134 results about "Engine testing" patented technology

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 invention relates to the technical field of mobile terminal testing, and discloses a 3D engine testing method and system, electronic equipment and a storage medium. A mobile terminal obtains a target test case set and a corresponding rendering test scene configuration file, loads the rendering test scene configuration file corresponding to a current test case and executes rendering operation; the verification frame is sent to the cloud, rendering target texture test diagrams corresponding to all rendering pipelines in the verification frame are obtained, an obtained rendering target texture test diagram set and a current test case identifier are sent to the cloud, the cloud compares the reference diagram with the test diagrams for the same rendering pipeline, the abnormity judgment result of each rendering pipeline is determined, and the abnormity judgment result is sent to the cloud. Compared with the prior art, the exported texture test chart is compared with the theoretical expected value of the rendering pipeline instead of depending on visual subjective judgment, the test result can be quantified, the similar fuzzy conclusion in visual sense is avoided, and the objectivity and reproducibility of the test are improved.

This invention relates to an online testing method for engine assembly status, belonging to the field of engine testing technology. Addressing the problems of low efficiency and poor consistency in existing technologies, such as the difficulty in simultaneously assessing spatial installation and appearance using single-image testing methods, and the tendency to miss measurements in complex structural areas, this invention proposes acquiring color and depth images of the engine under test. Based on the component characteristics, it selects a camera mode from color-only testing, depth-only testing, and collaborative testing. Multi-view image acquisition is performed according to a preset testing scheme, and the results of each test item are obtained through a preset testing algorithm. Finally, the results are fused and judged to generate an overall result. This invention improves the targeting, accuracy, and coverage of the inspection, and is applicable to the field of online testing of engine assembly quality.

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 relates to the technical field of data analysis, in particular to an engine universal characteristic diagram drawing and comprehensive performance analysis method, which comprises the following steps: collecting and reading engine test data in Excel and CSV formats, cleaning the data through rotating speed standardization processing and a Z-score abnormal value removal algorithm, inputting or selecting engine basic parameters and environmental parameters, and analyzing the comprehensive performance of the engine. Performing graphic drawing parameter configuration, rendering a graphic according to configuration parameters, superposing an auxiliary curve and a key area mark, starting a mouse real-time coordinate display and navigation interaction function, extracting core data to calculate a dynamic performance index and an economic performance index, quantitatively dividing a working area and calculating a comprehensive performance index; according to the method, a structured analysis report is automatically generated, export of graphs and reports is supported, and the problems that the multi-fuel, efficient and intelligent development of the engine technology is achieved, and a traditional tool which is large in manual intervention, scattered in process and single in function cannot meet the refined and efficient performance analysis requirement are solved.

The application provides a PEMS testing method and system for a sweeper engine, the method comprising: obtaining an engine model corresponding to a target sweeper, and building an engine test bench according to the engine model, and installing and debugging a PEMS device on the engine test bench; obtaining all operation modes related to the target sweeper, and testing the engine test bench according to a test condition corresponding to each operation mode; monitoring rotational speed data and emission data of the engine test bench in each test process, and evaluating a PEMS emission result of the sweeper according to the rotational speed data and the emission data. The PEMS testing method for the sweeper engine can greatly shorten a non-road emission test time of the sweeper by simulating actual road operation conditions of the sweeper.

The invention provides an engine in-cylinder brake test bench and a test method, relates to the technical field of engine test, and aims to solve the problem that an existing test bench cannot reproduce valve lift loss under a real high-pressure load. In the process that a power driving source drives a cam shaft to force a brake valve to open, the loading mechanism continuously applies a reverse mechanical acting force to the valve, so that a huge blocking load generated by high-pressure gas in a cylinder to the valve in a compression stroke of a real engine is approximately simulated physically; the valve and a transmission mechanism of the valve are passively in a real high-load stress state, so that lift reduction caused by elastic deformation or hydraulic compression of parts is simulated, a high-load operating environment in a cylinder is effectively restored, and real dynamic data including actual lift loss are measured.

The utility model relates to the technical field of engine testing, in particular to a pressure measuring device for an engine test, which comprises a joint and a pressure measuring sensor, the middle of the joint is provided with an up-down through mounting test hole, and the outer surface of the upper half part of the joint is provided with an engine connecting external thread. According to the pressure measuring device, pressure measuring oil cannot be replaced every time pressure measuring is carried out, the pressure measuring device can rapidly recover to the state before a test through the reset spring, the test can be continuously and rapidly carried out, and the test efficiency is improved; moreover, in the assembling process of the pressure measuring device, the gas of the test oil section arranged in the installation test hole can be exhausted, the gas content in the installation test hole is effectively reduced, the pressure is transmitted by the pressure measuring oil in the pressure measuring process, and the pressure measuring accuracy is improved.

