33 results about "Supersonic nozzle" patented technology

The invention provides a micron-sized beryllium powder preparation method based on a gas atomization method, and particularly relates to the technical field of metal powder material preparation. The preparation method provided by the invention comprises the following steps: (1) melting raw materials, namely putting a high-purity beryllium ingot with the purity of more than or equal to 99.9% into a vacuum induction melting furnace, vacuumizing until the pressure is less than or equal to 1 * 10 <-3 > Pa, filling inert gas, heating to 1300-1400 DEG C, and keeping the temperature for 10-30 minutes until the superheat degree of beryllium liquid reaches 50-100 DEG C; (2) gas atomization treatment: spraying beryllium liquid through a supersonic nozzle, crushing liquid beryllium into fine liquid drops by using atomized gas, and solidifying the fine liquid drops into powder; (3) multiple layers of cyclone separators connected in series are arranged, parameters are adjusted step by step, and powder with different particle sizes is sequentially collected in a graded mode; and the powder with the target particle size is sealed and packaged after vacuum drying. According to the method, secondary screening can be effectively avoided, continuous production can be achieved, and the obtained micron-sized beryllium powder is controllable in particle size, high in sphericity degree and low in oxygen content.

A system for trapping a target condensable gas may include a supersonic condensation nozzle configured to receive a gas stream containing a target condensable gas component and accelerate the gas into a supersonic gas stream; at least one particle injector in the supersonic nozzle for injecting particles such that the particles are in the supersonic gas stream, whereby a target gas condensate is formed on a portion of the particles; an expansion device defining a channel having a lobe, causing the flow of particles containing the target gas condensate to generate an expansion wave to separate the flow into a first flow path in which a concentration of particles containing the target gas condensate increases and a second flow path in which a target condensable gas content of the gas decreases; and a diverter having at least a first channel, the diverter configured to collect the first flow path.

The application discloses a device and a method for testing a model with an attack angle and ablation shape, and the device comprises an arc heater, a mixing chamber, a supersonic nozzle, a test model, a variable attack angle device, a camera temperature measuring device and a support; the arc heater, the mixing chamber and the supersonic nozzle are sequentially connected; the variable attack angle device is installed on the support; the test model is installed on the variable attack angle device and located at the outlet end of the supersonic nozzle; and the camera temperature measuring device is arranged at a position for shooting the test model. The application aims to meet the simulation requirement of the test of the model with the attack angle and the ablation shape.

The invention belongs to the field of transsupersonic wind tunnel design, and discloses a two-dimensional flexible nozzle design method for a variable outlet section of a transsupersonic wind tunnel. The design method comprises determining the length of a model area; determining the aerodynamic theory outlet section position of the transonic nozzle; determining the minimum distance between the aerodynamic theory outlet section of the supersonic nozzle and the aerodynamic theory outlet section of the transonic nozzle; determining the aerodynamic theoretical outlet section position of the supersonic nozzle; determining the aerodynamic theoretical outlet section height of the supersonic nozzle; and determining the expanding angle. According to the design method of the two-dimensional flexible spray pipe for the variable outlet section of the transsupersonic wind tunnel, the problem that shock waves generated by the connection order difference or the gap of the spray pipe section and the supersonic test section interfere with a flow field is solved fundamentally, and the uniformity index of the flow field in the full-speed domain range of the transsupersonic wind tunnel is improved; the supersonic flow field quality is improved and kept stable for a long time, the test data quality is improved, and the method has engineering practical value.

The invention relates to an electric automobile heat pump heat management system based on an adjustable supersonic speed two-phase expander. The electric automobile heat pump heat management system comprises a heat pump heat management unit, a power battery heat management unit and a motor electric control heat management unit which are mutually coupled. The heat pump heat management unit comprises an adopted expander which is an adjustable supersonic speed two-phase expander and comprises a direct-current servo electric cylinder, a motor push rod shaft, an inlet pipe section, an adjustable swirl vane flow guide cone, a supersonic speed spray pipe, a cold energy recovery module, a liquid discharge pipe section and a diffuser. Wherein the motor push rod shaft can axially extend or retract into the direct-current servo electric cylinder body according to a control signal so as to drive the adjustable swirl vane flow guide cone to axially move, so that the area of the cone extending into the throat part is changed, and continuous adjustment of the flow area of the throat part of the adjustable supersonic speed two-phase expander is realized. The heat management system for the heat pump of the electric automobile not only is beneficial to improving the heating performance of the transcritical CO2 heat pump in a low-temperature environment, but also can realize efficient control of the exhaust pressure of the compressor.

