68 results about "Engine test stand" patented technology

The invention provides an aero-engine test bed. The aero-engine test bed comprises a rack and an auxiliary support, the auxiliary support comprises a mounting platform, a mounting seat, a connecting piece, a supporting arm, a field force limiting mechanism and a controller; the mounting platform is arranged on the rack; the two mounting seats are oppositely arranged on the mounting platform; the connecting piece is arranged between the two mounting seats and is opposite to the mounting platform; the connecting piece is configured to move in the vertical direction; the supporting arm corresponds to the mounting seat; the two ends of each supporting arm are hinged to the corresponding mounting base and the corresponding connecting piece correspondingly. The supporting arm is provided with an installation joint used for being connected to an aero-engine. The field force limiting mechanism comprises a first component and a second component which are oppositely arranged; the first component is arranged on the mounting platform, and the second component is arranged on the connecting piece; and the controller is electrically connected with the field force limiting mechanism. Through cooperative work of the field force limiting mechanism and the controller, the supporting rigidity of the auxiliary support can be dynamically adjusted according to the real-time rotating speed of the aero-engine in the test run process.

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 present invention relates to a micro-engine test bench. A roll and pitch attitude test bench for a micro-engine, comprising a micro-engine and a support base, is characterized in that it further comprises a pitch test bench, which is mounted on the support base through a pitch device for driving its pitching motion; the micro-engine is fixedly mounted on a roll table, and the roll table is further mounted on the pitch test bench through a roll device for driving its rolling motion; a vibration sensor, a rotational speed sensor, an inclination sensor, and a tail nozzle temperature sensor are provided on the roll table, and all of them send induction signals to an electrical control cabinet. At the same time, the electrical control cabinet is also electrically connected to the pitch device and the roll device for controlling the pitch device and the roll device. The present invention realizes the precise control of the pitch angle and roll angle of a turbojet engine, simulates the real attitude of the micro-turbojet engine in the air, and accurately obtains various technical parameters when the micro-turbojet engine rolls and pitches.

The utility model discloses a rotation measuring device for an aero-engine test bed, which belongs to the technical field of aero-engine test beds and comprises an oil storage supporting box, one end of the oil storage supporting box is fixedly sleeved with a front adapter, and the other end of the oil storage supporting box is fixedly sleeved with a rear adapter. A measuring circular ring is rotationally connected between the front adapter and the rear adapter and located in an inner cavity of the oil storage supporting box, and three measuring mechanisms are arranged on the measuring circular ring. According to the utility model, the lubricating oil is arranged at the bottom of the inner cavity of the oil storage supporting box, and when the first motor drives the pinion to rotate and the measuring circular ring and the plurality of measuring mechanisms are driven to rotate through the meshing transmission between the pinion and the bull gear, the meshing transmission part between the pinion and the bull gear is lubricated by using the lubricating oil; and abrasion between the small gear and the large gear is relieved, the service life of the small gear and the large gear is guaranteed, and the practicability of the device is good.

The application discloses a remote control torch ignition system based on wireless instruction and fault self-diagnosis function and relates to the technical field of space propulsion. The application comprises a remote control center and a field control unit. The remote control center is used for generating an encrypted ignition instruction package containing an ignition instruction sequence and adjustable parameters and sending the package through a wireless data link, simultaneously receiving and displaying control feedback and diagnosis data from the field. The field control unit is arranged on an engine test stand and is electrically connected with a torch igniter and its matched fuel valve, oxidant valve and ignition power supply, used for receiving, decrypting and executing the encrypted ignition instruction package to control the corresponding valves and ignition power supply to act in sequence. The system further comprises a multi-dimensional data acquisition module used for synchronously acquiring multi-channel physical quantity time sequence signals reflecting the working state of the igniter during the ignition process. Through embedded multi-dimensional time sequence fusion diagnosis, the application can quantitatively evaluate the performance gradual state of the torch igniter in real time.

