913results about "Engine testing" patented technology

The invention discloses a spraying system for an aeroengine icing test and a high-altitude icing simulation test bed, the spraying system comprises a spraying device, the spraying device comprises a spraying support and a plurality of atomizing pipe groups, and the plurality of atomizing pipe groups are detachably arranged on the spraying support. Each atomizing pipe group comprises a heat insulation coating barrel, a plurality of atomizing nozzles sequentially arranged in the length direction of the heat insulation coating barrel, a water supply pipe and an air supply pipe which are arranged in the heat insulation coating barrel in the length direction of the heat insulation coating barrel, and a heat insulation material filled in the heat insulation coating barrel; the inner side end, located in the heat insulation wrapping barrel, of the atomizing nozzle communicates with a water supply pipe and an air supply pipe, the opposite outer side end of the atomizing nozzle extends out of the heat insulation wrapping barrel, and at least one end of the water supply pipe and at least one end of the air supply pipe extend out of the spraying support to correspondingly introduce water and compressed air. According to the invention, the atomization pipe group can be taken out as required for deep maintenance, and meanwhile, the anti-freezing and anti-blocking capabilities of the water supply pipe and the air supply pipe in the test process are improved, so that the long-time duration of the icing test of the aero-engine is ensured.

The invention belongs to the technical field of aero-engines, and particularly relates to an array type energy absorption target plate. Comprising a support frame; the multiple knife-shaped columns are fixed to the supporting frame at intervals, and cutting edges of the knife-shaped columns face the throwing direction of an impact object; the energy absorption turning plates are hung between the adjacent knife-shaped columns in a turnover mode through rotating shafts and arranged into a multi-layer array in the vertical direction, and the energy absorption turning plates are configured to turn over when being impacted so as to allow an impacted object to pass through and absorb kinetic energy of the impacted object; the inclined back plate is obliquely arranged on the side, opposite to an impact object, of the array type energy absorption turning plate, and the projectile body collecting box is located below the inclined back plate and used for collecting the impact object penetrating through the energy absorption turning plate array.

The invention relates to a centrifugal compressor high-altitude environment dynamic simulation test system. The system comprises a compressor test module; the high-altitude environment simulation module comprises an air inlet surge tank, an air inlet assembly and a first air exhaust assembly which are arranged at the upstream of the air inlet pipeline, and an air exhaust surge tank and a second air exhaust assembly which are arranged at the downstream of the air exhaust pipeline; a measurement module; the control module is used for comparing the first actually-measured pressure value with a target altitude pressure value of the air inlet end and controlling the air inlet amount of the air inlet assembly and the air suction amount of the first air suction assembly according to a comparison result, so that the pressure of the air inlet pressure stabilizing tank is stabilized at the target altitude pressure of the air inlet end; and the control module compares the second actually measured pressure value with the target altitude pressure value of the exhaust end, and controls the air suction amount of the second air suction assembly according to the comparison result, so that the pressure of the exhaust surge tank is stabilized at the target altitude pressure value of the exhaust end. It is ensured that test data can truly reflect the actual plateau working condition performance of the gas compressor.

The invention provides an engine in-the-loop semi-physical simulation test platform for a hybrid electric vehicle, which relates to the technical field of automobile engine testing and comprises a real-time virtual simulation platform and an engine transient test platform. The real-time virtual simulation platform comprises a driver model module, an energy management strategy module, a power assembly module, a vehicle dynamics module and an exhaust temperature control module. The driver model module carries out data calculation according to the output of the vehicle dynamics module, a vehicle dynamics model calculates a dynamics state threshold value, and energy management is carried out through the energy management strategy module; the engine transient test platform comprises an engine controller, a high-dynamic electric dynamometer, a dynamometer control system, an engine, a post-processing system, an emission detection system and a post-processing temperature control system. According to the platform, a real engine pedestal, a digital hybrid power whole vehicle model and a rapid prototype controller are deeply integrated, so that the model reusability is improved.

The utility model discloses an ammonia fuel low-speed engine test bed security system which comprises a plurality of two-way electromagnetic valves, a plurality of one-way valves, a plurality of pressure sensors, an air supply fan, an air draft fan, a manual two-way valve, a buffer tank, an ammonia detector, a three-way electromagnetic valve, a flow meter and an outdoor ammonia steam tank. And a signal line of the PLC is respectively connected with the control ends of the two-way electromagnetic valves, the pressure sensors, the air supply fan, the air draft fan and the flow meter. Under different working conditions of slight leakage or serious leakage of ammonia fuel, the leaked ammonia fuel is recovered into the outdoor ammonia evaporation tank, so that the safety of field personnel is ensured, and a reliable guarantee is provided for safe and reliable test run of the ammonia fuel low-speed engine.