The application provides a gas mass flow servo control device and a control method, which comprises a gas collecting pipe, an inlet electromagnetic valve group, an exhaust electromagnetic valve group, a pressure regulating valve and a regulator; the gas collecting pipe is sealedly connected with the inlet electromagnetic valve group, the exhaust electromagnetic valve group and the pressure regulating valve to provide a gas storage space with stable gas pressure; supersonic nozzles in the inlet electromagnetic valve group and the exhaust electromagnetic valve group are installed on the two sides of the gas collecting pipe in a split manner, and the on-off states are opposite, so that the required gas mass flow of a gas using device is provided while the gas pressure in the gas collecting pipe is kept stable; the regulator determines the current gas mass flow, the theoretical pressure of the gas collecting pipe at the next moment and the on-off combination of all supersonic nozzles in the inlet and exhaust electromagnetic valve groups, and drives the actuator to act. The application overcomes the problems of discontinuous data, large overshoot, long response time and large steady-state error during the regulation of the gas mass flow, and has the characteristics of simple structure, high automation and intelligence and good system stability.

The application discloses a laminar flow supersonic nozzle throat vicinity profile curve aerodynamic design method, relates to the field of supersonic equipment aerodynamic design, and comprises the following steps: giving a design nozzle initial design condition; determining nozzle key point coordinates; determining an initial section curve; determining a subsonic contraction curve; determining a boundary layer bleed slot boundary layer bleed slot lip curve; and giving throat vicinity profile curve coordinates. The method can meet the requirements of a model supersonic boundary layer natural transition test on a laminar flow supersonic nozzle, reduces the difficulty of laminar flow supersonic nozzle throat vicinity profile curve aerodynamic design and verification, and improves the design quality.

A burner comprises a primary nozzle for injecting an oxygen-rich gas. The primary nozzle is designed as a supersonic nozzle. A coaxial nozzle having an annular outlet opening is provided for injecting a fuel gas. The coaxial nozzle is designed as a subsonic nozzle and is coaxial to the primary nozzle. The primary nozzle has a convergent portion and a divergent portion, which adjoin each other at a radius of the narrowest cross-section. The annular outlet opening is located at an end face of the burner. The fuel gas, in the form of hydrogen or a mixture of hydrogen and a hydrocarbon-containing gas, is injected at a fixed inlet pressure and a fixed inlet volumetric flow rate, with respect to a planned thermal power of the burner. In contrast, the inlet pressure and the inlet volumetric flow rate of the oxygen-rich gas are varied according to the application.

The utility model relates to the field of nozzles, in particular to a supersonic nozzle for underground coal gasification, which comprises a nozzle component and a slag scraping component movably connected onto the nozzle component. The nozzle assembly comprises a nozzle shell movably connected to the slag scraping assembly, a sealing groove formed in the outer surface of the nozzle shell, a second compression section, an expansion section, a narrow throat opening formed in one end of the expansion section and a nozzle outlet formed in the other end of the expansion section, wherein the second compression section and the expansion section are connected to the nozzle shell. The threaded pipe is connected to the nozzle shell, the first compression section is connected to the threaded pipe, and the expansion section is connected with the second compression section. The first compression section, the second compression section and the expansion section are of a double-section compression-expansion structure, so that the gas flow speed is further increased to supersonic speed after the throat reaches the sound speed, the mixing efficiency of a gasifying agent and a coal seam is improved, and the gas tightness in an underground high-pressure environment is ensured through threads on the threaded pipe and a sealing groove.

The system for capturing target condensed gas includes a supersonic condensation nozzle configured to receive a gas flow having a predetermined target condensed gas content and for accelerating the gas into a supersonic gas flow; at least one particle injection device within the supersonic nozzle for injecting particles into the supersonic gas flow, whereby target gas condensate is formed on some of the particles; an expansion device that generates an expansion wave in the flow of particles containing the target gas condensate, defining a conduit with a convex corner that separates the flow into a first flow path having particles with a high concentration of target gas condensate and a second flow path of gas with a lower target condensed gas content; and a flow divider having at least the first conduit, the flow divider configured to receive the first flow path.

