314 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 discloses an instantaneous torque measuring system and method based on the front end of an engine, and relates to the technical field of engine testing and signal processing, and the system comprises a signal acquisition module, a noise analysis module, a signal processing module and a signal processing module, the noise frequency distribution and noise amplitude range extraction module is used for extracting noise frequency distribution and a noise amplitude range from the smoothed torque data and determining filtered torque data containing low-frequency drift noise and periodic interference signals, and the parameter extraction module is used for analyzing the noise frequency distribution and the periodic interference signals by adopting fast Fourier transform according to the filtered torque data so as to obtain the low-frequency drift noise and the periodic interference signals. Acquiring noise duration time and a noise source identifier, and determining an amplitude compensation coefficient and a frequency suppression parameter; according to the instantaneous torque measuring system and method based on the engine front end, accurate acquisition and noise suppression of engine torque signals are achieved, the accuracy and reliability of torque data are improved, and effective support is provided for engine performance monitoring and fault diagnosis.

The invention discloses a turbine for testing, an engine testing device and a method for determining a pneumatic instability boundary of a compression system, which can determine the pneumatic instability boundary of the compression system in a complete machine environment, do not cause extra burden to the turbine and compression system components, and do not need to modify a tester and surrounding equipment on a large scale. The turbine for testing is used for replacing an original turbine in a complete machine surge test of an engine, and the engine testing device is used for the complete machine surge test of the engine. Stator blades of the test turbine are arranged to be rotatable blades, so that the circulation sectional area of the test turbine is reduced by rotating the stator blades, and the compression system can enter a surge state.

The invention provides a liquid oxygen methane engine test bed composed of a multifunctional test system. The test bed comprises a gas path system, a liquid path system and a test station. Wherein the gas path system and the liquid path system are connected through a pipeline for gas supply, and the liquid path system is connected with the test run station and used for providing liquid fuel needed by testing for the test run station. The liquid path system comprises a low-pressure liquid path module and a high-pressure liquid path module. And the low-pressure liquid path module and the high-pressure liquid path module are respectively connected with a test run station. The test bed is composed of a set of gas path system, two sets of liquid path systems and three test stations. The two sets of liquid path systems jointly adopt one set of gas path system for gas supply, so that medium conveying can be carried out on the three test run stations according to requirements, the test run platform can meet the gas distribution requirements of engines of different models, meanwhile, the resource sharing of test equipment is improved, the total cost of equipment construction and maintenance is greatly reduced, and the working efficiency is improved. And the engine testing efficiency is improved.

The 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 belongs to the field of instrument detection, and provides an aircraft engine parameter indication detection system and method, and the method comprises the steps: generating a first sensor signal for an engine parameter indicator simulation test according to a first parameter; the first sensor signal is output to an engine parameter indicator in an analog signal mode so as to simulate the working state of an engine; collecting a first indication response signal generated after the engine parameter indicator receives the analog signal; calling a first pre-training artificial intelligence model, judging whether the working state of the engine parameter indicator is abnormal or not based on the first sensor signal and the first indication response signal, and outputting a corresponding detection result; calling a second pre-training artificial intelligence model, and combining the first sensor signal and the first indication response signal to generate a second parameter; judging whether to continue to execute the test process based on the second parameter; therefore, the testing precision and efficiency of the aircraft engine can be effectively improved.

The invention provides a method for installing a double-shaft compressor test piece on a compressor tester rack, and belongs to the field of aero-engine tests.The method comprises the steps that a simulation test piece is constructed, and an exhaust passage supporting seat is positioned and installed through the simulation test piece; mounting a biaxial compressor test piece with an independent supporting structure and the exhaust passage supporting seat; a first dial indicator and a second dial indicator are respectively arranged on the exhaust passage supporting seat and the independent supporting structure; at least two jacking devices are arranged at the symmetrical positions of the front side of the independent supporting structure, the biaxial compressor test piece is moved towards one side of the inner duct exhaust passage through the jacking devices, and in the moving process, the biaxial compressor test piece is controlled to be free of horizontal deflection according to a first dial indicator; when the biaxial compressor test piece is in butt joint with the positioning seam allowance of the inner duct exhaust passage, whether the biaxial compressor test piece is attached to the positioning seam allowance of the inner duct exhaust passage or not is judged according to the second dial indicator, and if yes, the biaxial compressor test piece is connected with the inner duct exhaust passage through a fastener.

The invention provides a biaxial compressor performance test and analysis method, which is used for realizing association between a uniaxial compressor test result and a complete machine test result, and belongs to the field of aero-engine test, and the method comprises the following steps: constructing a biaxial compressor performance test layout associating the uniaxial compressor test result with the complete machine test result, the test layout comprises the step of determining axial test positions and circumferential test positions of a total temperature instrument and a total pressure instrument in each test section in the double-shaft compressor; and a biaxial compressor test is carried out based on the constructed biaxial compressor performance speed measurement layout, a biaxial compressor test result is obtained, a uniaxial compressor test result and a complete machine test result are represented based on the biaxial compressor test result, and association of the test results is completed. The integrated analysis efficiency of test data of the single-shaft compressor, the double-shaft compressor and the whole machine is improved, and the application range of the test data is widened.