The present application belongs to the field of aero-engine ground test technology, and provides an aero-engine test stand ground vortex test method and device. The method coats a brightening coating on the fan blades, rotating cap cover and inlet duct inner wall of the engine, and sets a background plate and a side high-speed camera on both sides of the inlet duct, wherein the background plate is opposite to the side high-speed camera and is in the field of view of the side high-speed camera, and the surface of the background plate is provided with a high-density random speckle pattern; the front high-speed camera is arranged opposite to the inlet duct to construct a double-view high-speed imaging system. When the engine is stably operated at a target speed, the double cameras are synchronously triggered to shoot image sequences; the cross-correlation calculation is performed based on the side image and the vortex-free background speckle pattern to generate a ground vortex center trajectory and fit a development curve; and the ground vortex centroid and cross-sectional area are determined based on the front image through a gray scale weighting method. The method does not need to invade the flow field, and can realize the synchronous quantification of the spatial evolution and cross-sectional morphology of the ground vortex.

The invention relates to the technical field of spaceflight, and discloses an emergency shutdown system and method for a rocket engine test bed, and the system comprises a sensor output module which is used for receiving the input and output of a pressure sensor signal and a frequency signal, and outputting a sensor signal; the simulation module is used for loading simulation signals and simulating various signal combinations in an emergency shutdown scene; the signal switching module is used for switching a sensor signal and a simulation signal by using a two-in and one-out interface assembly; the signal acquisition and processing module adopts an FPGA (Field Programmable Gate Array) and DMA (Direct Memory Access) hardware structure, performs interpretation according to an emergency shutdown condition when receiving the starting signal, and outputs an emergency shutdown signal when the emergency shutdown condition is met; the control module is used for completing the emergency shutdown action when receiving the emergency shutdown signal, and by switching the sensor signal and the simulation signal, the requirements of different test scenes are met, the emergency shutdown condition interpretation is executed, the automatic emergency shutdown function is achieved, and the safety and the emergency shutdown debugging efficiency are improved.

The utility model discloses an aero-engine test bed tail gas treatment device, which relates to the technical field of tail gas treatment, and comprises a bottom plate, a silencing mechanism is arranged at the top of the bottom plate, an adsorption mechanism is arranged at one end of the silencing mechanism, a spraying mechanism is arranged at one end of the adsorption mechanism, and the spraying mechanism comprises a spraying box. And the spraying box is fixedly connected to the top surface of the bottom plate. Through cooperation of the spraying mechanism, the spraying box, the drainage pipe, the fixing ring, the motor, the first gear, the second gear, a water guide pipe, a gas outlet pipe, a valve, a water tank, a water inlet pipe, a hollow pipe, an atomizing nozzle and a connecting groove, tail gas is atomized and sprayed by using a catalyst in the spraying box after being adsorbed, so that the temperature of the tail gas can be reduced; the device can protect surrounding facilities and instruments, absorb unadsorbed toxic gas in the tail gas, prevent the toxic gas from being discharged into the air, reduce pollution of harmful gas emission to the atmospheric environment and protect the ecological environment.

The invention discloses a turboprop engine test bench which comprises a static frame, a movable frame, a spring piece and a protection device, the static frame is used for being hung and fixed to a roof of a test plant, the movable frame is arranged below the static frame and used for installing a turboprop engine, and the spring piece is arranged between the static frame and the movable frame; the protection device comprises a first protection seat installed on the static frame and a second protection seat installed on the movable frame, a bearing groove is formed in the side face of the first protection seat, and the second protection seat comprises a supporting block which extends into the bearing groove from the side face of the first protection seat and has a preset gap relative to the bottom wall of the bearing groove. The supporting block is used for falling onto the bottom wall of the bearing groove when the spring piece loses efficacy and is supported and fixed through the bearing groove. According to the turboprop engine test bed, the distance between the movable frame and the static frame can be effectively reduced, the length of the spring piece is shortened, the bending moment and deformation borne by the spring piece in the test process are reduced, and the machining precision requirement of the spring piece is lowered.

