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

The invention discloses 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.

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 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 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 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.

The utility model provides a test bed for a liquid oxygen methane engine. 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 gas path system comprises a first liquid nitrogen warehouse module, a second liquid nitrogen warehouse module, a gas making module and a gas distribution module. The first liquid nitrogen warehouse module comprises a first liquid nitrogen warehouse storage tank used for storing liquid nitrogen. The second liquid nitrogen warehouse module comprises a second liquid nitrogen warehouse storage tank used for storing liquid nitrogen. The gas making module comprises a liquid nitrogen storage box, a liquid nitrogen plunger pump, a liquid nitrogen vaporizer and a high-pressure nitrogen cylinder set. Wherein the liquid nitrogen in the first liquid nitrogen storage tank is filled into the liquid nitrogen storage tank through the second liquid nitrogen filling pipeline and is pumped into the liquid nitrogen vaporizer through the liquid nitrogen plunger pump to be gasified, and the gasified nitrogen is stored in the high-pressure nitrogen cylinder group. And the high-pressure nitrogen cylinder group is conveyed into the nitrogen distribution module through a nitrogen conveying main pipeline. 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 embodiment of the invention provides an engine test bench and a methanol filling system and a methanol filling method thereof. The methanol filling system comprises a daily container; a storage container; the filling unit comprises a controlled backflow pipeline, a controlled filling pipeline and a pumping module, the controlled backflow pipeline is connected between the pumping module and the storage container, the controlled filling pipeline is connected with the pumping module, and the pumping module is in pipeline connection with the daily container and the storage container; the filling unit is used for pumping methanol in the storage container to the daily container through the pumping module under the condition that filling of the controlled filling pipeline and filling of the storage container are both closed and filling of the controlled backflow pipeline and filling of the daily container are both opened. According to the embodiment of the invention, the methanol filling system can be simplified, so that the volume of the methanol filling system can be reduced.

The application relates to an aero-engine external oil system, which comprises a first oil tank, a second oil tank and the like; the system can work in an engine oil injection mode, an oil system self-flushing mode, an open external circulation mode, an internal self-circulation mode and an engine oil change mode; the application can realize automatic switching of two oil supply and return modes of the external open circulation and the internal self-circulation of the engine, simultaneously has the functions of cooling and heating the oil, and has the functions of measuring the oil supply amount and the oil consumption amount, and the applicability of the oil system of the test bench under different scenes is improved.

The invention relates to a multifunctional signal conditioning method for acquiring slowly varying parameters of an engine test bed. The multifunctional signal conditioning method solves the technical problems that an existing signal switching device is not flexible enough, tedious in calibration and insufficient in safety and reliability. The method comprises the following steps: S0, preparing a signal conditioning system; the method comprises the following steps: S1, electrifying a signal conditioning system, and establishing communication with an upper computer and a sensor; s2, switching the signal conditioning module to a standby state; the signal conditioning module carries out self-inspection on the measurement channel until the baseline is normal; zero drift measurement, noise evaluation and path self-inspection are carried out; s3, switching the signal conditioning module to a standard state; the signal conditioning module is used for calibrating and switching the measurement channel, and judging: calibrating the gain, linearity and zero offset of the signal conditioning module; s4, switching to a measurement state; the signal conditioning module continuously collects data until the test task is completed; and S5, carrying out regular calibration and regular self-inspection on the signal conditioning module.

This invention relates to engine testing equipment, specifically to a gas flow guiding device for a horizontal engine test stand. To address the shortcomings of existing engine test stand gas flow guiding devices that cannot simultaneously meet the requirements of ground testing and high-performance testing, the gas flow guiding device for a horizontal engine test stand of this invention includes a gas flow guiding cylinder, a cooling unit, and a mounting bracket disposed below the gas flow guiding cylinder. The gas flow guiding cylinder includes a horizontal section and an inclined section connected in sequence, and the horizontal and inclined sections are detachably connected. The cooling unit delivers cooling water to multiple spray pipes disposed on the inner wall of the gas flow guiding cylinder, forming a protective water film through the spray pipes, and supplies water to a cooling water tank at the bottom of the inclined section, where water is sprayed onto the upper surface of the cooling water tank to cool the gas.

