230 results about "Engine testing" patented technology

The invention relates to the technical field of engine testing, and discloses a reliability test method and system for a small general engine, and the method comprises the steps: collecting an engine vibration signal through a superconducting quantum interferometer, and collecting a temperature distribution parameter through a quantum dot temperature sensor; performing combined testing of cold and hot shock, high-load operation and random working conditions, and synchronously monitoring dynamic response characteristic data; constructing a Weibull probability model, and determining key influence factors through a global sensitivity analysis method; acquiring a surface roughness parameter by adopting a field emission scanning electron microscope, obtaining a material component parameter through energy spectrum analysis, and establishing a parameter mapping relation; establishing a vibration and temperature early warning system, executing a graded sweep frequency excitation and abrasive particle acceleration test, and recording a parameter degradation process; and generating a three-dimensional parameter cloud picture, and outputting a reliability test report. According to the method, the reliability of the small general engine can be comprehensively and efficiently evaluated, and a scientific basis is provided for design, maintenance and improvement of the engine.

The invention relates to the field of aero-engine testing, in particular to an aero-engine rotating speed signal generator and a control method, and the system comprises the steps that a main control module receives a test demand input by a user, selects and determines the model, matching frequency, voltage and phase parameters of a tachometer sensor needing to be simulated based on the test demand, and transmits the parameters to a DSP processor; the DSP processor receives parameters issued by the main control module and generates an SPWM signal through a timer; the timer is configured to be in a circulation mode, and the period of the PWM signal is changed by changing the initial value of the timer; the inversion module converts the isolated SPWM waveform into a three-phase alternating current signal and outputs the three-phase alternating current signal; and the detection module measures data of the three-phase alternating current signal output by the inversion module in real time and feeds back the data to the main control module to form closed-loop control. Test errors caused by performance errors of the sensor are avoided, and the actual performance of the tachometer indicator can be evaluated more accurately.

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 belongs to the field of aero-engine test and fault diagnosis, relates to an engine rotating part fault positioning technology, and provides a rotating part fault feature recognition method and system in a tachometer-free scene, and the method comprises the steps: obtaining a vibration signal and a theoretical fault feature order of a rotating part; obtaining an instantaneous rotating frequency signal of the rotating part through the constructed non-convex linear transformation regular term sparse representation model; carrying out iterative solution through the constructed sparse representation model to obtain a fault characteristic signal of the rotating part; obtaining an order envelope spectrum according to the instantaneous frequency conversion signal and the fault characteristic signal; and performing health assessment and fault identification on the rotating part according to the order envelope spectrum and the theoretical fault feature order. The method can solve the problem that the variable-speed fault of the rotating shaft part of the aero-engine cannot be recognized in a non-rotating-speed scene. Through the implementation of the method, the fault of the rotating shaft part of the aero-engine is effectively identified, and technical support is provided for troubleshooting in an aero-engine test.

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.

The invention discloses a wide-range high-precision steady-state and dynamic-state integrated rotating speed measuring system, and belongs to the technical field of rotating machinery metering. The system comprises a rotating speed measuring node (including an anti-interference sensor and an MCU microprocessor), an upper computer (including a time sequence coordination module and a data processing module) and a data output device, and adopts a continuous double-counting synchronous operation method to realize synchronous triggering of pulses and a time counter and period value inheritance. And a 40MHz temperature compensation crystal oscillator is matched to control the timing error within + / -1 clock period. The time sequence coordination module covers the ultra-wide range of 0.01-400000 r / min through a self-adaptive sampling mechanism (T = 0.01-25 s, K = 1-255), and the anti-interference sensor controls edge jitter within 2 microseconds. The dynamic sampling time of the system is less than or equal to 10ms, the steady-state relative error is less than or equal to 5 * 10 <-6 > (k = 2), the dynamic error is less than or equal to 1.5 * 10 <-4 >, the method is suitable for industrial automation, aero-engine testing and other scenes, the technical bottleneck is broken through, the rotating speed measurement precision and the dynamic response capability are improved, and an effective scheme is provided for precise monitoring of rotating machinery.

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 belongs to the field of aero-engine tests, and particularly relates to an aero-engine turbine rear baffle optical scanning measurement tool and a use method. A rotary table fixing plate is arranged on an optical scanning measurement platform; the supporting seat comprises an upper supporting seat and a lower supporting seat, and the upper supporting seat or the lower supporting seat is fixedly mounted on the rotary table fixing plate; the middle supporting plate is circular and is located between the upper supporting seat and the lower supporting seat, and the upper supporting seat, the middle supporting plate and the lower supporting seat are fixedly connected through bolts; a turbine rear baffle to be tested sleeves the outer side of the middle support plate; the multiple clamping rods are evenly arranged in the circumferential direction of the middle supporting plate, each clamping rod comprises a positioning part, an upper clamping part and a lower clamping part, the positioning parts are fixedly connected with the middle supporting plate, the upper clamping parts are fixedly connected with the upper surface of the turbine rear baffle to be detected through upper set screws, and the lower clamping parts are fixedly connected with the lower surface of the turbine rear baffle to be detected through lower set screws. And the lower clamping part is fixedly connected with the lower surface of the turbine rear baffle to be tested through a lower set screw. According to the invention, measurement errors can be reduced, and the measurement efficiency can be improved.