The invention discloses an aero-engine blade non-contact vibration measurement system and method, and belongs to the technical field of engine testing. The system comprises an optical fiber sensor, a rotating speed reference signal generation unit, a sensor clamp and a signal processing unit, the optical fiber sensor is arranged at a specific circumferential position of an engine case; the rotating speed reference signal generation unit is matched with the corresponding optical fiber sensor through an optical mark on the rotating shaft to obtain a rotating speed reference pulse signal of each rotation; the sensor clamp fixes and positions the optical fiber sensor; the signal processing unit processes the collected signals to obtain blade vibration parameters. The measuring method comprises the steps of setting optical marks, arranging optical fiber sensors, collecting signals and analyzing data, and completing blade vibration characteristic detection. The non-contact design is adopted, the problem of obtaining high-precision rotating speed reference signals in a complex rotating disc cavity is solved, the precision and stability of blade vibration measurement are improved, and reliable guarantee is provided for safe operation of an engine.

This invention relates to a maintenance and testing device for an aircraft air conditioning system. An engine testing module emits sound waves, which are detected by a piping testing module. The collected signals are analyzed and processed in the main controller to obtain a diagnostic result regarding whether the air conditioning system is damaged. It can accurately determine the physical health status of the air conditioning system and accurately identify any physical damage, with high accuracy and a simple testing method. Simultaneously, it detects temperature parameters at the engine, piping, and cockpit to determine the air conditioning system's operational health index. By detecting the air composition in the cockpit during air conditioning operation, it can detect the cockpit safety index. It can effectively analyze the air conditioning's operating efficiency and the cockpit safety index, ensuring that aircraft that pass the inspection will not pose a danger during missions.

The utility model provides a steering engine testing tool, comprising a base plate, a torsion arm, a steering engine installation plate, a first tension sensor and a second tension sensor, the steering engine installation plate is installed on the base plate, the torsion arm is movably clamped between the base plate and the steering engine installation plate, a first end of the first tension sensor is fixedly installed on the base plate, and a second end of the second tension sensor is fixedly installed on the base plate. The second end of the first tension sensor is connected with one end of the torsion arm, the first end of the second tension sensor is mounted on the bottom plate, the second end of the second tension sensor is connected with the other end of the torsion arm, the steering engine is mounted on the steering engine mounting plate, and a rotating shaft of the steering engine penetrates through the steering engine mounting plate to be connected with the torsion arm; the position of the steering engine does not need to be calibrated and debugged, the overall structure is simple, and disassembly, assembly and use are convenient.

A multifunctional crushing host test device, including a function valve table one suitable for the function of a jaw crusher host, a function valve table two suitable for the function of a cone crusher host and a function valve table three for adjusting the position of the motor, the function valve table one and the function valve table three are used in combination, the jaw crusher model can be verified; the function valve table two and the function valve table three are used in combination, the cone crusher can be tested on the bench, and the function is verified; the multifunctional crushing host test device of the application is integrated with different types of host drive and control system, integrates the hydraulic control device, has small floor area and is convenient to maintain; the function reliability of product design can be quickly verified, and early failures of internal mechanical transmission gears and other components of the host can be eliminated, so that the production time and manufacturing cost are greatly shortened.

The invention discloses an analysis method for damage residues of an engine blade. The method comprises the following steps: spraying and cleaning the injured part by using anhydrous alcohol; a special marking pen containing electrolytic copper powder is adopted for marking; adhering the extracted residues and the marks by using a carbon conductive adhesive tape; sealing and storing the extracted sample in a self-sealing bag; and finally, back scattering electron imaging and energy spectrum analysis are carried out through a scanning electron microscope. The method solves the technical problems of long period caused by leaf decomposition, secondary pollution caused by cutting sampling, low contrast between residues and a matrix, difficulty in distinguishing and the like in the traditional analysis method. Through a unique marking system and an extraction process, in-situ rapid sampling can be carried out after engine test run, the residue identification efficiency and the component analysis accuracy are remarkably improved, and a reliable technical means is provided for blade damage fault analysis.

