51 results about "Engine test stand" patented technology

The invention provides an aero-engine test bed. The aero-engine test bed comprises a rack and an auxiliary support, the auxiliary support comprises a mounting platform, a mounting seat, a connecting piece, a supporting arm, a field force limiting mechanism and a controller; the mounting platform is arranged on the rack; the two mounting seats are oppositely arranged on the mounting platform; the connecting piece is arranged between the two mounting seats and is opposite to the mounting platform; the connecting piece is configured to move in the vertical direction; the supporting arm corresponds to the mounting seat; the two ends of each supporting arm are hinged to the corresponding mounting base and the corresponding connecting piece correspondingly. The supporting arm is provided with an installation joint used for being connected to an aero-engine. The field force limiting mechanism comprises a first component and a second component which are oppositely arranged; the first component is arranged on the mounting platform, and the second component is arranged on the connecting piece; and the controller is electrically connected with the field force limiting mechanism. Through cooperative work of the field force limiting mechanism and the controller, the supporting rigidity of the auxiliary support can be dynamically adjusted according to the real-time rotating speed of the aero-engine in the test run process.

The utility model discloses a rotation measuring device for an aero-engine test bed, which belongs to the technical field of aero-engine test beds and comprises an oil storage supporting box, one end of the oil storage supporting box is fixedly sleeved with a front adapter, and the other end of the oil storage supporting box is fixedly sleeved with a rear adapter. A measuring circular ring is rotationally connected between the front adapter and the rear adapter and located in an inner cavity of the oil storage supporting box, and three measuring mechanisms are arranged on the measuring circular ring. According to the utility model, the lubricating oil is arranged at the bottom of the inner cavity of the oil storage supporting box, and when the first motor drives the pinion to rotate and the measuring circular ring and the plurality of measuring mechanisms are driven to rotate through the meshing transmission between the pinion and the bull gear, the meshing transmission part between the pinion and the bull gear is lubricated by using the lubricating oil; and abrasion between the small gear and the large gear is relieved, the service life of the small gear and the large gear is guaranteed, and the practicability of the device is good.

The application discloses a remote control torch ignition system based on wireless instruction and fault self-diagnosis function and relates to the technical field of space propulsion. The application comprises a remote control center and a field control unit. The remote control center is used for generating an encrypted ignition instruction package containing an ignition instruction sequence and adjustable parameters and sending the package through a wireless data link, simultaneously receiving and displaying control feedback and diagnosis data from the field. The field control unit is arranged on an engine test stand and is electrically connected with a torch igniter and its matched fuel valve, oxidant valve and ignition power supply, used for receiving, decrypting and executing the encrypted ignition instruction package to control the corresponding valves and ignition power supply to act in sequence. The system further comprises a multi-dimensional data acquisition module used for synchronously acquiring multi-channel physical quantity time sequence signals reflecting the working state of the igniter during the ignition process. Through embedded multi-dimensional time sequence fusion diagnosis, the application can quantitatively evaluate the performance gradual state of the torch igniter in real time.

The present application belongs to the field of aero-engine ground test technology, and provides an aero-engine test stand ground vortex test method and device. The method coats a brightening coating on the fan blades, rotating cap cover and inlet duct inner wall of the engine, and sets a background plate and a side high-speed camera on both sides of the inlet duct, wherein the background plate is opposite to the side high-speed camera and is in the field of view of the side high-speed camera, and the surface of the background plate is provided with a high-density random speckle pattern; the front high-speed camera is arranged opposite to the inlet duct to construct a double-view high-speed imaging system. When the engine is stably operated at a target speed, the double cameras are synchronously triggered to shoot image sequences; the cross-correlation calculation is performed based on the side image and the vortex-free background speckle pattern to generate a ground vortex center trajectory and fit a development curve; and the ground vortex centroid and cross-sectional area are determined based on the front image through a gray scale weighting method. The method does not need to invade the flow field, and can realize the synchronous quantification of the spatial evolution and cross-sectional morphology of the ground vortex.