The utility model relates to a portable dynamometer torque calibration device, and belongs to the technical field of rack torque calibration. Comprising a force arm, one end of the force arm is fixedly connected to a dynamometer, the other end of the force arm is provided with a force value sensor, a force applying mechanism is arranged below the force value sensor and applies force to the force value sensor, and the force value sensor is used for detecting a torque value and then comparing the torque value with a torque value of the dynamometer. The force applying mechanism comprises a bottom plate, a fixed pulley is arranged on the bottom plate, a movable pulley is arranged at the bottom of the force value sensor, a supporting rod is arranged on the bottom plate, a force applying lever obliquely arranged downwards is hinged to the supporting rod, a chain is wound around the fixed pulley and the movable pulley, and one end of the chain is arranged at the front end of the force applying lever. And the other end of the chain is fixed on the bottom plate. According to the invention, when the force application mechanism is used for applying force, the force application is very labor-saving, the operation is convenient, time-saving and labor-saving, the quick calibration of the dynamometer torque on the rack site is realized, and the calibration efficiency is improved.

The embodiment of the present application provides an engine suspension test bench, method, equipment and storage medium, comprising: a vibration table for restraining and installing an engine and suspension to be tested; a support buffer arranged below the vibration table, used for supporting the vibration table and the engine and suspension to be tested, so that the vibration table and the engine and suspension to be tested are in a suspended state; an exciter arranged on opposite sides of the vibration table, the exciter being used for driving the vibration table to vibrate when in-phase excitation or anti-phase excitation, so as to simulate road vibration; and a controller connected with the exciter, used for in-phase excitation or anti-phase excitation of the exciter. Through the test of the bench of the embodiment of the present application, the vibration performance similar to the road surface can be simulated, the risk assessment and abnormal sound problem reproduction function of the suspension abnormal sound are realized, so that the verification period is shortened and the comprehensiveness of the test is ensured.

The invention discloses a test run fixing device and method for a carrier rocket power system, and the device comprises an inhaul cable device which is suitable for being fixed to the top of the carrier rocket power system; the pre-tightening device is provided with a first end and a second end, the first end of the pre-tightening device is used for being connected with a test bed so as to fix the pre-tightening device, and the pre-tightening device can selectively adjust the pre-tightening force of the first end and the second end; the second end of the pre-tightening device is connected with the inhaul cable device through the rigging, and a sensor used for detecting the pulling force of the rigging is arranged on the rigging; and the monitoring device judges whether the tension detection value of the sensor meets a preset range or not and sends out an alarm signal and / or adjusts the pre-tightening force of the first end and the second end of the pre-tightening device after the tension detection value exceeds the preset range. According to the test run fixing device, the tension of the rigging can be adjusted through the pre-tightening device, the tension of the rigging is adjusted under the abnormal condition, and the safety and applicability of carrier rocket power system test run are improved.

The invention relates to the technical field of fuel nozzle performance testing, in particular to an integrated high-precision fuel flow testing method and detection method.The testing method comprises the steps that a spraying test bed or a nozzle test bed is correspondingly selected based on whether a to-be-tested workpiece tests the spraying angle or not; after the integrated high-precision fuel oil flow testing device is in a reset state, a corresponding motor rotating speed is input to a digital control system based on the calibrated flow of the workpiece to be tested, a plunger pump of a high-pressure oil supply system is started, and oil liquid in an oil tank system is pumped to a corresponding spray test bed or nozzle test bed to run; the actual pressure difference of the workpiece to be measured is collected and transmitted to the digital control system, the actual pressure difference and the target pressure difference are compared, and the actual pressure difference is adjusted; when the preliminarily obtained actual oil flow is larger than a detection threshold value, the actual oil flow corresponding to the current flowmeter is defined as corresponding detection data; and when the preliminarily obtained actual oil flow is smaller than or equal to the detection threshold value, a weighing method is adopted for flow detection.