This application provides a method for determining the bird-swallowing capability of an aero-engine, belonging to the field of aero-engine testing. The method includes: evaluating the bird strike resistance of blades using strength simulation, correcting it with component test results to obtain the blade's bird strike resistance characteristics; evaluating the aerodynamic impact of damaged blades through aerodynamic modeling, correcting it with blade-mounted testing to obtain the aerodynamic impact characteristics of damaged blades on the engine; determining the quantitative relationship between bird-swallowing parameters and blade damage based on test and simulation results; determining the strength and aerodynamic boundaries of the aero-engine's bird-swallowing capability; determining the engine's bird-swallowing capability based on the engine's bird-swallowing strength and aerodynamic boundaries, combined with bird-swallowing standards; and improving the bird-swallowing capability of an engine with determined bird-swallowing capability through targeted design improvements.

The invention provides a high-power engine high-temperature exhaust leading-out device which comprises a main exhaust pipe connected with an outer wall and a butt joint pipe connected with an engine to be detected and the main exhaust pipe, and the main exhaust pipe and the butt joint pipe are communicated with each other and form an exhaust pipeline for leading out exhaust gas. The butt joint pipe comprises at least two telescopic hoses, the bottom ends of the telescopic hoses are connected with a smoke exhaust pipe connector of the engine to be detected, and the tops of the telescopic hoses are connected with a main exhaust pipe. The main exhaust pipe comprises a first exhaust pipe body, a second exhaust pipe body, a third exhaust pipe body and an exhaust elbow, and the first exhaust pipe body, the second exhaust pipe body, the third exhaust pipe body and the exhaust elbow are sequentially arranged in the smoke circulation sequence and communicate with one another. Therefore, a smoke exhaust system actively matched with different engine test models is formed.

The invention relates to the technical field of aero-engine tests, and discloses a turbine test device, which comprises a mounting base on which a hydraulic power measuring device and a transmission shaft assembly are suspended, the transmission shaft assembly comprises a pair of shaft bodies, the pair of shaft bodies are in transmission connection through a torque flange, the pair of shaft bodies are coaxially arranged, and the pair of shaft bodies are connected through a transmission shaft; wherein one shaft body is suitable for being connected with a turbine output shaft of a turbine test piece in a matched mode, and the other shaft body is connected with a power measuring input shaft of a hydraulic power measuring device. The pair of shaft bodies of the transmission shaft assembly are directly connected, and the torque flange is adopted for torque transmission, so that clearance fit in the transmission link can be reduced, and the operation stability of a shaft system at a high rotating speed is improved; and meanwhile, the torque flange integrated at the joint of the pair of shaft bodies is used for directly measuring the torque, so that a torque measuring chain can be shortened, accumulated errors are reduced, and the measuring precision is improved.

This utility model relates to a mobile testing system for ground testing of a turboshaft engine, belonging to the field of turboshaft engine technology, and solves the problem of the lack of mobility in existing whole-engine testing technologies. This utility model includes an experimental platform unit, a measurement and control unit, and a water circulation unit; the experimental platform unit, measurement and control unit, and water circulation unit are mounted on a mobile device; the experimental platform unit includes an engine testing platform and a dynamometer; the measurement and control unit includes a measurement and control device and a data acquisition device; the water circulation unit includes a circulating water cooling device, a cold water tank, and a hot water tank. This utility model enables ground testing and rapid transfer of a turboshaft engine.

This invention relates to the field of aero-engine technology, specifically to a device and method for providing hot and cold airflow conditions for engine testing. The device includes a support, a fan inlet fixedly mounted on and connected to the fan, a gas release network detachably installed within the fan inlet, and multiple gas release ports connected to an external gas source, and a monitoring and control component connected to the gas release network and the fan motor, and fixedly connected to the fan. This invention, a device and method for providing hot and cold airflow conditions for engine testing, has a novel structure and can achieve automatic temperature control during flight missions at different altitudes, simulating the real environment of the engine during service, and enabling structural performance evaluation and life assessment.

This disclosure provides a testing method for engine seat rings and guide tubes, belonging to the field of engine testing. The method includes: controlling the engine to continuously operate for multiple cycles, each cycle sequentially including a first idle condition, an acceleration condition, a stable condition, a deceleration condition, and a second idle condition. Under the first and second idle conditions, the engine speed is a first speed; under the stable condition, the engine speed is a second speed, which is greater than the first speed; under the acceleration condition, the engine speed linearly increases from the first speed to the second speed; under the deceleration condition, the engine speed linearly decreases from the second speed to the first speed. After the engine stops running, the wear amount of the seat ring is used to determine whether the seat ring is qualified, and the wear amount of the guide tube is used to determine whether the guide tube is qualified. This method can fully verify the seat ring and guide tubes to prevent them from failing during engine operation.