The invention discloses a supersonic thrust vectoring nozzle device and method for pulse surface arc plasma excitation regulation and control, and belongs to the field of aerospace flow control. The device comprises a power supply module, an electrode assembly and a spray pipe base body, wherein the power supply module comprises a high-voltage pulse power supply, a parameterized controller and an external accessory; the electrode assembly is formed by connecting a plurality of groups of electrodes, the electrode assembly is axially distributed and embedded into the nozzle base body along the inner wall of the nozzle, and the surfaces of the electrodes are polished according to the molded surface of the nozzle; the electrode assembly is excited by the high-voltage pulse power supply to break down gas to generate explosive waves and plasma clusters, and the explosive waves and the plasma clusters disturb a flow field; and the parameterized controller realizes quantitative flow control of the supersonic nozzle by adjusting the discharge voltage, the discharge frequency and the discharge pulse width of the high-voltage pulse power supply. Vector control of the supersonic nozzle without mechanical parts is achieved through the mapping relation between discharge parameters and flow field characteristics, and the supersonic nozzle has the advantages of being simple in structure and fast in response.

The invention discloses an aerodynamic design method for a molded surface curve near a throat of a laminar flow supersonic nozzle, and relates to the field of aerodynamic design of supersonic equipment. Determining key point coordinates of the spray pipe; determining an initial section curve; determining a subsonic velocity shrinkage curve; determining a boundary layer exhaust seam lip curve of the boundary layer exhaust seam; according to the method, the requirement of a model supersonic boundary layer natural transition test on the laminar flow supersonic spray pipe can be met, the aerodynamic design and verification difficulty of the profile curve near the throat of the laminar flow supersonic spray pipe is reduced, and the design quality is improved.

The present application provides a kind of pressure exchange ejector, including ejector shell, adjustable supersonic nozzle driven by first electric push rod is equipped in the ejector shell, and adjustable cone driven by second electric push rod is equipped in the ejector shell, the adjustable cone is arranged in adjustable supersonic nozzle relative to the end of second electric push rod and is slidably connected with adjustable supersonic nozzle, the mixing chamber entrance and the mixing chamber outlet are further equipped in the ejector shell, the first conical part is set on adjustable supersonic nozzle corresponding to the mixing chamber entrance, and the second conical part is set on adjustable cone corresponding to the mixing chamber outlet;The present application has the following beneficial effects: the present application can adjust the position of adjustable supersonic nozzle and adjustable cone in real time to further adjust key area, maintain the original pressure recovery capability while maintaining a higher entrainment coefficient, i.e. entrainment coefficient is adaptive, can solve the problem of low performance and efficiency of ejector under non-design condition.

The invention discloses a large combustion wind tunnel for test, and relates to the technical field of wind tunnel test, and the large combustion wind tunnel comprises a heater, the left side of the heater is provided with a transition section, the left side of the transition section is provided with a supersonic nozzle, the left side of the supersonic nozzle is provided with a test section body, and the left side of the test section body is provided with a super-expansion section. An ejector is arranged on the left side wall of the super-expansion section, a silencing tower is arranged on the left side of the ejector, a first connecting pipe is arranged between the ejector and the silencing tower, and a test section inlet is formed in the right side wall of the test section body. The high-frequency dynamic pressure sensor, the hot-wire anemometer, the temperature measurement sensor, the high-speed camera and the thermal infrared imager are matched with one another, so that multi-dimensional real-time monitoring of flow field parameters and flame behaviors in a test section is realized, and accurate data support is provided for active control of a flow field.

The invention relates to the technical field of supersonic air inlet channel starting and active flow control, aims to solve the problems of air inlet channel flow separation, shock wave boundary layer interference and starting delay of an existing scramjet engine, and provides a miniature supersonic spray pipe array device for enhancing air inlet channel starting and an engine. The miniature supersonic spray pipe array device comprises a rotating mechanism, and a plurality of spray pipes are mounted on the rotating mechanism and arranged at intervals; an air flow channel in each spray pipe is an acceleration flow channel, and an air flow channel between every two adjacent spray pipes is a speed reduction flow channel; the acceleration flow channel is sequentially divided into an acceleration flow channel inlet section, a middle contraction section and an acceleration flow channel outlet section in the gas flowing direction, and the section size of the middle contraction section is smaller than the section size of the acceleration flow channel inlet section and the section size of the acceleration flow channel outlet section; according to the invention, the problems of shock wave boundary layer interference, flow separation and starting delay of the lip of the air inlet channel under the condition of high Mach number are effectively solved.

