3057results about "Engine testing" patented technology

The application provides a fault prediction method and apparatus, an electronic device and a storage medium. The method comprises: obtaining a vibration signal collected by a sensor installed on a target component of a target device, and cleaning and segmenting the vibration signal to obtain a target vibration signal; inputting the target vibration signal into a target anomaly judgment model to obtain an output result, and according to the output result, determining whether the target vibration signal is abnormal to obtain an anomaly judgment result; when the abnormal judgment result shows that the target vibration signal is abnormal, inputting the target vibration signal into a target fault prediction model to obtain a fault prediction result, wherein the target fault prediction model is obtained by combining an encoder of the target anomaly judgment model and a newly added full connection layer. The application solves the problem in the prior art that a faulty device cannot be timely maintained because the fault can only be monitored when the device fault is quite obvious.

The invention relates to the field of power equipment data processing, in particular to a steam turbine vibration fault diagnosis system fused with deep learning. Comprising a dynamic knowledge base construction module, a working condition adaptive data synchronization module, a knowledge-guided heterogeneous feature fusion module, a dynamic structure neural network module, an online self-optimization weight distribution module and a knowledge-enhanced coupling fault reasoning module. The dynamic knowledge base construction module updates the multi-modal knowledge graph through an incremental knowledge distillation mechanism, and generates an interpolation strategy template and a frequency band sensitivity matrix; the working condition self-adaptive data synchronization module dynamically calls an interpolation algorithm based on a rotating speed fluctuation mode to realize time sequence alignment optimization of multi-source sensor data; the system effectively solves the problems of time scale asynchronism and feature heterogeneity in multi-source heterogeneous data fusion through a knowledge-driven and data-driven closed-loop interaction mechanism, and realizes accurate diagnosis and early warning of steam turbine vibration faults under complex working conditions.

The invention provides a reinforced diesel engine friction pair on-line wear detection device and a wear detection method. The reinforced diesel engine friction pair on-line wear detection device comprises a wear calculation terminal, an NI-PXIe8115 acquisition instrument, a sampling detection circulating oil path, a cylinder pressure sensor, a rotating speed sensor, a vibration sensor, an acoustic emission sensor, a six-in-one lubricating oil physical and chemical sensor, an abrasive particle sensor, an abrasive particle visual sensor and a CAN / USB / RS485 communication interface. The method has the beneficial effects that the load of a friction pair of the strengthened diesel engine is large, the process from symptoms to failure is extremely short, and serious fault events are difficult to control, the device can quickly warn an abnormal state after being implemented, gives a corresponding action instruction to a user, and provides a reliable identification means for strengthening research, development and operation safety of the diesel engine.

The invention relates to the technical field of mechanical vibration testing, in particular to a method for testing dynamic rigidity and damping characteristics of an engine support, which comprises the following steps of: 1, simulating a boundary; step 2, double-source excitation loading is carried out; step 3, dynamic response acquisition: arranging vibration measurement points in the main shaft direction of the rigidity of the support to acquire acceleration signals in three directions, synchronously acquiring excitation force signals, and recording all the signals at a set sampling rate after anti-aliasing filtering; 4, constructing a frequency response matrix: performing time-frequency transformation on the exciting force signal and the acceleration signal, and calculating a cross-point frequency response function matrix; 5, parameter decoupling calculation is carried out, wherein parameter decoupling is achieved through cross iterative optimization; and 6, outputting parameters. Through the decoupling calculation of the low frequency band and the high frequency band, the cross iteration optimization method can effectively reduce the calculation error, improves the parameter decoupling precision, and guarantees the reliability of the test result under different frequency bands.

The invention discloses a variable-working-condition engine health assessment method and device based on NCA metric learning and electronic equipment, and the method comprises the steps: constructing a long-short-term memory convolution automatic encoder LSTMCNNAE feature extraction model, training the LSTMCNNAE feature extraction model through the data of an engine training set, and obtaining a trained LSTMCNNAE feature extraction model; engine test set data are input into the trained LSTMCNNAE feature extraction model, and low-dimensional time sequence degradation feature data are obtained; constructing and training an NCA metric learning model in each fault mode, and mapping the low-dimensional time sequence degradation feature data by using the trained NCA metric learning model in each fault mode to obtain mapping feature data; and performing engine health assessment processing based on the optimized Mahalanobis distance feature matrix and the mapping feature data.