The invention relates to the technical field of spaceflight, and discloses an emergency shutdown system and method for a rocket engine test bed, and the system comprises a sensor output module which is used for receiving the input and output of a pressure sensor signal and a frequency signal, and outputting a sensor signal; the simulation module is used for loading simulation signals and simulating various signal combinations in an emergency shutdown scene; the signal switching module is used for switching a sensor signal and a simulation signal by using a two-in and one-out interface assembly; the signal acquisition and processing module adopts an FPGA (Field Programmable Gate Array) and DMA (Direct Memory Access) hardware structure, performs interpretation according to an emergency shutdown condition when receiving the starting signal, and outputs an emergency shutdown signal when the emergency shutdown condition is met; the control module is used for completing the emergency shutdown action when receiving the emergency shutdown signal, and by switching the sensor signal and the simulation signal, the requirements of different test scenes are met, the emergency shutdown condition interpretation is executed, the automatic emergency shutdown function is achieved, and the safety and the emergency shutdown debugging efficiency are improved.

The utility model discloses an aero-engine test bed tail gas treatment device, which relates to the technical field of tail gas treatment, and comprises a bottom plate, a silencing mechanism is arranged at the top of the bottom plate, an adsorption mechanism is arranged at one end of the silencing mechanism, a spraying mechanism is arranged at one end of the adsorption mechanism, and the spraying mechanism comprises a spraying box. And the spraying box is fixedly connected to the top surface of the bottom plate. Through cooperation of the spraying mechanism, the spraying box, the drainage pipe, the fixing ring, the motor, the first gear, the second gear, a water guide pipe, a gas outlet pipe, a valve, a water tank, a water inlet pipe, a hollow pipe, an atomizing nozzle and a connecting groove, tail gas is atomized and sprayed by using a catalyst in the spraying box after being adsorbed, so that the temperature of the tail gas can be reduced; the device can protect surrounding facilities and instruments, absorb unadsorbed toxic gas in the tail gas, prevent the toxic gas from being discharged into the air, reduce pollution of harmful gas emission to the atmospheric environment and protect the ecological environment.

The invention relates to a sand vibration isolation foundation of a medium-high speed engine test bed, and belongs to the field of engine test bed foundations. The device sequentially comprises a concrete cushion layer, a concrete shell foundation, a sand vibration isolation layer, a balancing weight, a sizing block and a cast iron bottom plate. A brick mold and an outer waterproof layer are arranged on the outer side of the concrete shell foundation, an inner waterproof layer is arranged on the inner side of the concrete shell foundation, trenches are formed between the two sides of the balancing weight and the concrete shell foundation, a steel cover plate is arranged above the trenches, and a slope is made at the bottom of the trenches to facilitate liquid collection; the sand vibration isolation layer is further provided with a composite geomembrane and a steel mold, and liquid on the upper portion is isolated from permeating into the sand vibration isolation layer. Vibration mechanical energy transmitted from the upper portion is converted into heat energy to be dissipated by arranging the sand vibration isolation layer, vibration wave energy penetrating through the sand layer is reduced, compared with a common engine test bed foundation vibration isolation method, the excavation depth is reduced, the comprehensive manufacturing cost is reduced, the overhaul frequency is reduced or overhaul is avoided, and the construction cost is reduced. And meanwhile, the method can be adapted to a rack vibration isolation foundation form for transforming a built engine rack foundation to the maximum extent.

The utility model discloses an engine test bed steel frame, including steel column, hanging column and horizontal support spare, the utility model with steel column as the core bearing component, forms horizontal rigid connection through the first frame beam, second frame beam and steel beam of adjacent steel column top installation, constitutes spatial grid system, sets up the cross support system link between second frame beam, promotes the structural lateral displacement resistance ability significantly, combines steel beam pre-arch technology, ensures the stability under the large -span working condition, and the hanging column forms three point restraint system through internal structure, and the accurate positioning of cooperation assembly jig frame realizes the stable transmission of engine hoisting load, and the horizontal support spare constitutes the composite stress system by the vertical installation second connecting rod and the connecting rod of different inclination angle arrangement, forms spatial truss effect, effectively resists the horizontal vibration when the engine operation, prevents the frame torsional deformation, and the overall structure has high precision, anti -dynamic load and long -life characteristics.

The application provides an aero-engine test stand multi-sensor data space-time correlation detection method, comprising: selecting a certain specific test condition data, using different baseline modeling algorithms, respectively based on the physical space relationship of different sections of the aero-engine sensor, the physical space relationship of different measuring rakes and different radii on the same section, and the sensor data in a certain period of time, verifying the response data of the rake sensor and judging the abnormal condition of the sensor, correlating and deeply mining the multi-dimensional information of the aero-engine, and providing data support and important guarantee for the safety of the test system and the aircraft. The application can fully realize the verification and abnormal detection of the sensor response data in a short period under different test conditions.