This invention relates to the field of supersonic inlet start-up and active flow control technology, aiming to solve the problems of inlet flow separation, shock wave boundary layer interference, and start-up lag in existing scramjet engines. It provides a miniature supersonic nozzle array device and engine for enhancing inlet start-up. The miniature supersonic nozzle array device includes a rotating mechanism on which multiple nozzles are mounted, arranged at intervals. The airflow channel inside each nozzle is an acceleration channel, and the airflow channel between two adjacent nozzles is a deceleration channel. The acceleration channel is sequentially divided into an acceleration channel inlet section, a central contraction section, and an acceleration channel outlet section along the gas flow direction. The cross-sectional size of the central contraction section is smaller than that of the acceleration channel inlet section and the acceleration channel outlet section. This invention effectively solves the problems of shock wave boundary layer interference, flow separation, and start-up lag at the inlet lip under high Mach number conditions.

The application discloses a built-in multi-pipe supersonic condensation-cyclone-coalescence filter, which comprises a shell, a cyclone pre-separation module, a supersonic nozzle steam condensation module, a multi-stage guide vane type mist cyclone separation module and a coalescence filter core filter module are sequentially arranged in the shell from bottom to top. The filter can not only separate free liquid droplets carried in natural gas, but also deeply remove lubricating oil steam, hydrocarbons and water vapor contained in the natural gas through phase change condensation. The filter has the characteristics of large operation flexibility and high separation efficiency.

The invention relates to the technical field of supersonic nozzles, and provides an aperture-adjustable supersonic nozzle which comprises a nozzle flow channel formed by sequentially communicating a compression section, a throat section and an expansion section. The throat section is formed by an elastic metal diaphragm with a hole in the center, and the center hole of the elastic metal diaphragm forms the minimum flow cross section of the nozzle flow channel; an annular actuator is arranged around the periphery of the elastic metal diaphragm, and the annular actuator is configured to generate acting force in the radial direction of the center hole in an excitation state, so that the elastic metal diaphragm is elastically deformed, and the size of the hole diameter of the center hole is continuously adjusted. According to the invention, the annular actuator is adopted to realize high-precision, linear and stepless regulation of the aperture of the throat part of the supersonic nozzle in a preset range, so that the mass number and the distribution of gas clusters are dynamically regulated and controlled.

The invention provides an efficient fruit and vegetable powder preparation system integrating multi-stage cyclone classification and superfine grinding, belongs to the technical field of food processing, and aims to solve the problems of low classification precision, high energy consumption, large nutrient loss and insufficient material adaptability in the prior art. The system comprises a crushing and grading box and a crushing and grading system, a primary grinding cavity and a superfine grinding cavity are formed in the crushing and grading box and communicate with each other through a conical communicating channel, and automatic circulation of particles which do not reach the standard is achieved in cooperation with a backflow channel and an inclined face. The crushing and grading system comprises a multi-stage grading wheel driven by a high-efficiency motor, a grinding disc and wear-resistant grinding teeth, and seamless connection of primary grinding and superfine crushing is realized in combination with high-speed airflow generated by a supersonic nozzle. The grinding discs are connected through low-friction ceramic balls, so that energy consumption and abrasion are reduced; and the durability of the equipment is enhanced by the detachable grinding block and the wear-resistant ceramic coating.

A space propulsion system can serve miniaturised satellites, but can be scaled easily, and includes: a combustion chamber implemented by a cylindrical container having cylindrical walls, a first end provided with at least an injection duct for a combustion agent, a fuel and / or a mixture thereof, for the injection according to a direction tangential to the cylindrical walls so as to induce a helical combustion path in the combustion chamber, a possible additional perpendicular injection duct for a fuel or a combustion agent, and an opposite end provided with a discharge duct arranged according to a direction tangential to the cylindrical walls so as to receive and direct the helical path, wherein the cylindrical walls in case have a deposition of catalytic material inside thereof, for accelerating the combustion reaction; and a supersonic nozzle, connected to the discharge duct for discharging the combustion products in the combustion chamber.

The present application belongs to the field of transonic wind tunnel design, and discloses a design method of a binary flexible nozzle for a variable exit section of a transonic wind tunnel. The design method comprises determining a model area length; determining a position of a transonic nozzle aerodynamic theory exit section; determining a minimum distance between the transonic nozzle aerodynamic theory exit section and a supersonic nozzle aerodynamic theory exit section; determining a position of the supersonic nozzle aerodynamic theory exit section; determining a height of the supersonic nozzle aerodynamic theory exit section; and determining an expansion angle. The design method of the binary flexible nozzle for the variable exit section of the transonic wind tunnel solves the problem of shock wave interference with the flow field caused by the connection step or gap between the nozzle section and the supersonic test section, improves the uniformity index of the flow field in the full speed range of the transonic wind tunnel, improves the quality of the supersonic flow field and keeps it stable for a long time, improves the quality of the test data, and has engineering practical value.