The invention relates to the technical field of torque motors, in particular to a torque performance detection system and method for a torque motor. The method comprises the following steps: evaluating the initial performance of the motor by acquiring object data of the torque motor and acquiring structural data; predicting a torque fluctuation dynamic overrun condition according to the initial performance of the motor, further evaluating an electromechanical coupling chain scission effect, and calculating a dynamic thermal load overload degree; evaluating the abnormal condition of the motor, analyzing the operation balance attenuation trend of the motor, and carrying out optimization processing based on the performance attenuation condition and the aging fault probability of the motor; according to the invention, the torque motor is optimized, so that the operation efficiency of the torque motor is higher.

The invention provides an engine fault prediction method and device. The method comprises the following steps: acquiring historical operation data of an engine; according to the historical operation data and a Bayesian prediction model, a fault classification model of the engine is determined, and the Bayesian prediction model is a preset model of a remote monitoring platform; engine operation data collected by the sensor in the real-time operation process of the engine are obtained, wherein the engine operation data comprise first abnormal operation data; and determining a first predicted fault type of the engine according to the first abnormal operation data and a fault classification model. By means of the engine fault prediction method and device, the operation condition of the engine can be mastered in real time, the fault of the engine can be predicted, and the problem that in the prior art, due to the fact that an off-line regular test method is adopted for monitoring, a large neutral position period exists, and fault prediction of the engine is not accurate is solved.

The invention discloses an aviation hybrid power turbine power generation system test run rack which comprises a test run platform, a first mounting rack arranged on the test run platform and used for supporting an engine and a second mounting rack arranged on the test run platform and used for supporting a generator. A linear guide rail parallel to the axial direction of the engine, a bottom plate arranged on the linear guide rail in a sliding mode and a driving mechanism used for driving the bottom plate to slide relative to the linear guide rail are arranged on the test run platform, and the first mounting frame is arranged on the bottom plate; the driving mechanism drives the first mounting frame to move through the bottom plate so as to adjust the distance between the first mounting frame and the second mounting frame; the test bench for the aviation hybrid power turbine power generation system can be suitable for combined tests of different engines and generators, can be compatible with complete machine test tests of an aviation hybrid power split type eddy current system or an integrated type eddy current system, and is wide in application range.

The invention discloses a diversion cooling device and a rocket engine ignition test system, and belongs to the technical field of rocket launching tests. The flow guide cooling device comprises a spraying piece, a flow guide mechanism and a water supply mechanism. The spraying piece is arranged at the initial section of the tail flame of the rocket engine, a water curtain barrier can be arranged through spraying from top to bottom, cooling and noise reduction are achieved, fuel gas of the tail flame is prevented from burning other devices, and the temperature of the cooled tail flame cannot be too high when the cooled tail flame makes contact with the flow guide mechanism, and the flow guide mechanism cannot be damaged; in the flow guide mechanism, a flow guide groove water spraying panel which is in an arc shape and protrudes downwards in an inclined mode and flow guide groove bodies located on the two sides of the flow guide groove water spraying panel are used for conducting comprehensive spraying and flow guide on the high-impact-force and high-temperature tail flame, cooling and noise reduction are achieved, and water spraying areas with different spraying densities can conduct targeted spraying according to the temperature of the inner flame and the outer flame of the tail flame. And the arc plate and the second nozzle are detachable, so that the arc plate and the second nozzle are convenient to replace, assemble and disassemble after a certain part is damaged by high temperature, the cost is reduced, and the use economy is improved.

The invention discloses a GMM-L2 fault diagnosis method, device and equipment based on a DBGSA algorithm and a medium, and relates to the technical field of engine fault detection, and the method comprises the steps: obtaining the original data of a wind power engine; processing the original data of the wind power engine to obtain second data; then calculating a first clustering center in the second data for generating a first Gaussian mixture model for calculating a health degree; setting an alarm limit according to the health degree, and if the second data is smaller than the alarm limit, determining that the second data is in an abnormal state; processing the second data in the abnormal state to obtain third data; updating the clustering center of the third data by adopting a DBGSA algorithm of fuzzy clustering to obtain a third clustering center; and setting a membership threshold value of the fault type, and calculating the membership probability of the fault type to which each cluster belongs to obtain the fault type to which the third data belongs. According to the method, missing detection caused by classifying only one data point into one fault can be avoided.