The invention relates to a sand vibration isolation foundation of a medium-high speed engine test bed, and belongs to the field of engine test bed foundations. The device sequentially comprises a concrete cushion layer, a concrete shell foundation, a sand vibration isolation layer, a balancing weight, a sizing block and a cast iron bottom plate. A brick mold and an outer waterproof layer are arranged on the outer side of the concrete shell foundation, an inner waterproof layer is arranged on the inner side of the concrete shell foundation, trenches are formed between the two sides of the balancing weight and the concrete shell foundation, a steel cover plate is arranged above the trenches, and a slope is made at the bottom of the trenches to facilitate liquid collection; the sand vibration isolation layer is further provided with a composite geomembrane and a steel mold, and liquid on the upper portion is isolated from permeating into the sand vibration isolation layer. Vibration mechanical energy transmitted from the upper portion is converted into heat energy to be dissipated by arranging the sand vibration isolation layer, vibration wave energy penetrating through the sand layer is reduced, compared with a common engine test bed foundation vibration isolation method, the excavation depth is reduced, the comprehensive manufacturing cost is reduced, the overhaul frequency is reduced or overhaul is avoided, and the construction cost is reduced. And meanwhile, the method can be adapted to a rack vibration isolation foundation form for transforming a built engine rack foundation to the maximum extent.

The utility model discloses an engine test bed steel frame, including steel column, hanging column and horizontal support spare, the utility model with steel column as the core bearing component, forms horizontal rigid connection through the first frame beam, second frame beam and steel beam of adjacent steel column top installation, constitutes spatial grid system, sets up the cross support system link between second frame beam, promotes the structural lateral displacement resistance ability significantly, combines steel beam pre-arch technology, ensures the stability under the large -span working condition, and the hanging column forms three point restraint system through internal structure, and the accurate positioning of cooperation assembly jig frame realizes the stable transmission of engine hoisting load, and the horizontal support spare constitutes the composite stress system by the vertical installation second connecting rod and the connecting rod of different inclination angle arrangement, forms spatial truss effect, effectively resists the horizontal vibration when the engine operation, prevents the frame torsional deformation, and the overall structure has high precision, anti -dynamic load and long -life characteristics.

The application provides an aero-engine test stand multi-sensor data space-time correlation detection method, comprising: selecting a certain specific test condition data, using different baseline modeling algorithms, respectively based on the physical space relationship of different sections of the aero-engine sensor, the physical space relationship of different measuring rakes and different radii on the same section, and the sensor data in a certain period of time, verifying the response data of the rake sensor and judging the abnormal condition of the sensor, correlating and deeply mining the multi-dimensional information of the aero-engine, and providing data support and important guarantee for the safety of the test system and the aircraft. The application can fully realize the verification and abnormal detection of the sensor response data in a short period under different test conditions.

The invention belongs to the technical field of test equipment design, and particularly relates to a top-down aero-engine test bed overall structure design method and system.The method comprises the steps that an initial design input set is formed according to test bed requirements and test working conditions; respectively mapping each design constraint in the initial design input set to a pre-divided test bed multi-level logic layer, and generating an initial main model scheme; forming a multidisciplinary constraint rule base according to a preset multidisciplinary interface requirement; according to the initial main model scheme and the sub-disciplinary design requirements, generating a corresponding disciplinary view model; and performing simulation analysis on the view models of each subject, and performing iterative optimization on simulation results of the view models of each subject in combination with design constraints and rule constraints to generate a final overall main model scheme. According to the method, the incidence relation of the subsystems and the coordination relation of multiple disciplines are comprehensively considered, synchronous updating of the models at all levels is achieved, and the design efficiency and the overall performance of the test bed are remarkably improved.

The application belongs to the technical field of liquid rocket engine test, and relates to a liquid rocket engine test bench tail gas energy efficient utilization system, which comprises an air source, an adjustable throat area nozzle assembly, a turbine power generation device and a controller. The air source is connected with one end of the adjustable throat area nozzle assembly through a first pipeline, and the other end of the adjustable throat area nozzle assembly is connected with the turbine power generation device through a second pipeline. The controller is connected with the first pipeline, the second pipeline and the adjustable throat area nozzle assembly to control the throat area change of the adjustable throat area nozzle assembly according to monitored pipeline parameters, and then adjust the nozzle outlet velocity, so that the turbine work can be at a higher working efficiency point. The application can improve the power generation efficiency of the power generation device.