The invention belongs to the technical field of test equipment design, and particularly relates to a top-down aero-engine test bed overall structure design method and system.The method comprises the steps that an initial design input set is formed according to test bed requirements and test working conditions; respectively mapping each design constraint in the initial design input set to a pre-divided test bed multi-level logic layer, and generating an initial main model scheme; forming a multidisciplinary constraint rule base according to a preset multidisciplinary interface requirement; according to the initial main model scheme and the sub-disciplinary design requirements, generating a corresponding disciplinary view model; and performing simulation analysis on the view models of each subject, and performing iterative optimization on simulation results of the view models of each subject in combination with design constraints and rule constraints to generate a final overall main model scheme. According to the method, the incidence relation of the subsystems and the coordination relation of multiple disciplines are comprehensively considered, synchronous updating of the models at all levels is achieved, and the design efficiency and the overall performance of the test bed are remarkably improved.

The application belongs to the technical field of liquid rocket engine test, and relates to a liquid rocket engine test bench tail gas energy efficient utilization system, which comprises an air source, an adjustable throat area nozzle assembly, a turbine power generation device and a controller. The air source is connected with one end of the adjustable throat area nozzle assembly through a first pipeline, and the other end of the adjustable throat area nozzle assembly is connected with the turbine power generation device through a second pipeline. The controller is connected with the first pipeline, the second pipeline and the adjustable throat area nozzle assembly to control the throat area change of the adjustable throat area nozzle assembly according to monitored pipeline parameters, and then adjust the nozzle outlet velocity, so that the turbine work can be at a higher working efficiency point. The application can improve the power generation efficiency of the power generation device.

The utility model discloses a turbojet engine test bed, which belongs to the technical field of turbojet engine test experiments and comprises a fixed seat, a movable plate slidably connected to the top of the fixed seat, a thrust sensor arranged between the movable plate and the fixed seat, supports connected to two sides of the movable plate, and an adjusting block connected to the top of each support through a first bolt. A strip-shaped hole is formed in the adjusting block, and a first bolt penetrates through the strip-shaped hole to fasten the adjusting block and the top end of the support. The tops of the adjusting blocks are connected with pressing blocks through bolts; the hoops comprise the upper hoops and the lower hoops, the multiple sets of hoops are arranged according to the size of the turbine engine, the upper hoops and the lower hoops are connected between the pressing block and the adjusting block in a fastened mode and used for holding and fixing the turbojet engine, and the tops of the upper hoops are connected with vibration collectors; the thrust sensor and the vibration collector are connected with an external processor through data lines. The device is small and portable in structure, easy and convenient to apply, wide in application range and suitable for turbojet engines of various specifications.

The invention discloses a light-weight design-based locking type liquid rocket engine test bench, which is characterized in that a bench is fixedly mounted on the ground or in a pit, a bracket I, a bracket II, a bracket III, a bracket IV, a bracket V, a bracket VI, a bracket VII and a bracket VIII are mounted below a flat plate, and a platform support I and a platform support II are mounted above the flat plate; the platform is mounted above the first platform support and the second platform support, and the mounting plate used for being connected with a liquid rocket engine is mounted above the platform through the mounting plate transfer platform. The test bench has the advantages that the liquid rocket engine can move along with the test bench, locking of the mounting plate switching platform and the platform can be realized, and the liquid rocket engine can be subjected to hot test run tests at different positions on the platform.

An aero-engine test stand oil supply device and method with exhaust function, the oil supply device comprises a test stand, further comprising an oil depot, an oil tank, an oil gas separation tank and a recovery tank; the oil depot is used for storing aviation kerosene, and the oil depot is connected to the oil tank through a first oil pipeline; a pressure pump is connected to the oil tank through an air pipe; the oil tank is connected to the oil gas separation tank through a second oil pipeline; the oil gas separation tank is connected to the test stand through a third oil pipeline; the oil gas separation tank is further connected to the recovery tank through a fourth oil pipeline; a first valve is arranged on the first oil pipeline, a second valve is arranged on the third oil pipeline, and a third valve is arranged on the fourth oil pipeline; a shock device is arranged beside the second oil pipeline and used for shocking the oil pipeline. The shock device can shock the oil pipeline, and the aviation kerosene containing gas can be discharged into the recovery tank after the pressure pump is pressurized, so as to solve the problem of exhaust of the aero-engine test stand oil supply pipeline.