The invention belongs to the technical field of crushing devices and methods, and particularly relates to a PEEK superfine crushing system and method.The PEEK superfine crushing system comprises a subzero treatment box, a target jet mill, a crushing cavity, a grading impeller, a tungsten carbide target disc and a supersonic nozzle, and the grading impeller is coaxially arranged on the central axis of the crushing cavity; one end of the target jet mill is connected with a cloth bag type particle collector, and the other end of the target jet mill is connected with a low-temperature air source unit; the crushing method of the PEEK superfine crushing system comprises the following steps: S1, material pretreatment; s2, primary crushing; s3, cyclic crushing; s4, collecting a finished product; according to the invention, the crushing stability and the crushing precision of the PEEK material can be improved, and the preparation period of the PEEK superfine powder is shortened.

The application discloses a kind of for flexible wall nozzle profile static debugging method, it is in to solve the existing method in the process of flexible wall supersonic nozzle profile static debugging, nozzle profile iteration correction number is more, and the problem of low work efficiency.It includes the following steps: (1) according to the nozzle profile static debugging method of conventional static debugging profile corresponding to the first Mach number is debugged, until the deviation of measured profile and theoretical profile meets the requirements;(2) the nozzle profile corresponding to the second Mach number and the nozzle profile corresponding to the first Mach number are obtained on each actuator control variable difference, etc.This application obtains the nozzle static debugging profile corresponding to the first Mach number, and regards it as reference profile, with the difference between the adjacent Mach number theoretical profile or the last nozzle static debugging profile as adjustment amount to control actuator adjustment, and the obtained nozzle profile is used as the initial profile of the nozzle profile static debugging of the adjacent Mach number.

The present invention discloses a supersonic cyclone condensation separation device with a nozzle having an internal corrugated structure, belonging to the technical field of gas-liquid two-phase flow separation. The supersonic cyclone condensation separation device comprises: a cyclone generating section, a supersonic nozzle section, a supersonic deceleration section, and a subsonic deceleration diffuser section, all arranged coaxially and fixedly; axial flow guide vanes, a condensate collection chamber, and a central guide cone; axial flow guide vanes fixedly assembled with the central guide cone within the cyclone generating section; internal corrugations arranged along the axis of the inner wall surface of the supersonic nozzle section, with the inner diameter of the internal corrugations at the outlet section being equal to the inner diameter of the supersonic deceleration section; and an oblique inlet provided at the entrance of the condensate collection chamber, with the internal corrugations of the outlet section of the supersonic nozzle section communicating with the oblique inlet, so that condensate from the supersonic nozzle section enters the condensate collection chamber through the oblique inlet. This improves the reliability and adaptability of the separator to working conditions.

The invention relates to an adjustable supersonic speed two-phase expander which comprises a direct-current servo electric cylinder, a motor push rod shaft, an inlet pipe section, an adjustable rotational flow blade flow guide cone, a supersonic speed spray pipe, a cold energy recovery module, a liquid discharge pipe section and a diffuser. The motor push rod shaft can axially extend or retract into the direct-current servo electric cylinder body according to the control signal so as to drive the adjustable swirl vane flow guide cone to axially move, so that the area of the cone extending into the throat part is changed, and continuous adjustment of the flow area of the throat part of the adjustable supersonic speed two-phase expander is realized; and the expansion loss is reduced, and the heating performance of the transcritical CO2 heat pump in the low-temperature environment is improved. The invention further provides a cold and heat combined supply CO2 heat pump system adopting the adjustable supersonic speed two-phase expander and a cold energy recycling CERU, and more efficient and energy-saving hot water supply and indoor temperature adjustment in a small space place can be achieved.

The present application relates to a kind of electric vehicle heat pump thermal management systems based on adjustable supersonic two-phase expander, including mutually coupled heat pump thermal management unit, power battery thermal management unit and motor electric control thermal management unit.Heat pump thermal management unit includes the expander for adjustable supersonic two-phase expander, including direct current servo motor cylinder, motor push rod shaft, inlet pipe section, adjustable cyclone vane flow cone, supersonic nozzle, cold energy recovery module, drain pipe section and diffuser, wherein: motor push rod shaft can be according to control signal axial elongation or retract within direct current servo motor cylinder body, to drive adjustable cyclone vane flow cone axial movement, so that the cone area of throat changes, realizes the continuous regulation of adjustable supersonic two-phase expander throat flow area.Electric vehicle heat pump thermal management system of the present application not only helps to improve the transcritical CO2 heat pump heating performance under low temperature environment, and also can realize the efficient control of compressor exhaust pressure.