The invention discloses a low-vortex prewhirl nozzle casing air flow rapid detection clamp and a detection method, the clamp mainly comprises a base, a supporting seat, an air inlet pipe, an air outlet pipe, an upper sealing support plate, a lower sealing support plate, a pressing plate and the like, the supporting seat supports and seals a front installation edge large spigot and a rear installation edge large spigot of a low-vortex prewhirl nozzle casing, and the pressing plate supports and seals the front installation edge large spigot and the rear installation edge large spigot of the low-vortex prewhirl nozzle casing. The lower sealing support plate is used for sealing and radially restraining the small seam allowance of the rear mounting edge, and the upper sealing support plate is used for sealing and radially restraining the large seam allowance and the small seam allowance of the front mounting edge, so that all cavities of the low-vortex pre-swirl nozzle cartridge receiver are sealed. When the air flows of two different paths are measured, the clamp only needs to be clamped once, the clamp does not need to be detached in the middle, and the air flows of different outlets can be measured only by pressing the lower sealing support plate or loosening the lower sealing support plate. According to the invention, the prominent problems of slow test and air leakage are solved, and rapid detection data are provided for optimization of the low-vortex pre-swirl nozzle casing flow channel.

The invention relates to the field of aero-engine compression part test state monitoring and evaluation, and discloses a compression part stall early warning method and system based on shunting heterogeneity. A first pulsating pressure signal only containing main blade sweeping frequency characteristics and a second pulsating pressure signal only containing splitter blade sweeping frequency characteristics are obtained; and superposing the first pulsating pressure signal and the second pulsating pressure signal, and constructing an analysis model of pulsating pressure non-consistency parameters of the main blade and the splitter blade to dynamically obtain the change condition of the pulsating pressure non-consistency parameters of the main blade and the splitter blade along with the sampling number. By setting the threshold value of the coefficient in the critical stall state of the compression component, when the non-consistency parameter output value of the analysis model reaches the preset critical threshold value, it can be judged that the compression component reaches the critical stall point, and therefore stall early warning is given out in time, equipment damage and safety accidents are avoided, and the purpose of stall monitoring and early warning is achieved.

The invention relates to the field of gas ejectors, in particular to a valve needle stroke monitoring device and method.The valve needle stroke monitoring device comprises a clamping mechanism, a magnetic induction mechanism, a double-guide reset mechanism and a shell mechanism, and the clamping mechanism is used for clamping a valve body of the gas ejector; the magnetic induction mechanism comprises an ejector rod, a magnet and a Hall effect sensor, one end of the ejector rod is configured to be in contact with the end part of a valve needle of the gas ejector, the magnet is arranged at the other end of the ejector rod, and the Hall effect sensor is arranged opposite to the magnet to detect the displacement of the magnet; the double-guide reset mechanism is used for providing axial reset force for the ejector rod; the shell mechanism is used for integrating the clamping mechanism, the magnetic induction mechanism and the double-guide reset mechanism. According to the method, the real-time stroke of the valve needle is calculated according to the difference value between the real-time position signal and the initial position signal. By adopting the technical scheme, the stroke of the valve needle can be directly measured in a high-precision, high-reliability and convenient-to-mount manner.

An engine backfire problem-based alarming method, apparatus, and device, and a computer-readable storage medium. The method comprises: on the basis of collected information on the current vehicle speed and information on the temperature change of an air inlet pipe, determining whether a backfire problem occurs in an engine of a vehicle; if it is determined that the backfire problem occurs in the engine, calculating a total pressure impact on the air inlet pipe generated by the occurrence of the backfire problem in the engine; and sending alarm information on the basis of the total pressure impact on the air inlet pipe generated by the occurrence of the backfire problem in the engine. The method solves the existing technical problem in the related art that, when an engine backfire problem occurs, natural gas burns in an air inlet pipe, causing the air inlet pipe to crack, thereby rendering a vehicle unable to travel. The method enables an accurate determination of the change in strength of an air inlet manifold on the basis of a pressure impact generated by a backfire problem, thereby identifying in advance whether the air inlet manifold is cracked, providing an advance alarm to prompt replacement of the air inlet manifold, and avoiding the inability of the vehicle to travel due to cracking of the air inlet manifold.

The utility model discloses an airplane throttle lever onboard installation state simulation device, which belongs to the field of airplane throttle lever manufacturing and repairing and comprises a table-board type support frame and a throttle lever installation frame fixed on one side of the top end face of the table-board type support frame, the other side of the top end face of the table-board type support frame is detachably connected with a pulley assembly, and the other side of the top end face of the table-board type support frame is detachably connected with the throttle lever installation frame. A mounting hole is formed in the top end face of the throttle lever mounting frame, the throttle lever mounting frame and an external throttle lever are detachably connected by implanting a hexagon bolt into the mounting hole, a sliding rail is arranged on the top end face of the table-board type supporting frame, and the pulley assembly is arranged on the sliding rail and can be adjusted in position. And the slide rail is fixed on the slide rail through a T-shaped bolt and a butterfly nut. According to the utility model, the on-board installation state of the throttle lever can be simulated more truly, thereby reducing the difference.