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 present invention belongs to the technical field of aircraft engine testing, and particularly relates to a ground test system and method for aircraft engine hybrid power; the system comprises a turbine generator and a power supply module, the turbine generator is connected to a mode selection unit via a DC bus; the mode selection unit is respectively connected to a concentrated load module, a zero load module and a distributed load module via a DC bus; the power supply module is connected to the distributed load module via a DC bus; the mode selection unit is signal-connected to an integrated monitoring system and a vehicle platform measurement and control system; the integrated monitoring system is signal-connected to the distributed load module and the concentrated load module; the vehicle platform measurement and control system is signal-connected to the distributed load module, the power supply module and the turbine generator; the vehicle platform measurement and control system is connected to the integrated monitoring system; the mode selection unit is used to select a test mode; rapid switching of test items is achieved, and no human involvement is required during the entire process, thereby avoiding the risks caused by test switching and improving the efficiency of the test.

The present invention belongs to the field of engine testing technology and discloses an engine test bench measurement and control system alarm method, comprising determining whether the engine is in a preset operating condition. If the engine is in the preset operating condition, test data validity monitoring is performed; test data validity monitoring includes: urea injection amount data verification; urea injection amount data verification includes: determining the actual ammonia nitrogen ratio based on the urea injection amount data and ECU SCR upstream nitrogen oxide emission measurement data; if the actual ammonia nitrogen ratio is not within a preset range and the duration is greater than a first preset time, the urea injection amount data is judged to be abnormal and a urea injection amount data abnormality alarm is issued. The engine test bench measurement and control system alarm method of the present invention determines whether there is a problem with the urea injection amount data based on the actual ammonia nitrogen ratio, and when it is determined that there is a problem with the urea injection amount data, an alarm is issued to alert the tester, allowing the tester to promptly troubleshoot the problem and choose to continue or stop the test.

This application discloses a turbine outer ring connection structure, a thermal matching test apparatus, and a test method thereof, belonging to the field of aerospace engine testing technology. The turbine outer ring connection structure includes a turbine outer ring assembly: the turbine outer ring assembly includes the turbine outer ring and a metal casing connection assembly, the metal casing connection assembly includes a metal casing and a connector, a first connection hole is defined in the outer wall of the metal casing, and the connector is used to securely connect the turbine outer ring and the metal casing; the outer wall of the metal casing is defined by a plurality of displacement measurement holes spaced apart, and the displacement measurement holes are used to cooperate with preset markings on the turbine outer ring to observe and measure the displacement deformation of the turbine outer ring relative to the metal casing. The turbine outer ring is a monolithic CMC turbine outer ring, and the turbine outer ring connection structure is a full-ring assembly structure that enables modular installation. The thermal matching test apparatus can perform thermal fatigue testing of the CMC outer ring with alternating heating and cooling load cycles.

The present invention discloses a self-detection method, system, device and storage medium for an over-speed protection system. The method adopts the power turbine speed as a trigger condition and can respectively perform self-detection on the hardware circuit and control switch of the over-speed logic processing unit of the over-speed protection system, so as to facilitate rapid fault location when the over-speed protection function fails. Moreover, the self-detection process of the hardware circuit and the control switch of the over-speed logic processing unit will not cause actual fuel cut-off, thereby eliminating the need for special development of engine start-up detection programs. Moreover, dynamic detection can be performed in an actual installation and use environment without the need for special ground detection equipment. Therefore, the over-speed protection function can be self-detected during normal engine testing and operation, ensuring that the over-speed protection function is intact during engine operation.

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.

The invention relates to the technical field of engines, in particular to a device for oil recovery treatment after engine testing. The recovery container comprises a box body, a magnetic filter plate and a flow baffle; the magnetic filter plate is mounted in the box body and is parallel to the bottom surface of the box body, and a set distance is formed between the magnetic filter plate and the bottom surface of the box body; the flow baffle comprises an upper-layer plate and a lower-layer plate, the upper-layer plate and the lower-layer plate are both perpendicular to the bottom surface of the box body, a set distance is formed between the upper-layer plate and the lower-layer plate, the lower edge of the lower-layer plate is attached to the bottom surface of the box body, the lower edge of the upper-layer plate is attached to the top surface of the magnetic filter plate, and the lower edge of the upper-layer plate is lower than the upper edge of the lower-layer plate. Through an optimized multi-stage filtering structure and reasonable flow field control, efficient purification of recycled diesel oil is achieved, it is ensured that the recycled diesel oil reaches the secondary use standard, and therefore the engine failure risk is reduced, the test run cost is saved, and meanwhile diesel oil waste and environmental pollution are avoided.