This invention relates to the field of engine testing technology. It discloses a dual-modal integrated engine performance testing system, comprising a hardware testing module, a data acquisition and preprocessing module, a central control and analysis module, a result display and storage module, a predictive analysis submodule, and a preprocessing execution submodule. The invention also discloses a dual-modal integrated engine performance testing method, comprising the following steps: Step 1: System initialization; Step 2: Engine start-up and modal identification; Step 3: Parameter acquisition and preprocessing; Step 4: Data processing, performance evaluation, and predictive analysis; Step 5: Preprocessing decision-making and execution; Step 6: Result display and storage; Step 7: Real-time control. Through the above settings, potential faults can be avoided in advance, reducing the probability of fault occurrence and improving the stability and safety of engine operation.

The invention relates to the technical field of engine knock detection and control, in particular to an engine knock energy prediction method and device, a vehicle, a storage medium and a product, and the method comprises the steps: obtaining an operation data set of an engine test, including operation data of an engine in a plurality of acting stages and real knock energy corresponding to each acting stage; a training data set and a verification set are generated according to the operation data set, each of the training data set and the verification set comprises a data sample and a real label, the data samples comprise operation data of the engine in the current acting stage, and the real labels are real knocking energy of the data samples; and training a pre-constructed knock energy prediction model by using the training data set, verifying the knock energy prediction model by using the verification set, and predicting the knock prediction energy of the engine by using the currently collected operation data and the knock energy prediction model. Therefore, the problem that the detonation energy prediction precision is poor due to the fact that differential operation working conditions are generated by the hybrid power engine due to power coupling in the related technology is solved.

The invention provides a design method of a double-row mixing type aero-engine steady-state temperature distortion generating device, and belongs to the technical field of aero-engine testing systems.The design method specifically comprises the steps that 1, the design requirement of the temperature distortion generating device is confirmed; 2, a secondary flow high-temperature gas flow distribution scheme is determined; 3, designing the size of a secondary flow high-temperature gas pipeline; and step 4, performing performance verification and structure optimization. On the basis of the high-temperature airflow jet mixing principle, secondary flow high-temperature gas is injected into an inner flow channel of the aero-engine by means of double-row multi-ring-cavity gas injection and the like, introduction of large-flow high-temperature airflow is achieved, the characteristic section temperature distortion index simulation range of the aero-engine is widened, and the simulation precision of the aero-engine is improved. The temperature distortion generator designed through the method can meet the requirement for the steady-state temperature distortion test of the aero-engine under the large temperature distortion index condition, meanwhile, the device is simple in structure, a large amount of machining cost can be saved, and the preparation period of the temperature distortion device is shortened.

The utility model discloses a thrust loading device for thrust calibration of a turbojet engine test bench, which belongs to the technical field of aero-engine testing and comprises a loading mechanism, a plugging cover and a control system. Wherein the loading mechanism is used for transmitting and adjusting thrust; the plugging cover is connected with the tail end of the loading mechanism through a bolt; the control system comprises a motor, a driver and a controller; wherein a base of the motor is connected with the outer side of the plugging cover through a bolt, and a lead screw in the motor is in threaded connection with a threaded through hole formed in the center of the plugging cover; the controller is electrically connected with the driver and is used for generating a pulse signal; the driver is electrically connected with the motor through a cable, and is used for receiving the pulse signal generated by the controller and driving the motor to operate; the design can solve the problems that in the prior art, a system is complex to install and debug, hydraulic oil may leak, pressure fluctuation and reduction are caused, and stability is poor.

The application relates to the technical field of aero-engine testing, and discloses an air inlet dustproof mesh cover assembly and a high-altitude simulation test bench. The air inlet dustproof mesh cover assembly comprises: an air inlet dustproof mesh cover which comprises a support framework and a mesh cover main body covering and fixed outside the support framework, the support framework is internally provided with a hollow air inlet channel, and the support framework is provided with a blowing hole for blowing air to the mesh cover main body; and a pneumatic defrosting device which is suitable for continuously feeding air into the air inlet channel and blowing air to the mesh cover main body through the blowing hole. Through the pneumatic defrosting device, the ice and frost on the mesh cover main body can be removed in real time, the screen mesh of the mesh cover main body can be dredged, and the phenomenon of frost blocking the mesh holes can be reduced or avoided, manual defrosting is not needed, the test is not interrupted, the icing test efficiency is improved, the energy consumption is reduced, the test continuity is ensured, the problems of frost blocking the mesh holes of the existing air inlet dustproof mesh cover and manual defrosting needing to pause the test are effectively solved.