The invention relates to an engine vibration boundary condition calibration test bed and a test method, and belongs to the technical field of vehicle testing. According to the technical scheme, the engine vibration boundary condition calibration test bed comprises a simulation suspension used for installing an engine to be calibrated; the vibration excitation device comprises a Z-direction vibration exciter located at the bottom of the simulation suspension, a Y-direction vibration exciter located on one side or two sides of the simulation suspension in the vehicle driving direction, and an X-direction vibration exciter located on the front side and / or the rear side of the simulation suspension in the vehicle driving direction; a plurality of acceleration sensors which are installed on the simulation suspension and are used for collecting acceleration signals of the simulation suspension; and the data processing module is used for collecting and processing acceleration signals of the plurality of acceleration sensors. The scheme has the beneficial effects that the vibration environment of the engine in actual work can be accurately simulated, a reliable basis is provided for vibration calibration, and the calibration efficiency and the data accuracy are improved at the same time.

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 a maximum unbalance test method and system for a double-rotor turboshaft engine, and the method comprises the steps: analyzing the vibration mode and working speed of a rotor, determining the test content of each rotor, formulating the design requirements of a vibration test scheme of a whole machine, a rotor / shaft system, an accessory and a pipeline, and determining the maximum unbalance of the whole machine according to the test content. A fuel gas generator rotor acceleration and deceleration test and a power turbine rotor acceleration and deceleration test are respectively carried out by adopting an Np rotating speed open-loop control mode, and finally vibration test data are analyzed to verify the vibration level of each part. Due to the adoption of Np rotating speed open-loop control, follow-up change of the power turbine rotor under the action of airflow due to the change of the rotating speed of the fuel gas generator rotor is avoided, and the rotating speed of the fuel gas generator rotor does not need to be changed when the rotating speed of the power turbine rotor is changed; therefore, independent verification of the fuel gas generator rotor and the power turbine rotor can be realized, and interference is avoided.

The invention provides a high-temperature-rise-rate temperature distortion test system and test method, and belongs to the technical field of aero-engine tests, and the system comprises a gas inlet channel, a gas generation device, a fuel supply device, a combustion-supporting gas supply device, a process gas supply device, a control device and a measurement device. After rich fuel is mixed with combustion-supporting gas in a certain proportion in the combustor for combustion, high-temperature fuel gas is guided into the gas inlet channel through the flame guide assembly, secondary combustion is conducted in the gas inlet channel, the high-temperature fuel gas is evenly mixed with high-speed cold air in the gas inlet channel, other combustors do not work, and the cold air from an inlet of the gas inlet channel is still in a corresponding area; cold air and hot air flow into the engine at the same time, a distortion temperature field is formed at an inlet of the engine, so that simulation of temperature distortion test parameters of an inlet section of a power source of the engine is achieved, adjustment of the temperature rise rate is achieved by controlling the fuel supply rate and other modes, and high-temperature-rise-rate temperature distortion tests with different requirements can be achieved.

A snake-arm robot and a servicing device are mechanically coupled. The mechanical coupling is accomplished by a longitudinal insertion of the snake-arm robot into the servicing device or the servicing device into the snake-arm robot. An actuator moves the snake-arm robot through a passage within an engine until the snake-arm robot reaches a desired location. The movement of the snake-arm robot concurrently moves the servicing device through the passage. Subsequently, the snake-arm robot is de-coupled from the servicing device and the snake-arm robot is removed from the engine while leaving the servicing device in place within 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 relates to the technical field of data processing, in particular to an engine running state monitoring method and system, and the method comprises the steps: obtaining a vibration signal and a crankshaft rotating speed signal of an engine in real time, and converting the vibration signal from a time domain to an angle domain by taking the crankshaft rotating speed signal as a reference; performing order spectrum analysis on the vibration signal in the angle domain to generate a real-time order spectrum, and comparing the real-time order spectrum with a reference order spectrum to determine the energy deviation of each order; meanwhile, extracting waveform segments of each order in a plurality of continuous periodic vibration signals, and calculating the similarity between the waveform segments so as to evaluate the morphological dispersion degree and quantify the morphological stability degree; and finally, the energy deviation and the form stability degree are fused, the comprehensive fault risk index of each order is determined, and the operation state of the engine is monitored based on the comprehensive fault risk index of each order. The method improves the accuracy and reliability of engine state monitoring.