The invention belongs to the technical field of aero-engine ground tests, and provides an aero-engine test bed ground vortex test method and device, and the method comprises the steps: coating the inner wall surfaces of an engine fan blade, a rotating cap cover and an air inlet channel with a brightening coating, and respectively arranging a background plate and a side high-speed camera at the two sides of the air inlet channel, wherein the background plate is positioned right opposite to the lateral high-speed camera and is positioned in the field of view of the camera, and the surface of the background plate is provided with high-density random speckle patterns; a front high-speed camera is arranged to directly face an air inlet channel, and a double-view-angle high-speed imaging system is constructed. When the engine stably operates at the target rotating speed, the double cameras are synchronously triggered to shoot an image sequence; performing cross-correlation calculation based on the lateral image and the vortex-free background speckle pattern, generating a ground vortex center track, and performing fitting to obtain a development curve; and determining the mass center and the sectional area of the ground vortex through a gray weighting method based on the front image. The method does not need to invade into a flow field, and can realize synchronous quantification of ground vortex space evolution and section morphology.

The utility model relates to high -power turbo shaft engine test board electrical system belongs to engine test technical field, including alternating current source, test board controller, first alternating current direct current converter, second alternating current direct current converter, direct current direct current conversion unit, alternating current source connects respectively dynamometer, emergency power supply, still through first alternating current direct current converter connection fuel oil electric governing pump distribution input end, through second alternating current direct current converter connection starting generator distribution input end, emergency power supply passes through direct current direct current conversion unit and connects engine electronic controller, test board controller respectively, the system still includes distributed data acquisition module and sensor signal isolation unit. The existing turbo shaft engine test board electrical device electrical wiring complex, control precision low, system reliability poor problem is solved.

The embodiment of the invention provides a test bed fault prediction method and device of an engine, electronic equipment and a storage medium, and relates to the technical field of computers. The method comprises the steps of obtaining a first data set; analyzing the first data set based on the value range of each parameter in the first data set to obtain an analysis result of the first data set; and if the analysis result represents that the first data set has the abnormal parameter value, inputting the first data set into the fault prediction model, and outputting predicted fault information. The parameter values collected on the sampling points are combined into a first data set, the first data set is analyzed, whether abnormal data exist in the first data set or not is judged, if yes, the first data set is input into the trained fault prediction model, and a fault prediction result of the test bed is output. According to the scheme, the fault of the test bed does not need to be detected manually, manpower can be saved, meanwhile, the analysis standard of abnormal data is unified, and high precision is achieved.

The invention relates to an auxiliary assembly device for a universal shaft of an engine test bed. The auxiliary assembly device comprises a base, a movable support, a bidirectional displacement mechanism, a bearing connecting structure and a positioning restraining mechanism. A horizontal reference coordinate system is arranged on the top of the base. The movable support is driven by a two-way displacement mechanism, a horizontal driving assembly of the movable support controls X-axis displacement, and a vertical driving assembly of the movable support controls Y-axis displacement. The bearing connecting structure is fixed to the upper end of the movable support, and the inner ring radially restrains the central shaft section of the universal shaft. The positioning constraint mechanism predefines end face three-dimensional coordinates and axial directions of the engine output shaft and the load shaft. The bidirectional displacement mechanism drives the two ends of the universal shaft to synchronously arrive at theoretical coordinate points in a linkage mode and are axially collinear, and full-automatic high-precision centering is achieved. The split type movable support supports the disc body to be separated from the base body and rotate along with the shaft. The closed-loop servo system compensates offset in real time, the gravity center coincident bearing and the damping shock absorption layer cooperate to guarantee transmission stability, the assembly precision is remarkably improved, and the service life is remarkably prolonged.

