine stator 904 and the turbine rotor 905 are distributed around the rotating shaft system 902; the wall surface of the casing cylinder 901 is provided with an electrostatic sensor mounting hole 906, and the casing cylinder 901 is sequentially connected to other components in the turbine simulation device 9 to form a whole.

[0062] Among them, the rotating shaft system 902 includes a fixing bolt assembly 902a, a front-end bearing 902b, a rotating shaft 902c, a snap ring fixing assembly 902d, a rear-end bearing 902e, and a compression bolt 902f. The front-end bearing 902b and the rotating shaft 902c are connected through the fixing bolt assembly 902a, and the fixing bolt assembly 902a fixes the front-end bearing 902b on the rotating shaft 902c; the rear-end bearing 902e and the rotating shaft 902c are connected through the snap ring fixing assembly 902d, and the snap ring fixing assembly 902d fixes the rear-end bearing 902e on the rotating shaft 902c; the compression bolt 902f is used to fix the turbine rotor 905.

[0063] The turbine simulation device 9 is mainly used to provide a turbine rotor support structural member with a simple structure, easy to process and low cost. During the test, the high-temperature and high-speed airflow accelerated by the nozzle 8 will drive the turbine rotor to rotate, and the combustion carbon deposits or falling particulate matter in the airflow will impact the rotating turbine rotor, causing surface faults of the turbine rotor blades, and being monitored by an electrostatic sensor.

[0064] The present invention also provides a working method for simulating gas path faults and electrostatic monitoring tests of an aeroengine:

[0065] (1) Conduct research on the relationship between the electrostatic signals of metal particles and non-metal particles in the gas exhaust of an aeroengine and parameters such as exhaust temperature, exhaust pressure, and exhaust speed. The test method is as follows:

[0066] Step 1.1, along the gas flow direction, sequentially connect an air compression system 1, a first gas path pipeline 1401, an air heating device 2, and a second gas path pipeline 1402 on the test platform; install a first particulate matter injection device and a first electrostatic sensor 1201 on the first gas path pipeline 140, install a second electrostatic sensor 1202 on the second gas path pipeline 1402, connect the air compression system 1, the particulate matter injection device 3 to a control system 4 and connect the control system 4 and a signal acquisition system 13 for collecting sensor signals to the test system.

[0067] Step 1.2: Start the air compression system, adjust the gas to the specified pressure, and make the high-speed gas flow out to the first gas pipeline 1401.

[0068] Step 1.3: Prepare the metal particles and non-metal particles required for the experiment, put the particles into the particle injection device in advance, start the signal acquisition system to record the electrostatic signals throughout the process, and start the air compression system through the control system to obtain a high-speed air flow at room temperature.

[0069] Step 1.4: After the working conditions tend to be stable, open the particle injection device, and the particles fall into the first gas pipeline 1401 through the injection pipe, pass through the electrostatic sensor and the pressure sensor and temperature sensor built in the air heating device with the high-speed air flow, and are discharged to the atmospheric environment through the second gas pipeline 1402.

[0070] Step 1.5: Observe the changes in the signals of the electrostatic sensor, pressure sensor, and temperature sensor in the signal acquisition system, and store all signal data.

[0071] Step 1.6: Turn off the air compression system, put the particles into the particle injection device again, start the air heating device 2, and heat the air flowing through the air heating device.

[0072] Step 1.7: After the temperature reaches the specified value, start the air compression system again to obtain a high-speed air flow at room temperature.

[0073] Step 1.8: After the working conditions tend to be stable, open the particle injection device, and the particles fall into the first gas pipeline 1401 through the injection pipe, pass through the electrostatic sensor and the pressure sensor and temperature sensor built in the air heating device with the high-speed air flow, and are discharged to the atmospheric environment through the second gas pipeline 1402.

[0074] Step 1.9: Observe the changes in the signals of the electrostatic sensor, pressure sensor, and temperature sensor in the signal acquisition system, and store all signal data.