The invention discloses a method for rapidly predicting and dynamically regulating and controlling the quality of a flow field of a gas compressor under a low Reynolds number. According to the method, firstly, pressure gradient parameters Ks of a blade suction surface laminar flow separation point under different Reynolds numbers are obtained through high-precision performance testing / numerical calculation, and then experience prediction models of the Ks, an incoming flow Reynolds number Re, a separation point momentum thickness Reynolds number Re theta s, a blade surface separation scale and boundary layer development characteristics are sequentially established; and the influence of the low Reynolds number effect on the separation bubble structure and the boundary layer growth rate is quantified, so that the performance degradation degree of the gas compressor under the low Reynolds number can be quickly predicted. Based on the model, parameters such as excitation frequency of the front edge deformation surface of the blade are optimally configured, periodic pressure disturbance waves are induced to be generated, and dynamic regulation and control of large-scale separation flow under the low Reynolds number are achieved. The prediction speed of the performance variation of the gas compressor under the low Reynolds number is increased, and support is provided for aerodynamic design and performance regulation and control of the high-altitude gas compressor.

The invention relates to the technical field of data processing, in particular to a gearbox operation state abnormity monitoring and alarming system based on sensor analysis, and the system comprises a data collection module which is used for collecting a vibration signal of a gearbox, obtaining a time domain signal, constructing a time domain graph, converting the time domain signal into a frequency domain signal, and constructing a spectrogram; the data analysis module is used for obtaining a running state preliminary evaluation coefficient of the gearbox according to the amplitude of each frequency in the spectrogram and the number of peak points and valley points in the time domain graph; the feature obtaining module is used for obtaining resonance related feature indexes according to the spectrum width in the spectrogram and the peak point in the time domain graph if the running state preliminary evaluation coefficient is within the preset range; obtaining related characteristic indexes of the engine according to the amplitude of the engine frequency in the spectrogram; and the abnormity alarm module is used for performing abnormity alarm on the gearbox according to the resonance related characteristic indexes and the engine related characteristic indexes, so that the accuracy of performing abnormity alarm on the running state of the gearbox is improved.

Operating a fuel injector in a fuel system for an engine includes energizing a first solenoid actuator to move a spill valve from a first position to a second, closed position, and energizing a second solenoid actuator to move a fuel injection valve in the fuel injector from a closed position to an open position. A pull-in tier of a waveform energizing the second solenoid actuator is generated via a first current produced by a boosted voltage power supply and a second current produced by a lower voltage power supply. Arrival timing of the valve at the open position is detected based on a property of the second current, such that a valve arrival timing error may be used to trim the fuel injector. Related methodology and control logic is also disclosed.

The invention discloses a fusion diagnosis method for potential multiple faults of an aero-engine gas path in a transition state, and belongs to the field of aero-engine fault diagnosis. The fusion diagnosis method for the potential multiple faults of the aero-engine gas path in the transition state comprises the steps that collaborative noise reduction and multi-dimensional representation of aero-engine gas path transition state data are studied to obtain multi-dimensional gas path transition state sample data; constructing an aero-engine gas path transition state potential multi-fault fusion diagnosis model, training the diagnosis model by using the multi-dimensional gas path transition state sample data, and outputting a fault diagnosis result by using the trained aero-engine gas path transition state potential multi-fault fusion diagnosis model; the aero-engine gas path transition state potential multi-fault fusion diagnosis model is explained, and a fault mechanism is revealed; accurate mapping and mechanism revealing from limited gas path monitoring information to potential multiple faults are achieved, and theoretical and application support is provided for interpretable intelligent operation and maintenance of an aero-engine.