This invention discloses a dynamic pressure-based method for testing and analyzing hammer shock waves in aero-engines, belonging to the field of aero-engine testing and structural strength design. The method first uses a surge-induced pressure method to generate hammer shock waves at the engine inlet. Based on the flow field characteristics of the air intake outlet section (AIP section) during surge, dynamic total pressure and static pressure measuring points are arranged in a combination of circumferential and radial directions. Pressure signals are synchronously recorded using a high-speed data acquisition system, and four characteristic parameters—surge overpressure, overpressure ratio, loading time, and pressure rise rate—are defined to quantitatively analyze the intensity, spatial distribution, and dynamic process of the hammer shock waves. This invention achieves rapid, accurate, and comprehensive characterization of the aerodynamic load of hammer shock waves, providing reliable input loads directly for the strength design of complex structures such as S-curve air intakes, thereby improving aircraft safety.

The invention provides a blade flying-off simulation device, rotor test equipment and a rotor test method, and relates to the technical field of aero-engine rotor dynamics tests. The blade flying-off simulation device is suitable for simulating blade flying-off working conditions and comprises a wheel disc and at least one flying-off assembly, the flying-off assembly is arranged on the edge of the wheel disc, and the flying-off assembly comprises simulation blades movably arranged on the wheel disc in the radial direction of the wheel disc; the release mechanism is arranged on the simulation blade, and the release mechanism has a locking state for restraining the simulation blade on the wheel disc and a release state for allowing the simulation blade to move in the radial direction of the wheel disc and be separated from the wheel disc.

The application discloses a kind of wind-induced vortex-induced vibration generator magnetic restoring couple moment testing device, including swing angle drive and limiting system, measurement system, magnetic restoring couple moment generation and transmission system.Swing angle drive and limiting system include swing angle limiting disc, swing angle drive disc, swing angle positioning pin.Swing angle drive disc is rotated under the drive of driving handle, around swing angle limiting disc rotating shaft, and drive torque instrument, swing shaft and swing permanent magnet to rotate around swing angle limiting disc rotating shaft with the same angular velocity.Swing permanent magnet generates magnetic restoring couple moment under the action of other two fixed permanent magnets, and the size of magnetic restoring couple moment is measured by swing shaft transmission to torque instrument, while laser ranging sensor measures the swing distance of swing shaft, and the change relationship between magnetic restoring couple moment and swing angle can be obtained after converting into swing angle.The application has simple structure, stable and reliable work, and has very important engineering application value.

The present application relates to the technical field of test bed, and discloses a supporting device, a test bed and a test installation method. The supporting device comprises a mounting platform, mounting seats, supporting arms, a damping assembly and a mounting joint. The mounting seats are arranged at intervals on the mounting platform. The supporting arms are rotatably connected to the mounting seats at one end. The damping assembly comprises elastic members and connecting members. The other ends of the supporting arms are rotatably connected to the connecting members. The connecting members and the mounting platform are arranged at intervals. The elastic members are arranged between the connecting members and the mounting platform and are used for supporting the connecting members. The mounting joint is arranged on the supporting arms and is used for connecting a test piece. The present application helps to reduce the safety hazards of the test piece and improve the test efficiency.

Test stand device 1 for the steerable mounting of a wheel R of a vehicle to be tested or a wheel assembly RM comprising: a support element 2 for setting up the wheel R with at least one connecting element 30 in a region of an end section of the support element 2, at least two air bearing elements 40 for supporting the support element 2, wherein each air bearing element 40 supports at least one connecting element 30.