The invention relates to the technical field of aero-engine detection, in particular to a blade positioning detection system and method for an aero-engine, and the system carries out the positioning detection of a blade for the aero-engine, especially a fan blade, through a detection mechanism of a plurality of line laser sensor groups, cooperating with an inner rotating mechanism and an outer surrounding mechanism. Wherein the inner rotating mechanism not only can provide necessary blade self-rotation during detection, but also can correct the deviation of the center line of the fan blade, and the outer surrounding mechanism is used for adjusting the positions of a plurality of line laser sensor groups aiming at different batches of fan blades with different twist degrees, so as to cover a blade edge fillet area of the fan blade at a complementary angle; light path offset and positioning drift caused by a traditional moving sensor are avoided, the structure of sensor fixing and blade rotating is adopted, the space complementarity of a multi-line laser sensor is reserved, the coverage range of a single-line laser sensor on a twisted blade is expanded through rotating, and stable geometric conditions are provided for continuous detection of a high-curvature area.

A privilege-free chaos engine testing environment is provided. A reverse proxy provided on a communication line between a first resource and a plurality of second resources intercepts communications from the first source intended for the plurality of second resources. Mirror communications (URLs) of the first communication and generated. A chaos scenario is selectively injected into the mirror communication according to a chaos policy to generate a response communication. The response communication is transmitted to the first.

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 an engine coolant consumption testing device and a testing method thereof, and belongs to the technical field of engine testing. The device comprises a detection machine table, a feedback support is arranged at the top of one end of the detection machine table, an expansion detection ball and a water supplementing detection ball are arranged on a sliding rod on the feedback support, a pressure relief pipe column is arranged at the top of the expansion detection ball, and a pressure cover sleeves the top of the pressure relief pipe column; according to the invention, real-time visual monitoring and accurate quantitative calculation of the consumption of the engine coolant are realized, abnormal consumption of the coolant can be rapidly discriminated to trigger timely maintenance, and direct data support can be provided for scientific formulation of a maintenance and supplement period of the coolant; ineffective loss caused by gasification and pressure fluctuation of the cooling liquid in the testing process is greatly reduced, the accuracy of consumption testing is improved, and meanwhile the testing result can directly provide a key reference basis for capacity optimization design of upper and lower scribed lines of the auxiliary water tank of the engine.

The invention belongs to the field of aero-engine testing, and particularly relates to an aero-engine tail jet flow core area geometric characteristic calculation method. The method comprises the following steps: step 1, acquiring aero-engine tail jet flow spatial distribution data; 2, performing homogenization treatment on the aero-engine tail jet flow in the same state at different moments to obtain an aero-engine tail jet flow uniform thermal image; 3, determining the boundary temperature of a tail jet flow core area according to the uniform thermal image of the tail jet flow of the aero-engine; 4, determining a tail jet flow core area according to the boundary temperature of the tail jet flow core area, and counting the total number of pixel points in the tail jet flow core area; 5, calculating the length and the area of the actual target position corresponding to a single pixel point; and step 6, calculating the total length and the total area of the tail jet flow core area according to the total number of the pixel points in the tail jet flow core area and the length and the area of the actual target position corresponding to the single pixel point.

The application provides a method and system for verifying compatibility of an engine and an air inlet of an aircraft with ground vortex air intake, and is applied to the technical field of engine testing and verification. The method comprises: obtaining first engine state data of the engine affected by the ground vortex air intake under different values of each influencing factor in multiple influencing factors; taking the value corresponding to the first engine state data satisfying the preset condition as a variable; combining the variables corresponding to each of the multiple influencing factors to obtain multiple sets of test conditions; obtaining second engine state data of the engine affected by the ground vortex air intake under each set of test conditions; collecting ground vortex images under each set of test conditions and analyzing vortex physical characteristics of each of the multiple ground vortex images; and verifying the compatibility of the engine and the air inlet under the ground vortex working condition according to the second engine state data and the vortex physical characteristics corresponding to each set of test conditions. The method improves the accuracy and comprehensiveness of the compatibility verification of the engine and the air inlet.