[0075] (2) Conduct the simulation of engine foreign object ingestion failure and the study of electrostatic characteristics. The test method is as follows:

[0076] Step 2.1, sequentially connect the air compression system 1, the first gas pipeline 1401, the second gas pipeline 1402, the third gas pipeline 1403, the micro turbojet engine 6, the fuel supply device 7, the nozzle 8, the turbine simulation device 9, the exhaust pipeline 10, and the exhaust valve 11 on the test platform. Install the sixth electrostatic sensor 1206 and the seventh electrostatic sensor 1207 at the inlet of the turbine simulation device 9 and the inlet of the exhaust pipeline 10 respectively. Install the second particulate injection device 302 on the fuel experiment pipeline 702 of the fuel supply device 7. Connect the micro turbojet engine 6 and the fuel supply device 7 to the control system 4, and connect the control system 4 and the signal acquisition system 13 that collects sensor signals to the test system;

[0077] Step 2.2, start the air compression system, adjust the gas to the specified pressure, and make the high-speed gas flow out to the first gas pipeline 1401;

[0078] Step 2.3, conduct simulation of damage faults of turbine components caused by engine combustion carbon deposition or engine block shedding and study of electrostatic characteristics, specifically as follows:

[0079] Step 2.4, open the exhaust valve 11, prepare the block shedding particulates required for the experiment, and put the block shedding particulates into the second particulate injection device 302 in advance;

[0080] Step 2.5, start the signal acquisition system to record the electrostatic signals throughout the process, start the micro turbojet engine, and start the air compression system;

[0081] Step 2.6, first start the fuel supply device for rich fuel supply, simulate the combustion carbon deposition fault, observe the change of signals of the electrostatic sensor in the signal acquisition system, and store all signal data;

[0082] Step 2.7, close the fuel supply of the fuel supply device, open the second particulate injection device 302, the block shedding particulates fall into the fuel experiment pipeline 702 through the injection pipe. After being burned by the high-temperature tail flame of the micro turbojet engine, the block shedding particulates pass through the nozzle with the high-speed air flow, are accelerated to the specified Mach number, pass through the sixth electrostatic sensor 1206, impact the turbine rotor 905 in the turbine simulation device 9 and cause damage to the turbine rotor fault. Subsequently, the residual substances of the block shedding particulates pass through the seventh electrostatic sensor 1207 and are discharged to the atmospheric environment through the exhaust pipeline 10;

[0083] Step 2.8, observe the change of signals of the electrostatic sensor in the signal acquisition system, and store all signal data.

[0084] (3) The method for simulating the combustion chamber carbon deposition fault and studying the electrostatic characteristics is as follows:

[0085] Step 3.1, successively connect the air compression system 1, the first gas pipeline 1401, the second gas pipeline 1402, the third gas pipeline 1403, the micro turbojet engine 6, and the fuel supply device 7 on the test platform. The fourth static electricity sensor 1204 and the fifth static electricity sensor 1205 are respectively installed at the inlet and outlet of the fuel experiment pipeline 702, and connect the control system 4 and the signal acquisition system 13 to the test system;

[0086] Step 3.2, start the signal acquisition system to record the static electricity signals during the whole process, start the micro turbojet engine, and start the air compression system;

[0087] Step 3.3, after the working conditions tend to be stable, start the fuel injection device 701 for rich fuel injection, and a large amount of soot particles are generated by the high-temperature mixing of the micro turbojet engine tail flame and the rich fuel to simulate the combustion chamber carbon deposition fault;

[0088] Step 3.4, observe the change of the signal of the static electricity sensor in the signal acquisition system, and store all signal data.

[0089] (4) The method for simulating the component ablation and chipping fault and studying the static electricity characteristics is as follows:

[0090] Step 4.1, successively connect the air compression system 1, the first gas pipeline 1401, the second gas pipeline 1402, the third gas pipeline 1403, the micro turbojet engine 6, and the fuel experiment pipeline 702 on the test platform. The second particulate matter injection device 302 is connected to the fuel experiment pipeline 702. The fourth static electricity sensor 1204 and the fifth static electricity sensor 1205 are respectively installed at the inlet and outlet of the fuel experiment pipeline, and connect the control system 4 and the signal acquisition system 13 to the test system;

[0091] Step 4.2, prepare the component chipping required for the experiment, put the component chipping into the second particulate matter injection device 302 in advance, start the signal acquisition system to record the static electricity signals during the whole process, start the micro turbojet engine, and start the air compression system;

[0092] Step 4.3, after the working conditions tend to be stable, open the second particulate matter injection device 302, the component chipping falls into the fuel experiment pipeline 702 through the injection pipe, and the component chipping is discharged to the atmospheric environment through the fuel experiment pipeline 702 after being burned by the high-temperature tail flame of the micro turbojet engine and passing through the static electricity sensor with the high-speed air flow;

[0093] Step 4.4, observe the change of the signal of the static electricity sensor in the signal acquisition system, and store all signal data.

[0094] (5) The method for simulating the blade-casing rubbing fault and studying the static electricity characteristics is as follows:

[0095] Step 5.1, sequentially connect the air compression system 1, the first gas pipeline 1401, the air heating device 2, the second gas pipeline 1402, the rotor rubbing device 5, and the third gas pipeline 1403. The second electrostatic sensor 1202 is installed on the second gas pipeline 1402, and the third electrostatic sensor 1203 is installed on the third gas pipeline 1403. The control system (4) and the signal acquisition system 13 are connected to the test system.