The application discloses a system and method for processing virtual development bench hardware-in-the-loop heat dissipation, and is used for improving a hardware-in-the-loop running environment. The system comprises a flat plate heat exchange module, a fan module, an oil inlet pipeline, a fan control module, a hardware-in-the-loop cabinet, an oil outlet pipeline, an oil quantity measurement unit, an oil sprayer, a cooling oil tank, a temperature sensor, a cooling tank connecting pipeline and an oil circulation pump. The flat plate heat exchange module is connected with the oil inlet pipeline, the cooling tank connecting pipeline, the cooling oil tank and the oil outlet pipeline in sequence. The flat plate heat exchange module is provided with the fan module on one side, the fan module is connected with the fan control module, the hardware-in-the-loop cabinet is connected with the fan control module, the temperature sensor and the oil circulation pump, the temperature sensor is arranged on the cooling tank connecting pipeline and the sensing head of the temperature sensor is immersed in the oil medium, the oil circulation pump is installed at the connecting port of the cooling tank connecting pipeline and the oil inlet pipeline, and the oil quantity measurement unit and the oil sprayer are both installed on the cooling oil tank and the heads of the oil quantity measurement unit and the oil sprayer are both immersed in the oil medium to a preset depth.

The application discloses a heat testing device for sweat cooling panels under high-temperature fuel state, and aims at solving the technical problem that the existing cold flow measurement method cannot accurately measure the permeability and compatibility of sweat cooling panels under high-temperature working conditions. Specifically, the heat testing device comprises a test shell and a heating mechanism; the test shell is internally provided with a high-temperature fuel cavity for placing the sweat cooling panel; the high-temperature fuel cavity is used for simulating the fuel flow channel of an engine combustion chamber; the bottom of the test shell is provided with multiple fuel inlets in parallel and communicated with the high-temperature fuel cavity, and is also provided with multiple fuel outlets in parallel and communicated with the high-temperature fuel cavity; the top of the test shell is provided with at least one sweat outlet communicated with the high-temperature fuel cavity; and the heating mechanism is connected with the test shell and used for heating the test shell. The heat testing device can test the permeability of fuel under high-temperature state or the permeability of sweat cooling panels under high-temperature state, and can also complete the compatibility test of high-temperature fuel, sweat cooling panels and high-temperature alloy structures.

The invention relates to the technical field of spacecraft propulsion system measurement, in particular to a device and a method for measuring response time and thrust of a microminiature thruster. A thrust frame of the device is arranged in a vacuum chamber, a to-be-tested thruster and a laser transmitter are installed on the thrust frame, and a gas source provides gas for the to-be-tested thruster. The laser receiver and the laser transmitter are arranged at an interval, and the laser receiver is used for receiving laser transmitted by the laser transmitter. Computer calculates thruster opening response time and thruster closing response time through transmission light intensity change time and control signal emission time difference and calculates thrust according to thrust data acquired by force sensor in time period from thruster starting control signal fluctuation first tending to stabilize to thruster starting control signal termination and the force device stabilizes the thrust. According to the device, laser is used for irradiating plume of the miniature thruster, the body structure of the thruster is not damaged, rapid non-contact measurement of the response time of the thruster is achieved, and steady-state thrust measurement of the thruster can also be achieved.

The invention discloses a method and system for analyzing factors influencing radial expansion of flash jet flow of an oil injector, and relates to the field of oil injectors. Flash evaporation spraying images of the single-hole oil sprayer under different thermal working conditions are collected; the thermal working condition comprises injection temperature and environment pressure; obtaining a spraying width within a preset axial distance from a nozzle outlet according to the flash evaporation spraying image; establishing a nucleation rate model according to the injection temperature and the environment pressure; determining a nucleation rate index according to the nucleation rate model; taking the spray width as a measurement index of radial expansion, and establishing an incidence relation between the spray width and a nucleation rate index; according to the incidence relation, determining a factor influencing radial expansion: when the spray width is increased along with the increase of the nucleation rate index, the influence factor is the nucleation rate; when the spray width tends to be stable along with the increase of the nucleation rate index, the influence factor is heat energy required by vaporization.

The present application relates to the technical field of high-temperature pipeline dynamic stress measurement of an aero-engine, in particular to a strain gauge installation method. The method marks a patch area on a high-temperature pipeline to be measured, and performs surface treatment on the high-temperature pipeline in the patch area. After the treatment, the patch area is coated with primer, and pre-solidification is performed. Secondary coating is performed on the primer to form a bonding layer. The stress gauge is attached to the bonding layer, and the bonding layer is solidified. The glass cloth fixing frame on the stress gauge is removed, and the bonding layer is secondarily solidified. The stress gauge is coated to form a cover layer. The cover layer is finally solidified to achieve the installation of the strain gauge. Through detection, the survival rate of the installed strain gauge reaches 80%, solving the problem of low measurement success rate due to the brittleness and damage of high-temperature strain gauges in the existing high-temperature pipeline dynamic stress measurement process.