Method for aging an exhaust aftertreatment device (54, 56) for a motor vehicle by means of an engine test bench test in which an internal combustion engine (10), which has an intake tract (12) through which air flows, a combustion chamber (20) and an exhaust tract (22) through which exhaust gas from the internal combustion engine (10) flows, in which the exhaust aftertreatment device (54, 56) is arranged, is operated in several test cycles (92), each of which has several different test cycle phases (94 to 106), wherein in the respective test cycle (92) combustion processes take place at least temporarily in the combustion chamber (20) in which a fuel-air mixture with a combustion air ratio of less than 1 is burned, and via an air supply device (74, 76) which is fluidically connected to the exhaust tract (22) at an inlet point (78, 80) arranged upstream of the exhaust aftertreatment device (54, 56). is,Air is introduced into the exhaust tract (22), wherein the exhaust gas acting on the exhaust aftertreatment device (54, 56) has an exhaust gas composition resulting from the combustion of the fuel-air mixture in the combustion chamber (20) and the introduction of air into the exhaust tract (22) by means of the air supply device (74, 76), which corresponds to an exhaust gas composition resulting from the combustion of a stoichiometric fuel-air mixture.

The utility model discloses an unmanned aerial vehicle engine test bed, which comprises a power test bed frame, steel channel beams are arranged at the front and the back of the lower end of the power test bed frame, trundles are arranged on two sides of the lower end of each steel channel beam, and lifting mechanisms are arranged at two ends of each steel channel beam. Compared with the prior art, the test bed has the advantages that the test bed is high in bearing capacity and adaptive capacity, meets test requirements of unmanned aerial vehicle engines with blades within 100 inches, provides comprehensive and accurate data support for research, development and production, is convenient to move and fix, improves use flexibility and convenience of the test bed, reduces site arrangement cost, is stable in structure and supporting system, and is suitable for popularization and application. Testing safety and stability are guaranteed, testing errors and hidden dangers are reduced, accurate data are provided for most unmanned aerial vehicle engine testing, performance optimization is facilitated, the engine installation process is simplified, testing efficiency is improved, the bottom space is flexible, various requirements are met, and applicability is enhanced.

This invention discloses an engine test stand and a multi-engine testing method based on flexible switching, solving the technical problems of long switching cycles and high switching costs caused by changing the moving frame during engine test stand switching. The engine test stand includes piping fixtures, various transition fixtures, and pipeline transition pipes. The transition frame includes an upper transition frame, or an upper transition frame and a lower transition frame. The upper end of the upper transition frame is connected to a fixed frame, and the upper transition part of the transition frame is connected to the lower end of the lower transition frame, or to the lower end of the upper transition frame. The lower transition part of the transition frame carries a pipeline docking flange. The upper end of each transition fixture is used to adapt to the lower transition part of the transition frame, and the lower end is adapted to the upper end of the frame of one type of engine. The piping fixture is used for piping the engine's inlet pipeline in the preparation room, including a connecting ring plate and a piping docking flange. Each type of pipeline transition pipe is connected at one end to the engine's inlet pipeline and at the other end to the pipeline docking flange.

This invention relates to the field of engine testing system technology and discloses an integrated command system for an engine test bench, comprising: a time synchronization unit and a data video processing unit. The time synchronization unit is networked with the process measurement system and camera system of the engine test bench via a network switch. The first network port of the data video processing unit is connected to the process measurement system, and the second network port of the data video processing unit is connected to the camera system via the network switch. By setting up the time synchronization unit and the data video processing unit, the time synchronization unit provides a unified absolute time reference for the process measurement system and the camera system. The data video processing unit adopts a dual-port independent connection design, receiving measurement parameters and video streams in real time, and performing precise matching according to timestamps to automatically generate a fused image integrating parameters and video. This eliminates the need for test personnel to switch between multiple screens for observation, significantly improving test monitoring efficiency and operational convenience.