The invention belongs to the technical field of aero-engine vibration tests, and particularly relates to an aero-engine vibration assessment test method and system. Comprising the following steps: determining the worst vibration environment of accessories; determining the staying rotating speed of an engine rotor and the staying time of the staying rotating speed; according to the staying rotating speed of the engine rotor and the staying time of the staying rotating speed, a vibration assessment test run spectrum is formulated; based on the worst accessory vibration environment, carrying out an engine complete machine test by referring to the vibration assessment test run spectrum; generating an engine rotating speed and vibration curve graph according to the whole engine test measurement data, and making an accessory vibration limit value; an accessory vibration assessment test is carried out on a complete engine, and the complete engine used in the accessory vibration assessment test simulates the possible maximum vibration environment and test temperature of accessories in a full operation cycle and a full rotation speed range; and the installation and vibration environment is more in line with the engineering practical situation.

The invention relates to the technical field of turbocharger experiments, in particular to a turbocharger surge experiment device which comprises a first branch pipe, a second branch pipe, a surge tank and an exhaust pipe, a vortex shedding flowmeter and a first flow adjusting valve are arranged on the exhaust pipe, and the two sides of the exhaust pipe are connected with the first branch pipe and the second branch pipe respectively. A surge relief valve is arranged on a pipeline of the first branch pipe, a second flow regulating valve is arranged on a pipeline of the second branch pipe, a flow limiting valve is arranged at one end of the pressure stabilizing tank, a pressure difference transmitter is arranged at the other end of the pressure stabilizing tank, the flow limiting valve is connected to a pipe section in front of the vortex shedding flowmeter through a connecting pipe, and a three-way connector is arranged on a pipeline of the connecting pipe. And the three-way joint is connected to the pressure difference transmitter through a pipeline at one end. The test device not only can simulate the surge generation condition of the turbocharger, but also can test the surge bearing limit of the turbocharger, and ensures smooth research and development of the turbocharger.

The invention discloses a voiceprint monitoring method, system, medium and equipment for rotation stall of an aero-engine compressor, and the method comprises the steps: determining the layout of a microphone array through the model parameters of the compressor of the aero-engine, and carrying out the synchronous collection of sound pressure time domain signals of multiple channels of the compressor of the aero-engine through the microphone array; arranging the multi-channel sound pressure time-domain signals in sequence to construct a time-domain signal matrix; performing spectral analysis on the sound pressure time-domain signals by adopting a fast Fourier transform algorithm to obtain a spectrogram of the sound pressure time-domain signals of each channel, monitoring whether an abnormal single-tone frequency peak value lower than one time of rotation frequency appears in the spectrogram or not, obtaining an acoustic mode spectrogram of the abnormal single-tone frequency peak value by adopting a single-frequency acoustic mode decomposition method, and obtaining an acoustic mode spectrum of the abnormal single-tone frequency peak value; and whether the rotating stall characteristic of the gas compressor occurs in the acoustic mode spectrogram is monitored to judge whether the rotating stall characteristic of the gas compressor occurs or not.

The invention relates to the technical field of aviation equipment monitoring, and particularly provides a fatigue life consumption determination method and equipment for an aero-engine wheel disc, and the method comprises the following steps: measuring any rotation speed cycle of the wheel disc, and calculating the fatigue life consumption of the aero-engine wheel disc based on the rotation speed cycle; acquiring corresponding peak stress and valley stress; based on the peak stress and the valley stress, the maximum equivalent stress is obtained by combining the preset stress ratio of the wheel disc and the material strength of the wheel disc; on the basis of the maximum equivalent stress, a fatigue damage conversion coefficient is obtained by combining a stress and life curve model; and obtaining the service life consumption of the wheel disc based on the fatigue damage conversion coefficient in combination with a rotating speed cycle value corresponding to the rotating speed cycle. A relation is established between the service life consumption of the wheel disc and the rotating speed circulation, the accuracy of the obtained service life consumption of the wheel disc is ensured without a given rotating speed circulation interval and a fatigue damage conversion coefficient, the maintenance period of the engine is shortened, and the use economy of the engine is improved.

The invention relates to the technical field of motor testing, and discloses an intelligent diagnosis system and method for a brushless motor of a vehicle water pump, and the method comprises the steps: collecting an actually-measured first vibration mean value, and obtaining an estimated second vibration mean value of a brushless motor to be tested at the r + v rotating speed based on the actually-measured first vibration mean value; acquiring an actually measured second vibration mean value of the brushless motor to be measured at the r + v rotating speed, and judging whether the brushless motor to be measured has abnormal performance according to the estimated second vibration mean value and the actually measured second vibration mean value; the process is repeated until abnormal performance occurs or r is equal to R, circulation is ended, the temperature reference value, the temperature mean value and the electrical measurement value are input into a first machine learning model, and an electrical correction value is obtained; intercepting an abnormal wave band in the actual electrical oscillogram, and inputting the abnormal wave band into a second machine learning model in an image form to obtain a fault type of the brushless motor to be tested; according to the invention, the fault type of the brushless motor can be diagnosed with high accuracy.