The invention belongs to the technical field of hydraulic pump load monitoring, and provides an airspace engine test bed hydraulic pump load system which is characterized in that the change trend type of output pressure in each flow conveying fluctuation time period is further analyzed, if load alternate impact is caused by output pressure change, the early warning intervention time is acquired, and in the early warning intervention time, the early warning intervention time is acquired; therefore, when the output pressure is close to an over-high or over-low early warning line, the intervention opportunity is determined in advance, a worker can have enough time to stably adjust the working state of the hydraulic pump, the sudden shutdown condition is avoided, dynamic adjustment operation is conducted on load alternate impact within the early warning intervention time, and the working efficiency is improved. And the load of the hydraulic pump is kept stable, so that the acquired data is accurate and reliable, and a powerful basis is provided for subsequent engine performance analysis and improvement.

The invention discloses a supersonic wind tunnel diffuser for a ramjet engine test bed, and solves the technical problems of large design difficulty and high control requirements caused by wide working condition design and high production cost and shortened service life of equipment caused by multi-model design. According to the supersonic wind tunnel diffuser, the contraction section, the equal straight sections, the expansion section and the cooling section of the supersonic wind tunnel diffuser are independently arranged, the number of the equal straight sections is N, and the universal flange assembly is designed, so that the design effects of variable layout and adjustable length are achieved, the test requirements of engines of different specifications are met, and the test cost is greatly reduced.

This invention discloses a composite exhaust device for a turboprop engine test stand, comprising a support frame, a propeller flow exhaust assembly mounted on the support frame for propeller flow exhaust, and a gas exhaust assembly for gas exhaust. The gas exhaust assembly includes an ejector tube arranged horizontally to maintain a set distance from the tail nozzle, a gas exhaust pipe extending horizontally and then bending vertically upward, and a gas exhaust tower arranged vertically. A portion of the gas exhaust pipe is fixedly arranged inside the propeller flow exhaust assembly, and another portion extends vertically outside the propeller flow exhaust assembly. The inlet end of the gas exhaust pipe is connected to the exhaust end of the ejector tube, and the exhaust end of the gas exhaust pipe is connected to the inlet end of the gas exhaust tower. This solution avoids problems such as poor propeller flow exhaust and gas backflow, and the propeller flow exhaust assembly does not need to consider the influence of gas temperature, thus reducing the material and manufacturing costs of the composite exhaust device and making it suitable for widespread promotion and application.

The present disclosure relates to a control method for an aero-engine test stand comprising a hydraulic servo regulating valve, comprising: monitoring test working conditions of the aero-engine test stand; and controlling the hydraulic servo regulating valve in a safe state according to different test working conditions. The different test working conditions include: occurrence of a sudden state and triggering of an emergency signal, loss of a control signal of the hydraulic servo regulating valve, and abnormality of a position feedback signal of the hydraulic servo regulating valve.

Method for analyzing and evaluating measured values ​​of a test system designed as an engine test bench in which internal combustion engines are examined, wherein a test specimen is monitored during a test run by means of a plurality of sensor means and each of the sensor means provides measured values ​​of at least one measured quantity to an evaluation device for further processing, characterized in that a logic tree is generated for a plausibility check of the measured values ​​of the measured quantities, by means of which a plausibility is determined according to predefined rules by forming and using a presumably true value for each of the measured quantities.

The utility model provides a test bed for a liquid oxygen methane engine. The test bed comprises a gas path system, a liquid path system and a test station. Wherein the gas path system and the liquid path system are connected through a pipeline for gas supply, and the liquid path system is connected with the test run station and used for providing liquid fuel needed by testing for the test run station. The gas path system comprises a first liquid nitrogen warehouse module, a second liquid nitrogen warehouse module, a gas making module and a gas distribution module. The first liquid nitrogen warehouse module comprises a first liquid nitrogen warehouse storage tank used for storing liquid nitrogen. The second liquid nitrogen warehouse module comprises a second liquid nitrogen warehouse storage tank used for storing liquid nitrogen. The gas making module comprises a liquid nitrogen storage box, a liquid nitrogen plunger pump, a liquid nitrogen vaporizer and a high-pressure nitrogen cylinder set. Wherein the liquid nitrogen in the first liquid nitrogen storage tank is filled into the liquid nitrogen storage tank through the second liquid nitrogen filling pipeline and is pumped into the liquid nitrogen vaporizer through the liquid nitrogen plunger pump to be gasified, and the gasified nitrogen is stored in the high-pressure nitrogen cylinder group. And the high-pressure nitrogen cylinder group is conveyed into the nitrogen distribution module through a nitrogen conveying main pipeline. The test bed is composed of a set of gas path system, two sets of liquid path systems and three test stations. The two sets of liquid path systems jointly adopt one set of gas path system for gas supply, so that medium conveying can be carried out on the three test run stations according to requirements, the test run platform can meet the gas distribution requirements of engines of different models, meanwhile, the resource sharing of test equipment is improved, the total cost of equipment construction and maintenance is greatly reduced, and the working efficiency is improved. And the engine testing efficiency is improved.