The invention discloses a one-key starting method for an aero-engine test bed, and belongs to the field of ground table control, and the method comprises the steps: collecting target parameters controlled in the historical starting process of the aero-engine test bed, generating a sequence data set, and calculating the coupling degree; constructing a starting target optimization function; the maximum value and the minimum value of the target parameters in different starting stages are screened from the sequence data set, an optimized value interval is obtained, and the value of the optimal target parameter is output; the deviation of the target parameters is calculated, and the PID controller is used for outputting the adjusting quantities of different starting stages; and taking the optimized sequence data set of the target parameters as input target parameters of the aero-engine test bed in different starting stages, and dynamically adjusting the input target parameters based on the adjusting quantity to realize one-key starting of the aero-engine test bed. According to the method, real one-key starting of the aero-engine test bed can be realized, the stability fluctuation and the fault occurrence rate in the starting process are reduced, and the starting efficiency and stability of the ground table are remarkably improved.

This application discloses a spatial flow field display method and system based on a 3D engine particle system, belonging to the field of spatial flow field display. The method includes: acquiring raw flow field data from a turboshaft engine test stand, preprocessing and standardizing it to construct a database that can be efficiently read by a 3D engine; in the 3D scene construction stage, performing polygon simplification and topology optimization on the physical model in the flow field to ensure that the engine can maintain high-performance operation while maintaining visual effects; and establishing a mapping mechanism of spatial coordinates-particle trajectory-particle dynamic binding, enabling abstract flow field data to accurately drive the motion trajectory of each particle in the particle system, achieving a precise correspondence between data and visual effects. Through frame update scripts, this application allows the particle system to respond in real time to data changes in the database, dynamically adjusting its motion state and vividly displaying the instantaneous characteristics of the flow field, providing a powerful and convenient interactive tool for flow field analysis.

The invention belongs to the technical field of aero-engines, and particularly relates to a suspension type engine test bed force measuring system center loading calibration device which comprises a center loading support (7), a connecting pull rod (5), a simulation engine (3), a hydraulic loading device (6), a movable frame (2), a static frame (1) and a supporting platform (4). During use, according to positive and negative thrust calibration requirements, the calibration device is installed in front of and behind a test run rack, standard load is applied in a pulling mode, and the pull rod is located at the center height of a simulation engine.

The application belongs to the technical field of aircraft structure design, and particularly relates to an engine test stand nacelle middle section structure. The engine test stand nacelle middle section structure comprises an internal frame, one end of the internal frame is connected with an air inlet duct, and the other end is connected with a test stand through a stand connecting piece; a cabin door is installed on the internal frame; and an external skin is wrapped outside the internal frame. The engine test stand nacelle middle section structure adopts a connecting piece to connect the nacelle middle section structure on the engine test stand, keeps the connection form of the existing components unchanged, meets the requirements of structure separation design and shape continuity with the air inlet duct, has a simple structure, is easy to process, and has strength and rigidity meeting actual requirements, so that the needs of engine test can be better met.

The present application relates to a kind of pulse jet device for simulating surge condition of micro turbojet engine, jet unit and bleed air unit are all installed on test bench, and the environment simulation under the surge condition of micro turbojet engine test is realized by joint action;The bleed air unit uses external fan to supply stable high pressure airflow to jet unit by bleed air pipeline;The jet unit is located in gas collection cavity, and the phase of pulsating jet in subsection gas collection cavity is adjusted by adjusting pulsating jet angle by hydraulic unit and servo valve, and the simulation of engine surge condition is realized by the joint action of the two. The present application can realize the change of pulsating jet by changing the direction and phase of jet on the basis of micro turbojet engine test bench, and the simulation of micro turbojet engine surge condition caused by different influencing factors can be completed.