The invention discloses an engine pedestal oil supply pressure regulating system which comprises an engine assembly, a plurality of oil depots, an oil tank and a regulating assembly, the engine assembly is used for measuring oil consumption, the oil depots are arranged side by side and used for storing different types of oil products, and the oil tank is arranged above the engine assembly and used for temporarily storing the oil products. The oil tank can communicate with the multiple oil depots and the engine assembly, and the regulation and control assembly is arranged between the oil tank and the engine assembly and between the oil depots and used for controlling the oil tank to communicate with the engine assembly and the oil depots. According to the invention, the problems that gas exists in fuel oil and the pressure is violently fluctuated after pressure reduction due to relatively large pressure fluctuation when a pressure reducing and regulating valve group is used for supplying oil and regulating pressure for an engine pedestal can be effectively solved.

The application discloses a turbine blade film hole detection device and a detection method, and belongs to the field of turbine blade film hole processing technology, and comprises a detection device base, a rotating base, a fence, a pressing clamp and a strong light lamp; the rotating base is installed on the top of the detection device base; the fence is installed on the outer side of the rotating base; the pressing clamp is installed on the rotating base and is used for fixing and positioning the detected part; the strong light lamp is installed in the cavity of the detected part, the strong light emitted by the strong light lamp passes through the film hole and is used for judging whether the film hole of the part is through or not. The application is used for the film hole permeability detection of the hollow turbine blade of an aero-engine, and makes up for the defects of the high-pressure water detection and the human eye recognition detection mode.

The application discloses a method and system for testing the reliability of a natural gas engine, the method comprising: controlling the outlet water temperature of the natural gas engine to be in a hot state working condition zone and working at the maximum net power speed and full load for a first preset time; the temperature range of the hot state working condition zone being 105-110 DEG C; controlling the outlet water temperature of the natural gas engine to enter a cold state working condition zone, keeping the maximum net power speed, reducing the load from full load to zero load and keeping for a third preset time for a second preset time; the temperature range of the cold state working condition zone being 25-30 DEG C; controlling the load of the natural gas engine to increase from zero load to full load while keeping the maximum net power speed for a fourth preset time; and returning to the step of controlling the outlet water temperature of the natural gas engine to be in the hot state working condition zone. The cold-hot temperature difference can realize the maximum measurement of the engine and fully meet the simulation of possible actual situations.

The utility model discloses a recovery device for an oil rail pressure testing machine, which comprises a recovery cover, an oil leakage pipe, a filter screen, an electric heating wire and an oil receiving tank, an inlet of the oil leakage pipe is connected to the bottom of the recovery cover; the filter screen is mounted at an inlet of the oil leakage pipe; the electric heating wire is mounted in the filter screen; the engine oil recovery device has the advantages that engine oil is guided to the oil leakage pipe through the inner wall of the recovery cover and then flows into the oil receiving tank, a complete recovery path is formed, cleaning frequency is reduced, and cost is saved.

The utility model provides a diesel engine piston experiment device which comprises a piston model, a transmission mechanism, a simulation cylinder cover and an experiment table. The piston model is located in an inner cavity of the simulation cylinder cover; the simulation cylinder cover is installed on the experiment table, the bottom of the piston model is connected with the piston rod, and the piston rod is connected with the transmission mechanism. A combustion chamber is arranged on the upper surface of the piston model; an oil nozzle is arranged at the top of an inner cavity of the simulated cylinder cover; the piston model is internally provided with an annular cooling cavity, and the bottom of the inner cavity of the simulation cylinder cover is provided with a cooling liquid nozzle aligned with the inlet; the piston model is of a split structure, the split structure with the combustion chamber is the upper portion of the piston, and the side wall of the combustion chamber is partially or completely provided with an oleophylic coating. According to the utility model, the detonation process of different combustion chambers can be simulated, the combustion chamber temperature fields of oleophylic coatings in different areas can be simulated, and experimental data is provided for later optimization of the piston combustion chamber.

A device to measure the movement of a shutter (2) of an injector (3) has a laser emitter (20) to generate light radiation, a receiver (23) associated with the laser emitter (20), a housing seat for the injector (3), which is arranged so as to allow the shutter (2) to move through the light radiation generated by the laser emitter (20), and a control unit (25), which is configured to generate a signal indicating the movement of the shutter (2) based on the quantity of light radiation generated by the laser emitter (20) and gathered by the receiver (23) itself.