An operating condition design method for reliability verification of a dual-motor system of a P13-configuration electric drive transmission and a reliability testing method for a dual-motor system of a P13-configuration electric drive transmission, which meet the development, usage, and safety requirements of electric drive transmissions while shortening the product development cycle. The design method comprises: on the basis of structural principles and usage modes of P13-configuration electric drive transmissions, and considering also motor verification coverage scenarios and whole-vehicle road scenarios, designing dual-motor system reliability verification operating conditions which use P3 motor operating conditions as the main conditions, complemented by P1 motor operating conditions; and combining product performance design parameters and whole-vehicle control logic to form an initial operating condition test table for the dual-motor system reliability verification operating conditions (S101); and adjusting the running time of each operating condition in the initial operating condition test table, so as to obtain a final required operating condition test table for dual-motor system reliability verification and the number of operating condition cycles for the dual-motor system reliability verification (S102).

Embodiments of the present application disclose a fuel injection parameter adjustment method, device, equipment and storage medium. The fuel injection parameter adjustment method comprises: determining that a vehicle enters a series-parallel hybrid working condition; recording a set of initial fuel injection parameters of an engine; performing fuel injection parameter self-learning, obtaining a plurality of sets of test fuel injection parameters based on the set of initial fuel injection parameters; sequentially using the plurality of sets of test fuel injection parameters to run the engine, and calculating a plurality of test fuel consumptions of the vehicle; wherein each set of test fuel injection parameters corresponds to a test fuel consumption; the running time of each set of test fuel injection parameters is a first self-learning time; based on comparing the plurality of test fuel consumptions, determining an optimal self-learning result from the plurality of sets of test fuel injection parameters; and replacing the initial fuel injection parameters with the self-learning result.

The utility model relates to the field of diesel engine fuel injection valves, and in particular to a multifunctional dual-fuel low-speed diesel engine fuel injection valve. The multifunctional dual-fuel low-speed diesel engine fuel injection valve includes a check valve, a top cover, a valve seat, a nozzle, a limiting structure and an anti-skid structure. The check valve is located at the top and is used for high-pressure fuel inlet. The top cover is located below the check valve to enhance the stability of the lift. The valve seat is located below the top cover and is used to control the high-pressure hydraulic oil inlet of the thrust block stroke. The nozzle is located at the lower part of the valve seat and is used to control the injection of high-pressure fuel. A limiting structure is provided between the nozzle and the valve seat, and the nozzle is quickly disassembled and assembled through the limiting structure. An anti-skid mechanism is provided on the top cover, and the anti-skid structure is used to limit the loosening of the top cover when in use. The utility model can quickly disassemble and assemble the nozzle through the designed limiting structure, which greatly improves the convenience of repairing and replacing the nozzle, reduces downtime, and improves work efficiency.

The invention provides a single-line excitation OH plane laser-induced fluorescence temperature measurement system and method, and belongs to the technical field of aero-engine special tests, the system comprises an Nd: YAG laser, a sheet light shaping lens group, two ICCD cameras and a data acquisition device, the laser outputs quadruplicated pulse laser, the sheet light shaping lens group is arranged at the output end of the laser, and the data acquisition device is arranged at the output end of the laser. Laser sheet light is output through the sheet light shaping lens group to illuminate a to-be-detected area in the flame and reacts with OH groups in the flame to generate fluorescent light; the cameras are respectively arranged opposite to flames, are respectively in communication connection with the data acquisition device, are respectively provided with a band-pass optical filter with different bandwidths, and are used for synchronously measuring fluorescence to obtain a bispectral fluorescence image, and the data acquisition device is used for carrying out data processing on the image to realize two-dimensional temperature distribution measurement. Through the processing scheme provided by the invention, the measurement system configuration and the data processing flow are remarkably simplified, and the light spot quality and the signal-to-noise ratio are improved.