The invention relates to a rocket engine test bed network system, in particular to a design method for a high-reliability network structure of an engine test bed, and solves the technical problems of low resource utilization rate, cross-system coordination delay, relatively high operation and maintenance cost and single-point failure risk of an existing rocket engine test bed network architecture. The design method for the high-reliability network structure of the engine test bed comprises the following steps: 1) determining all systems of the engine test bed to be graded; 2) dividing the grades of the systems of the engine test bed to obtain the network importance grades of the systems of the engine test bed; 3) integrating the network structure of the engine test bed according to the network importance levels, wherein the system of the first network importance level adopts an independent looped network architecture; the system of the second network importance level and the system of the third network importance level both adopt a'core-convergence-access' three-layer topology architecture, and the design of the high-reliability network structure of the engine test bed is completed.

The invention discloses an aero-engine test bed performance test analysis method and system, and relates to the technical field of test bed performance tests.The aero-engine test bed performance test analysis method comprises the steps that the error times in error records caused by error objects representing test bed parts and the error total value representing the sum of error values generating all error values are obtained; evaluation values of the error objects are obtained after calculation, and high-frequency labels, conventional labels and low-frequency labels are sequentially marked on the error objects according to a set proportion according to the descending order of the evaluation values; the problems of the test bed, which are long-term or high-frequency problems, can be determined; then, for the test object capable of detecting the fault of the error object, determining verification detection according to the data distribution condition of the previous detection time of the test object, and giving different weights in combination with the detection accuracy of the test object and a compatible value representing the number of the error objects capable of being detected by the test object, so as to obtain an available value of the test object; and marking the test object with the maximum available value as the selected test object.

The utility model discloses a turbojet engine test bed, which belongs to the technical field of turbojet engine test experiments and comprises a fixed seat, a movable plate slidably connected to the top of the fixed seat, a thrust sensor arranged between the movable plate and the fixed seat, supports connected to two sides of the movable plate, and an adjusting block connected to the top of each support through a first bolt. A strip-shaped hole is formed in the adjusting block, and a first bolt penetrates through the strip-shaped hole to fasten the adjusting block and the top end of the support. The tops of the adjusting blocks are connected with pressing blocks through bolts; the hoops comprise the upper hoops and the lower hoops, the multiple sets of hoops are arranged according to the size of the turbine engine, the upper hoops and the lower hoops are connected between the pressing block and the adjusting block in a fastened mode and used for holding and fixing the turbojet engine, and the tops of the upper hoops are connected with vibration collectors; the thrust sensor and the vibration collector are connected with an external processor through data lines. The device is small and portable in structure, easy and convenient to apply, wide in application range and suitable for turbojet engines of various specifications.

The utility model discloses a steel cable system for a turboshaft engine test bed, and relates to the technical field of turboshaft engines. The device comprises a steel cable, a rigid protective sleeve and a fixing device, the outer ring of the steel cable is in threaded connection with the rigid protective sleeve; a first universal ball head is arranged in a connector of the steel cable; a second universal ball head is arranged at the threaded connection part of the rigid protective sleeve and the steel cable; the first universal ball head is connected with an engine fuel regulator; the second universal ball head is connected with the fixing device; the fixing device is installed on an engine fuel regulator. According to the utility model, the steel cable system is fixedly supported, so that the control handle is smooth and not easy to block; a worker can accurately control the engine to complete testing, and meanwhile the service life of the steel cable is greatly prolonged.

The invention discloses a light-weight design-based locking type liquid rocket engine test bench, which is characterized in that a bench is fixedly mounted on the ground or in a pit, a bracket I, a bracket II, a bracket III, a bracket IV, a bracket V, a bracket VI, a bracket VII and a bracket VIII are mounted below a flat plate, and a platform support I and a platform support II are mounted above the flat plate; the platform is mounted above the first platform support and the second platform support, and the mounting plate used for being connected with a liquid rocket engine is mounted above the platform through the mounting plate transfer platform. The test bench has the advantages that the liquid rocket engine can move along with the test bench, locking of the mounting plate switching platform and the platform can be realized, and the liquid rocket engine can be subjected to hot test run tests at different positions on the platform.