[0096] Step 5.2, start the air compression system, start the signal acquisition system to record the electrostatic signals throughout the process, and start the air compression system;

[0097] Step 5.3, start the air heating device 2, and after the air flow temperature in the air heating device reaches the specified temperature, start the rubbing device to simulate the rubbing fault of the engine;

[0098] Step 5.4, observe the change of the signals of the electrostatic sensors in the signal acquisition system, and store all signal data.

[0099] (6) The method for simulating the damage fault of the turbine component caused by engine combustion carbon deposition or engine block dropping and studying the electrostatic characteristics is as follows:

[0100] Step 6.1, sequentially connect the air compression system 1, the first gas pipeline 1401, the second gas pipeline 1402, the third gas pipeline 1403, the micro turbojet engine 6, the fuel supply device 7, the nozzle 8, the turbine simulation device 9, the exhaust pipeline 10, and the exhaust valve 11. The sixth electrostatic sensor 1206 and the seventh electrostatic sensor 1207 are respectively installed at the inlet of the turbine simulation device and the inlet of the exhaust pipeline. The second particulate injection device 302 is installed on the fuel experiment pipeline 702. The control system 4 and the signal acquisition system 13 are connected to the test system;

[0101] Step 6.2, open the exhaust valve 11, prepare the dropped block particles required for the experiment, and put the dropped block particles into the second particulate injection device 302 in advance;

[0102] Step 6.3, start the signal acquisition system to record the electrostatic signals throughout the process, start the micro turbojet engine, and start the air compression system;

[0103] Step 6.4, first start the fuel supply device to supply rich fuel, simulate the combustion carbon deposition fault, observe the change of the signals of the electrostatic sensors in the signal acquisition system, and store all signal data;

[0104] Step 6.5: Shut off the fuel supply of the fuel supply device, open the second particulate injection device 302, and let the dropped particulate matter fall into the fuel experiment pipeline 702 through the injection pipe. After being burned by the high-temperature tail flame of the micro turbojet engine, the dropped particulate matter accelerates to the specified Mach number with the high-speed airflow through the nozzle, then impacts the turbine rotor 905 in the turbine simulation device 9 through the sixth electrostatic sensor 1206, causing a fault in the turbine rotor. Subsequently, the residual matter of the dropped particulate matter passes through the seventh electrostatic sensor 1207 and is discharged into the atmospheric environment through the exhaust pipeline;

[0105] Step 6.6: Observe the change of the signal of the electrostatic sensor in the signal acquisition system and store all signal data.

[0106] (7) The method for studying the electrostatic characteristics under various fault combination states is as follows:

[0107] The above six studies can be combined and set to study the electrostatic characteristics under different fault combination states.

[0108] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aeroengine gas path fault simulation and electrostatic monitoring test platform, including a test platform, characterized in that, Install an air compression system (1) on the test platform. The air compression system (1) is sequentially connected to an air heating device (2), a rotor rubbing device (5), a micro turbojet engine (6), a fuel supply device (7), and a nozzle (8) through an air pipeline (14). The outlet of the nozzle (8) is connected to a turbine simulation device (9). A first particulate matter injection device is provided on the air pipeline (14) between the air compression system (1) and the air heating device (2), and a second particulate matter injection device is provided on the air pipeline (14) between the micro turbojet engine (6) and the nozzle (8). An electrostatic sensor (12) is provided on each section of the air pipeline (14). The air pipeline (14) includes a first air pipeline (1401), a second air pipeline (1402), and a third air pipeline (1403). The air compression system (1) is connected to the air heating device (2) through the first air pipeline (1401), the air heating device (2) is connected to the rotor rubbing device (5) through the second air pipeline (1402), and the rotor rubbing device (5) is connected to the micro turbojet engine (6) through the third air pipeline (1403). The outlet of the nozzle (8) is connected to the inlet of an exhaust pipeline (10) through the turbine simulation device (9), and an exhaust valve (11) is provided at the outlet of the exhaust pipeline (10). The electrostatic sensor (12) includes a first to seventh electrostatic sensor. The first electrostatic sensor (1201) is mounted on the first air pipeline (1401) between the air compression system (1) and the air heating device (2), the second electrostatic sensor (1202) is mounted on the second air pipeline (1402) between the air heating device (2) and the rotor rubbing device (5), the third electrostatic sensor (1203) is mounted on the third air pipeline (1403) between the rotor rubbing device (5) and the micro turbojet engine (6), the fourth electrostatic sensor (1204) and the fifth electrostatic sensor (1205) are mounted at both ends of a fuel test pipeline (702) in the fuel supply device (7), the sixth electrostatic sensor (1206) is mounted at one end of the turbine simulation device (9) near the nozzle (8), and the seventh electrostatic sensor (1207) is mounted at the inlet of the exhaust pipeline (10). The turbine simulation device (9) includes a hollow cylindrical casing (901). A rotating shaft system (902) is provided at the center of the casing (901). The rotating shaft system (902) is connected to the inner wall surface of the casing (901) through a shaft system fixing link (903). Centered on the rotating shaft system (902), turbine stators (904) and turbine rotors (905) are distributed around the rotating shaft system (9). An electrostatic sensor mounting hole (906) is provided on the wall surface of the casing (901). The test platform further includes a control system (4), which is teleconnected to an air compression system (1), an air heating device (2), a particulate injection device (3), a rotor rub-impact device (5), a micro turbojet engine (6), and a fuel supply device (7); The test platform further includes a signal acquisition system (13) for collecting signals, which is teleconnected to the air heating device (2), the micro turbojet engine (6), and an electrostatic sensor (12); The test platform adopts a segmented combined design, and through different combinations, various aero-engine fault simulations and electrostatic tests can be carried out.