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 discloses an engine test bed intercooler temperature control system comprising an intercooler used for simulating work under actual working conditions; the constant-temperature heater is used for heating the cooling liquid to a preset temperature; the electronic water pump is used for driving cooling liquid to circulate and controllable in flow; the plate heat exchanger is used for heat exchange between the external circulation chilled water and the internal circulation cooling liquid; the expansion kettle is connected into the circulating system through a three-way valve to realize water replenishing and pressure balance; the bypass valve is arranged on the water pump bypass pipeline and used for adjusting the internal circulation flow and pressure, and the PID proportional valve is arranged on the external circulation chilled water pipeline and used for dynamically adjusting the external circulation chilled water flow; and the flow meter and the temperature and pressure sensor are used for monitoring the flow and pressure of the cooling liquid and the temperature of the outlet gas of the intercooler in real time.

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 utility model discloses a multi-model micro turbojet engine test bench, which relates to the technical field of engine testing and comprises a body, an oil tank is arranged on the inner bottom surface of the body and communicated with a plurality of connecting pipes, the tops of the connecting pipes extend out of the body, a turbojet engine is arranged on the top surface of the body and communicated with the connecting pipes through oil pipes, and the connecting pipes are communicated with the oil pipes. A control system is installed on the side face of the body and communicated with an external power source. The turbojet engine clamping device is simple in structure, convenient to use, capable of clamping turbojet engines of different models, wide in application range, reasonable in space application, convenient to operate and control, capable of achieving real-time observation and high in practicability.

The invention relates to the field of engine testing, and discloses an engine testing tray which comprises a chassis (50), a first positioning assembly, a second positioning assembly, a third positioning assembly and a fourth positioning assembly, the first positioning assembly, the second positioning assembly, the third positioning assembly and the fourth positioning assembly can be arranged on the chassis (50), and the first positioning assembly comprises a positioning piece and a fixing piece which can horizontally move to adapt to different types of cylinder bodies. The second positioning assembly and the third positioning assembly each comprise a fixing piece capable of horizontally moving to be matched with different types of cylinder bodies, and the fourth positioning assembly comprises a plurality of positioning tools matched with different types of cylinder bodies. Each positioning tool can be arranged on the base plate (50) and comprises a positioning piece and a fixing piece which are matched with different types of cylinder bodies. According to the technical scheme, the four positioning assemblies on the chassis can be matched with different cylinder bodies through relative movement and selective corresponding installation, the operation is simplified, the operation time is shortened, and the test efficiency is 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 utility model belongs to the technical field of engine testing, and particularly relates to an oil consumption device for testing a methanol fuel engine, which comprises a methanol storage container, a pump, a pressure regulating device, a heat exchanger and a flow meter, the input end of the pump connected with the pressure adjusting device in parallel is communicated with the interior of the methanol storage container through a pipeline, the output end of the pump connected with the pressure adjusting device in parallel is communicated with the liquid input end of the heat exchanger through a pipeline, and the liquid output end of the heat exchanger is communicated with the liquid input end of the flowmeter through a pipeline; according to the fuel consumption testing device for the methanol fuel engine, the mode that the pressure adjusting device, the heat exchanger and the flow meter are matched is adopted, the flow of output methanol is adjusted through the pressure adjusting device, and the temperature of the output methanol is controlled through the heat exchanger; the problem of how to manufacture the fuel consumption device for testing the methanol fuel engine with low cost is solved.

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 application provides an automatically adjustable multi-mode pressure distortion generation system, belonging to the field of aerospace engine testing. The system comprises a distortion generation device, a hydraulic system, and a control system. The distortion generation device comprises a sealed housing, a distortion plug plate, and a drive device. The sealed housing is provided with pipe connection flanges at the front and rear of the sealed housing for connecting to the intake passage of a compressor test piece. The distortion plug plate is disposed within the sealed housing, and the drive device is connected to the distortion plug plate. The control system connects the distortion generation device and the hydraulic system, and the hydraulic system is connected to the drive device. The control system controls the movement of the distortion plug plate within the sealed housing, thereby blocking the intake passage and changing the inlet blockage ratio of the compressor test piece. The present application can achieve a range of blockage ratios from 0% to 100%, thereby creating different intake distortion conditions, and has the ability to quickly open the distortion generation device under special conditions such as surge.

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 provides a high-speed camera and LED light source protection device for an aero-engine test, and relates to the field of aero-engine test equipment. According to the high-speed camera and LED light source protection device for the aero-engine test, the protection device is composed of a main camera cabin and two auxiliary lighting cabins and is provided with a base and a handle; a high-speed camera is placed in the main camera shooting cabin, and an LED lighting device is installed in the auxiliary lighting cabin; the three cabin bodies circulate with compressed air provided outside the test cabin through air circulation interfaces on the rear end surfaces; the engine test and protection device is used in a vacuum test cabin, the exterior of the protection device is in a vacuum state, the interior is atmospheric environment, air is forced to circulate, and temperature control can be performed. According to the high-speed camera and LED light source protection device for the aero-engine test, the problem that the high-speed camera and the LED light source cannot be used in a vacuum environment is successfully solved, and reliable recording and lighting guarantee is provided for the aero-engine test.

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.