The present invention provides an electronic throttle module with throttle opening display and fault diagnosis functions, and relates to the field of engine test technology. The electronic throttle module with throttle opening display and fault diagnosis functions includes a power supply circuit, a 6-pin aviation plug J1, a DC-DC power supply module P1, a connector J2, a dual-channel instrument amplifier integrated circuit IC1, and a DC voltmeter V1. In the present invention, the module verifies the correctness of the two sets of voltages based on the amplitude and linear relationship between the two voltages of the electronic throttle, displays the throttle opening through a DC voltmeter, displays the fault through the on and off status of two LED fault indicator lights, and judges the cause of the fault accordingly. It also adopts a double-sided copper-clad circuit board to achieve an integrated design, and uses a transparent cover waterproof box to achieve a waterproof function. It is suitable for use in engine test benches to reduce the difficulty of troubleshooting and improve work efficiency. It is suitable for promotion and application in the field of engine test technology and can be directly used to guide the design or production of related products.

An aero-engine test stand oil supply device and method with exhaust function, the oil supply device comprises a test stand, further comprising an oil depot, an oil tank, an oil gas separation tank and a recovery tank; the oil depot is used for storing aviation kerosene, and the oil depot is connected to the oil tank through a first oil pipeline; a pressure pump is connected to the oil tank through an air pipe; the oil tank is connected to the oil gas separation tank through a second oil pipeline; the oil gas separation tank is connected to the test stand through a third oil pipeline; the oil gas separation tank is further connected to the recovery tank through a fourth oil pipeline; a first valve is arranged on the first oil pipeline, a second valve is arranged on the third oil pipeline, and a third valve is arranged on the fourth oil pipeline; a shock device is arranged beside the second oil pipeline and used for shocking the oil pipeline. The shock device can shock the oil pipeline, and the aviation kerosene containing gas can be discharged into the recovery tank after the pressure pump is pressurized, so as to solve the problem of exhaust of the aero-engine test stand oil supply pipeline.

The invention provides a control method and device for a multi-cylinder engine test bed, and can be applied to the technical field of mechanical control. The control method of the multi-cylinder engine test bed comprises the steps that the expected rail pressure of an oil rail, the expected rotating speed of an engine, the actual rail pressure and the actual rotating speed are obtained, the oil rail is used for conveying fuel oil to an oil injector through the rail pressure, and the oil injector is used for injecting the fuel oil into air cylinders of the engine for combustion; combustion heat energy is converted into mechanical rotation of the engine; the rail pressure current duty ratio of a rail pressure electromagnetic valve is adjusted based on the rail pressure deviation between the expected rail pressure and the actual rail pressure, and the rail pressure electromagnetic valve is used for adjusting the fuel flow in the fuel rail; and the fuel injection current duty ratio of a fuel injection electromagnetic valve is adjusted based on the rotating speed deviation between the expected rotating speed and the actual rotating speed so that the rotating speed of the engine can be controlled, and the fuel injection electromagnetic valve is used for adjusting the fuel quantity in the fuel injector.

The invention belongs to the technical field of aero-engine ground tests, and provides an aero-engine test bed ground vortex test method and device, and the method comprises the steps: coating the inner wall surfaces of an engine fan blade, a rotating cap cover and an air inlet channel with a brightening coating, and respectively arranging a background plate and a side high-speed camera at the two sides of the air inlet channel, wherein the background plate is positioned right opposite to the lateral high-speed camera and is positioned in the field of view of the camera, and the surface of the background plate is provided with high-density random speckle patterns; a front high-speed camera is arranged to directly face an air inlet channel, and a double-view-angle high-speed imaging system is constructed. When the engine stably operates at the target rotating speed, the double cameras are synchronously triggered to shoot an image sequence; performing cross-correlation calculation based on the lateral image and the vortex-free background speckle pattern, generating a ground vortex center track, and performing fitting to obtain a development curve; and determining the mass center and the sectional area of the ground vortex through a gray weighting method based on the front image. The method does not need to invade into a flow field, and can realize synchronous quantification of ground vortex space evolution and section morphology.

The utility model relates to high -power turbo shaft engine test board electrical system belongs to engine test technical field, including alternating current source, test board controller, first alternating current direct current converter, second alternating current direct current converter, direct current direct current conversion unit, alternating current source connects respectively dynamometer, emergency power supply, still through first alternating current direct current converter connection fuel oil electric governing pump distribution input end, through second alternating current direct current converter connection starting generator distribution input end, emergency power supply passes through direct current direct current conversion unit and connects engine electronic controller, test board controller respectively, the system still includes distributed data acquisition module and sensor signal isolation unit. The existing turbo shaft engine test board electrical device electrical wiring complex, control precision low, system reliability poor problem is solved.