The embodiment of the invention provides an engine test bench and a methanol filling system and a methanol filling method thereof. The methanol filling system comprises a daily container; a storage container; the filling unit comprises a controlled backflow pipeline, a controlled filling pipeline and a pumping module, the controlled backflow pipeline is connected between the pumping module and the storage container, the controlled filling pipeline is connected with the pumping module, and the pumping module is in pipeline connection with the daily container and the storage container; the filling unit is used for pumping methanol in the storage container to the daily container through the pumping module under the condition that filling of the controlled filling pipeline and filling of the storage container are both closed and filling of the controlled backflow pipeline and filling of the daily container are both opened. According to the embodiment of the invention, the methanol filling system can be simplified, so that the volume of the methanol filling system can be reduced.

The application provides a multifunctional test system of a liquid oxygen-methane engine test stand, which comprises a gas path system, a liquid path system, a test station and a control module. The gas path system and the liquid path system are connected by pipelines for gas supply, the liquid path system is connected with the test station for providing liquid fuel required by the test station, and the control module is connected with the gas path system and the liquid path system for controlling the operation of the gas path system and the liquid path system. The liquid path system comprises a liquid oxygen storage module, a liquid methane storage module, a liquid oxygen supercooling module, a liquid methane supercooling module, a liquid oxygen conveying module and a liquid methane conveying module. The multifunctional test system is composed of one gas path system, two liquid path systems and two test stations. The two liquid path systems comprise a high-pressure and low-pressure liquid oxygen liquid path module and a high-pressure and low-pressure liquid methane liquid path module, which are connected with one gas path system for gas supply, can convey medium according to requirements, improve the resource sharing of the test equipment, reduce the total cost of equipment construction and maintenance, and improve the efficiency of engine test.

A kind of supersonic engine test bench, high-altitude simulation cabin is the shell structure of sealing, engine thrust measuring rack is fixedly installed in high-altitude simulation cabin, test engine is installed on engine thrust measuring rack;Intake system is communicated with the test engine or exhaust system, one end of exhaust system is fixedly installed in high-altitude simulation cabin through the shell surface of high-altitude simulation cabin, and the other end is fixedly communicated with the tail gas treatment system.The supersonic engine test bench of the application realizes the supersonic intake state simulation of supersonic engine when supersonic engine and engine ground test are carried out;At the same time, its engine thrust measuring rack realizes the measurement of engine thrust, simple structure, in addition, the exhaust gas of engine test bench is treated, so that the gas discharged from the gas outlet of alkaline spray tower meets the national pollutant discharge standard;Through setting silencing tower, the exhaust of exhaust system is silenced and noise is reduced, and noise pollution is avoided.

The invention provides an aero-engine test bed, relates to the technical field of aero-engines, and aims to solve the technical problem of high pollution risk of the aero-engine test bed. The aero-engine test bed comprises an injection cylinder, a first catalyst treatment device, a first space, a second space and an exhaust tower, the first space, the second space and the exhaust tower are sequentially arranged, and the first space is used for installing an aero-engine; the injection cylinder is arranged in the second space, one end of the injection cylinder is communicated with the first space, and the other end of the injection cylinder extends into the exhaust tower and is located in the area, close to the bottom, of the exhaust tower. According to the aero-engine test bed, the tail gas purification efficiency is effectively improved, and the risk of emission pollution is reduced.

The application relates to an aero-engine external oil system, which comprises a first oil tank, a second oil tank and the like; the system can work in an engine oil injection mode, an oil system self-flushing mode, an open external circulation mode, an internal self-circulation mode and an engine oil change mode; the application can realize automatic switching of two oil supply and return modes of the external open circulation and the internal self-circulation of the engine, simultaneously has the functions of cooling and heating the oil, and has the functions of measuring the oil supply amount and the oil consumption amount, and the applicability of the oil system of the test bench under different scenes is improved.