This application discloses a digital modeling method and apparatus for a turboshaft engine test bench fuel system, belonging to the field of aero-engine fuel system technology. The method includes: establishing a physical digital model of the test bench fuel system based on its structural composition and dividing its operating modes; measuring and processing input and output parameters for use in the physical digital model; establishing a mechanism model based on the physical digital model according to the physical formulas of the input and output parameters, and optimizing the mechanism model based on historical data collected on key characteristic relationships; constructing a simulation model of the fuel system using a hybrid C++ and Simulink programming approach based on the physical digital model and the optimized mechanism model; and performing real-time monitoring and processing of the measurement data, integrating the test bench physical mechanism model with the measurement data to compensate for the insufficient accuracy caused by simplified assumptions in traditional mechanism models, significantly improving modeling and simulation speed without sacrificing accuracy.

The invention discloses a liquid engine test bed valve fault monitoring method and system, and belongs to the technical field of liquid engine test bed valve monitoring, and the method comprises the following steps: collecting and processing complete data of a valve in all modes in previous test run, including a normal state and various fault cases, establishing quantitative correlation models of valve performance parameters, operation modes and environment variables, concluding safe and feasible parameter adjustment boundaries and correlation valve coordination strategies in different fault modes, and storing the models and the strategies into a decision knowledge base; through the combination of the steps, accurate judgment, layered compensation and early warning of the valve fault are achieved, the intelligence and precision level of fault monitoring of the test bed valve is improved, fault misjudgment is reduced, test bed safety is guaranteed, and then intelligent fault monitoring and risk prevention and control of the whole process of the liquid engine test bed valve are achieved.

The utility model discloses an exhaust system of an engine test bed, which relates to the technical field of exhaust, and comprises a wall-passing air duct, a spraying air duct is mounted on one side of the wall-passing air duct, an exhaust air duct is mounted on one side of the spraying air duct, an inner cylinder is movably mounted on one side of the exhaust air duct, and an outer cylinder is mounted on the other side of the exhaust air duct. An adapter elbow is arranged at the upper end of the inner cylinder, a silencer is arranged at one end of the adapter elbow, a silencing pipe is installed on the upper side of the silencer, a tail end silencing elbow is installed at the upper end of the silencing pipe, an annular connecting pipe is installed on the spraying air duct, one side of the annular connecting pipe is communicated with a water inlet main pipe, a branch pipe is connected to the annular connecting pipe, and the branch pipe is connected with a water outlet pipe. The branch pipe extends into the spraying air duct, the spraying head is fixedly installed at the end, extending into the spraying air duct, of the branch pipe, through the arrangement of the silencer and the silencing pipe, the noise energy is better reduced, after airflow passes through a narrow space, the friction and expansion compression process is generated, and the sound transmission energy is effectively reduced.

This invention provides an engine test bench tank pressure boosting and depressurization system, comprising: a nitrogen source, a pressure regulating and distribution plate, a safety boosting module, a gas distribution control module, an airtightness module, a liquid oxygen / liquid methane tank, and an exhaust gas module. The nitrogen source is connected to the pressure regulating and distribution plate via a gas delivery pipeline from a storage tank for gas distribution and pressure regulation. The pressure regulating and distribution plate is sequentially connected to the safety boosting module, the gas distribution control module, and the liquid oxygen / liquid methane tank along the gas delivery direction via a nitrogen boosting pipeline, achieving boosting and gas distribution. The exhaust gas module is connected to the liquid oxygen / liquid methane tank for the safe discharge of gas from the tank. Before testing, the system can perform airtightness testing on the boosting pipeline using the airtightness module to ensure the accuracy of the boosting process control. The multiple boosting pipelines can be flexibly adjusted according to boosting requirements, ensuring the accuracy and stability of boosting.