2. The aero-engine gas path fault simulation and electrostatic monitoring test platform according to claim 1, characterized in that, The air compression system (1) includes an air compressor (101), an air storage tank (102), a vent valve (103), a gate valve (104), a filter (105), a pressure regulating valve (106), and a quick valve (107) that are sequentially connected through an air pipeline.

3. The aero-engine gas path fault simulation and electrostatic monitoring test platform according to claim 1, wherein The rotating shaft system (902) includes a fixed bolt assembly (902a), a front-end bearing (902b), a rotating shaft (902c), and a rear-end bearing (902e) that are sequentially connected; the front-end bearing (902b) and the rotating shaft (902c) are connected through the fixed bolt assembly (902a), and the front-end bearing (902b) is fixed on the rotating shaft (902c); the rear-end bearing (902e) and the rotating shaft (902c) are connected through a circlip fixing assembly (902d), and the rear-end bearing (902e) is fixed on the rotating shaft (902c).

4. A working method of an aero-engine gas path fault simulation and electrostatic monitoring test platform, characterized in that, Based on the aero-engine gas path fault simulation and electrostatic monitoring test platform described in claim 1, the following steps are included: Step 1.1, along the gas flow direction, connect the air compression system (1), a first air pipeline (1401), the air heating device (2), and a second air pipeline (1402) in sequence on the test platform; install a first particulate injection device and a first electrostatic sensor (1201) on the first air pipeline (1401), install a second electrostatic sensor (1202) on the second air pipeline (1402), connect the air compression system (1) and the first particulate injection device to the control system (4), and connect the control system (4) and the signal acquisition system (13) for collecting sensor signals to the test system; Step 1.2, start the air compression system, adjust the gas to the specified pressure, and make the high-speed gas flow out to the first air pipeline (1401); Research on the relationship between static electricity signals of metal particles, non-metal particles and parameters such as exhaust temperature, exhaust pressure, and exhaust speed in the gas exhaust of aero-engines is as follows: Step 1.3, prepare the metal particles and non-metal particles required for the experiment, put the particles into the first particulate injection device in advance, start the signal acquisition system to record the static electricity signals throughout the process, and start the air compression system through the control system to obtain high-speed air flow under normal temperature environment; Step 1.4: After the working condition tends to be stable, turn on the first particulate injection device. The particles fall into the gas pipeline (14) through the injection pipe, pass through the electrostatic sensor and the pressure sensor and temperature sensor built in the air heating device with the high-speed air flow, and are discharged into the atmospheric environment through the gas pipeline (14). Step 1.5: Observe the signal changes of the electrostatic sensor, pressure sensor and temperature sensor in the signal acquisition system, and store all signal data. Step 1.6: Turn off the air compression system, put particles into the first particulate injection device again, start the air heating device (2), and heat the air flowing through the air heating device. Step 1.7: After the temperature reaches the specified value, start the air compression system again to obtain a high-speed air flow under normal temperature environment. Step 1.8: After the working condition tends to be stable, turn on the first particulate injection device. The particles fall into the gas pipeline (14) through the injection pipe, pass through the electrostatic sensor and the pressure sensor and temperature sensor built in the air heating device with the high-speed air flow, and are discharged into the atmospheric environment through the gas pipeline (14). Step 1.9: Observe the signal changes of the electrostatic sensor, pressure sensor and temperature sensor in the signal acquisition system, and store all signal data.