The embodiment of the invention provides a test bed fault prediction method and device of an engine, electronic equipment and a storage medium, and relates to the technical field of computers. The method comprises the steps of obtaining a first data set; analyzing the first data set based on the value range of each parameter in the first data set to obtain an analysis result of the first data set; and if the analysis result represents that the first data set has the abnormal parameter value, inputting the first data set into the fault prediction model, and outputting predicted fault information. The parameter values collected on the sampling points are combined into a first data set, the first data set is analyzed, whether abnormal data exist in the first data set or not is judged, if yes, the first data set is input into the trained fault prediction model, and a fault prediction result of the test bed is output. According to the scheme, the fault of the test bed does not need to be detected manually, manpower can be saved, meanwhile, the analysis standard of abnormal data is unified, and high precision is achieved.

The invention relates to an auxiliary assembly device for a universal shaft of an engine test bed. The auxiliary assembly device comprises a base, a movable support, a bidirectional displacement mechanism, a bearing connecting structure and a positioning restraining mechanism. A horizontal reference coordinate system is arranged on the top of the base. The movable support is driven by a two-way displacement mechanism, a horizontal driving assembly of the movable support controls X-axis displacement, and a vertical driving assembly of the movable support controls Y-axis displacement. The bearing connecting structure is fixed to the upper end of the movable support, and the inner ring radially restrains the central shaft section of the universal shaft. The positioning constraint mechanism predefines end face three-dimensional coordinates and axial directions of the engine output shaft and the load shaft. The bidirectional displacement mechanism drives the two ends of the universal shaft to synchronously arrive at theoretical coordinate points in a linkage mode and are axially collinear, and full-automatic high-precision centering is achieved. The split type movable support supports the disc body to be separated from the base body and rotate along with the shaft. The closed-loop servo system compensates offset in real time, the gravity center coincident bearing and the damping shock absorption layer cooperate to guarantee transmission stability, the assembly precision is remarkably improved, and the service life is remarkably prolonged.

The invention belongs to the technical field of hydraulic pump load monitoring, and provides an airspace engine test bed hydraulic pump load system which is characterized in that the change trend type of output pressure in each flow conveying fluctuation time period is further analyzed, if load alternate impact is caused by output pressure change, the early warning intervention time is acquired, and in the early warning intervention time, the early warning intervention time is acquired; therefore, when the output pressure is close to an over-high or over-low early warning line, the intervention opportunity is determined in advance, a worker can have enough time to stably adjust the working state of the hydraulic pump, the sudden shutdown condition is avoided, dynamic adjustment operation is conducted on load alternate impact within the early warning intervention time, and the working efficiency is improved. And the load of the hydraulic pump is kept stable, so that the acquired data is accurate and reliable, and a powerful basis is provided for subsequent engine performance analysis and improvement.

The utility model discloses a catalytic device for treating tail gas of an aero-engine test bed. The catalytic device is installed in an exhaust tower of the aero-engine test bed and located at an outlet of an injection cylinder. The catalytic device comprises a fixed frame and a catalyst module arranged in the fixed frame; the catalyst module comprises a circle of catalyst units arranged in the circumferential direction, a circular exhaust cavity is formed in the middle of each catalyst unit, and the exhaust cavities are connected with the injection barrel. The problems that an existing device is low in treatment efficiency, difficult to disassemble and replace and the like are effectively solved.

The invention discloses a supersonic wind tunnel diffuser for a ramjet engine test bed, and solves the technical problems of large design difficulty and high control requirements caused by wide working condition design and high production cost and shortened service life of equipment caused by multi-model design. According to the supersonic wind tunnel diffuser, the contraction section, the equal straight sections, the expansion section and the cooling section of the supersonic wind tunnel diffuser are independently arranged, the number of the equal straight sections is N, and the universal flange assembly is designed, so that the design effects of variable layout and adjustable length are achieved, the test requirements of engines of different specifications are met, and the test cost is greatly reduced.