The utility model relates to the field of nozzles, in particular to a zirconia ceramic supersonic nozzle structure for underground coal gasification, which comprises a nozzle component, fixing threads connected onto the nozzle component, a sealing component movably connected inside the nozzle component and two sealing grooves arranged on the outer surface of the nozzle component. The nozzle assembly comprises a buffer body movably connected to the sealing assembly and a first compression section connected to the buffer body. The maintenance cost is reduced by arranging the sealing assembly with the adjustable diameter, meanwhile, the sealing ring and the sealing structure are matched with each other to conduct isolation sealing, so that the airtightness of the whole nozzle structure is improved, gas leakage is avoided, the sealing structure is rapidly disassembled through the arrangement of the pressing nut, and the sealing structure is convenient to disassemble. The use convenience of the whole nozzle structure is further improved, and the air tightness of the device is ensured through the arrangement of the fixing threads and the two sealing grooves, so that it is ensured that air cannot leak from the surface of the buffer body.

The invention belongs to the technical field of oil sludge treatment, and discloses a supersonic speed hot air jet coupling hot flue gas oil sludge drying device which is structurally characterized in that a motor is connected with a speed reducer, the speed reducer is connected with the front end of a rotating shaft, the motor drives the rotating shaft to rotate after being electrified, and the speed of the rotating shaft is adjusted through the speed reducer; the barrel is transversely arranged, the rear end of the rotating shaft penetrates through the barrel, multiple rows of efficient stirring rake teeth are uniformly arranged on the rotating shaft in the barrel in the radial direction, and shoveling plate type rake blades are arranged at the ends of the efficient stirring rake teeth; a smoke outlet is formed in the top of the front end of the barrel; a material outlet is formed in the bottom; a material inlet and a compressed air inlet are formed in the top of the rear end of the barrel, a smoke inlet is formed in the side portion of the barrel, and a supersonic nozzle is arranged on the inner side of the material inlet and accelerates airflow from subsonic velocity to supersonic velocity. The supersonic spraying technology is applied to oil sludge treatment research, a novel treatment thought is provided for waste oil sludge, and development of the multi-industry combined treatment and utilization technology of petroleum industry waste is promoted.

The application relates to the technical field of supersonic nozzles, and provides a supersonic nozzle with adjustable aperture, which comprises a nozzle flow channel formed by a compression section, a throat section and an expansion section in sequence; the throat section is formed by a center-aperture elastic metal diaphragm, the center aperture of the elastic metal diaphragm constitutes the minimum flow passage section of the nozzle flow channel; an annular actuator is arranged around the outer periphery of the elastic metal diaphragm, the annular actuator is configured to generate a radial force along the center aperture in an excited state, the elastic metal diaphragm is elastically deformed, and the aperture size of the center aperture is continuously adjusted. The annular actuator is adopted to realize high-precision, linear and stepless adjustment of the throat aperture of the supersonic nozzle within a preset range, so that the mass number and distribution of gas clusters are dynamically controlled.

The invention relates to the technical field of high-speed particle impact testing, and discloses a device and method for accelerating micro-nano particles to supersonic speed for impact testing, the device comprises a high-pressure pump, a high-pressure guide pipe is installed in the water pumping end of the high-pressure pump in a penetrating manner, and a high-pressure calandria is installed in the water drainage end of the high-pressure pump in a penetrating manner; and a heating box pool is fixedly installed on one side of the high-pressure pump, heating pipe fittings are fixedly installed in the heating box pool, and a pressure pump is installed at the top of the heating box pool in a penetrating mode. The high-pressure guide pipe at the water pumping end of the high-pressure pump and the interior of the purification box are installed in a penetrating mode, then particles are subjected to secondary high-pressure acceleration through the high-pressure pump, then the particles are discharged into the supersonic spraying pipe through the high-pressure discharging pipe, and interference of liquid phase relative impact can be eliminated; the characteristics of high pressure and high flow can be achieved through high-pressure pumping, secondary acceleration can be conducted on particles in the evaporation process, the speed bottleneck of a traditional jet device can be broken through, and the particles are accelerated to 600 m / s or above.