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.

The utility model discloses an engine plugging mechanism and a leakage test bench, and belongs to the technical field of engine testing. The engine plugging mechanism comprises an adjusting mechanism and a plugging assembly installed on one side of the adjusting mechanism. The adjusting mechanism is provided with a bottom plate, one side of the bottom plate is connected with a fixing plate, and the side, away from the bottom plate, of the fixing plate is connected with a push plate. The plugging assembly is provided with a plugging head and a sealing piece, the sealing piece is installed on one side of the plugging head, a shaft is installed on the side, away from the sealing piece, of the plugging head, and the shaft is in conical surface fit with the push plate. The engine plugging mechanism is simple in structure, stable and reliable in operation, low in cost, high in positioning precision, convenient to maintain in the later period and capable of being applied to any equipment needing automatic plugging, and a robot executing mechanism or a servo system is not needed. The shaft is matched with the conical surface of the push plate, the position of the plugging head can be fixed, when the conical surface of the shaft is separated from the conical hole in the push plate, the plugging head can be attached to the engine plugging opening in a self-adaptive mode within a certain range, and stable sealing is achieved.

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.

This invention discloses a propeller flow rectification device and design method for testing high-power turboprop engines. The propeller flow rectification device includes a base, a mounting frame mounted on the base, a rectification ring for guiding and rectifying the propeller flow, and an adjustable tie rod for aligning the rectification ring. The rectification ring includes a rectification panel, a structural reinforcement on the outer wall of the rectification panel, a tie rod connecting seat on the structural reinforcement, and an outer panel on the structural reinforcement. The two ends of the adjustable tie rod are connected to the tie rod connecting seat and the mounting frame, respectively. Its ingenious structure ensures the overall flow field stability within the square test chamber. The alignment of the rectification ring can be achieved by adjusting the support length of the adjustable tie rod, eliminating the need to reinstall the engine and reducing the workload of alignment. By replacing the rectification ring, it can accommodate blades of different lengths, shortening the test cycle and improving test efficiency.

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 provides a device for providing a reference end for stabilizing atmospheric pressure, and belongs to the technical field of aero-engine test, the device comprises a pressure stabilizing box body, the pressure stabilizing box body comprises a top plate, a middle-layer pressure baffle mounted on the top plate, a bottom plate, an inner-layer pressure baffle and an outer-layer pressure baffle, and the inner-layer pressure baffle and the outer-layer pressure baffle are mounted on the bottom plate; a mounting interval is formed between the inner-layer pressure baffle and the outer-layer pressure baffle, the middle-layer pressure baffle is inserted into the mounting interval, a gap is formed between the middle-layer pressure baffle and the bottom plate, and the middle-layer pressure module is fixedly connected with the inner-layer pressure baffle or the outer-layer pressure baffle through a mounting block; the bracket is arranged on the lower side of the pressure stabilizing box body; the plurality of voltage stabilizing output units are arranged in the voltage stabilizing box body; the constant-humidity constant-temperature box is used for accommodating the pressure measuring module; and the output pipeline is connected with the stable pressure output unit and the constant-humidity constant-temperature box, and a stable pressure measurement reference value is provided for the test system through a pressure measurement module in the constant-humidity constant-temperature box.

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.

The application belongs to the technical field of engine testing, and discloses a public engine dynamometer test bench, which comprises a base, a protective cover rotatably arranged on the base, a dynamometer fixedly arranged on the base, a coupling rotatably arranged on the base, a supporting assembly slidably arranged on the base, an engine detachably and fixedly arranged above the supporting assembly, the coupling being connected with an output shaft of the engine and an input end of the dynamometer, an adjusting assembly fixedly arranged on the base, the adjusting assembly being in transmission connection with the supporting assembly, and a monitoring mechanism arranged on the base, the monitoring mechanism being used for monitoring a dynamometer test process of the engine and discovering abnormal conditions in time. The application can be adapted to engines with different displacements, can quickly complete coaxial butt joint of the engine and the coupling, and can be adapted to mounting hole positions of different models of engines through the multidirectional sliding of sliding blocks and positioning plates of the supporting assembly, the combination of electromagnets and hydraulic cylinders, comprehensive analysis of multiple source data and accurate discovery of abnormal conditions and prediction of potential risks.