5. A working method of an aero-engine gas path fault simulation and electrostatic monitoring test platform, characterized in that, The aero-engine gas path fault simulation and electrostatic monitoring test platform according to claim 1 includes the following steps: Step 2.1: Connect the air compression system (1), the first gas pipeline (1401), the second gas pipeline (1402), the third gas pipeline (1403), the micro turbojet engine (6), the fuel supply device (7), the nozzle (8), the turbine simulation device (9), the exhaust pipeline (10) and the exhaust valve (11) in sequence on the test platform. Install the sixth electrostatic sensor (1206) and the seventh electrostatic sensor (1207) at the inlet of the turbine simulation device (9) and the inlet of the exhaust pipeline (10) respectively. Install the second particulate injection device (302) on the fuel experimental pipeline (702) of the fuel supply device (7). Connect the micro turbojet engine (6) and the fuel supply device (7) to the control system (4), and connect the control system (4) and the signal acquisition system (13) for collecting sensor signals to the test system. Step 2.2: Start the air compression system, adjust the gas to the specified pressure, and make the high-speed gas flow out to the first gas pipeline (1401). Carry out the simulation of the damage fault of engine combustion carbon deposition or engine block dropping to the turbine component and the study of electrostatic characteristics, specifically as follows: Step 2.3: Open the exhaust valve (11), prepare the block dropping particles required for the experiment, and put the block dropping particles into the second particulate injection device (302) in advance. Step 2.4: Start the signal acquisition system to record the electrostatic signal throughout the process, start the micro turbojet engine, and start the air compression system. Step 2.5: First start the fuel supply device for rich fuel supply, simulate the combustion carbon deposition fault, observe the signal changes of the electrostatic sensor in the signal acquisition system, and store all signal data. Step 2.6: Shut off the fuel supply of the fuel supply device, open the second particulate injection device (302), the dropped particulate matter falls into the fuel experiment pipeline (702) through the injection pipe. After being burned by the high-temperature tail flame of the micro turbojet engine, the dropped particulate matter is accelerated to the specified Mach number by the high-speed air flow through the nozzle, and then impacts the turbine rotor (905) in the turbine simulation device (9) through the sixth electrostatic sensor (1206), causing damage to the turbine rotor. Subsequently, the residual matter of the dropped particulate matter passes through the seventh electrostatic sensor (1207) and is discharged into the atmospheric environment through the exhaust pipeline (10). Step 2.7: Observe the change of the signal of the electrostatic sensor in the signal acquisition system and store all signal data.

6. A working method of an aero-engine gas path fault simulation and electrostatic monitoring test platform, characterized in that, The aeroengine gas path fault simulation and electrostatic monitoring test platform according to claim 1 includes the following steps: Step 6.1: Connect the air compression system (1), the first gas path pipeline (1401), the second gas path pipeline (1402), the third gas path pipeline (1403), the micro turbojet engine (6), the fuel supply device (7), the nozzle (8), the turbine simulation device (9), the exhaust pipeline (10) and the exhaust valve (11) in sequence. The sixth electrostatic sensor (1206) and the seventh electrostatic sensor (1207) are respectively installed at the inlet of the turbine simulation device and the inlet of the exhaust pipeline. The second particulate injection device (302) is installed on the fuel experiment pipeline (702). The control system (4) and the signal acquisition system (13) are connected to the test system. Step 6.2: Open the exhaust valve (11), prepare the dropped particulate matter required for the experiment, and put the dropped particulate matter into the second particulate injection device (302) in advance. Step 6.3: Start the signal acquisition system to record the electrostatic signal during the whole process, start the micro turbojet engine, and start the air compression system. Step 6.4: First start the fuel supply device for rich fuel supply, simulate the combustion carbon deposition fault, observe the change of the signal of the electrostatic sensor in the signal acquisition system, and store all signal data. Step 6.5: Shut off the fuel supply of the fuel supply device, open the second particulate injection device (302), the dropped particulate matter falls into the fuel experiment pipeline (702) through the injection pipe. After being burned by the high-temperature tail flame of the micro turbojet engine, the dropped particulate matter is accelerated to the specified Mach number by the high-speed air flow through the nozzle, and then impacts the turbine rotor (905) in the turbine simulation device (9) through the sixth electrostatic sensor (1206), causing damage to the turbine rotor. Subsequently, the residual matter of the dropped particulate matter passes through the seventh electrostatic sensor (1207) and is discharged into the atmospheric environment through the exhaust pipeline. Step 6.6: Observe the change of the signal of the electrostatic sensor in the signal acquisition system and store all signal data.

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