298 results about "Supersonic speed" patented technology

The invention belongs to the technical field of gas turbine maintenance, and particularly relates to a solid-state repair method for a hot-end component of a gas turbine, which comprises the following steps: S1, acquiring damage information of the surface of a to-be-repaired matrix; s2, roughening treatment is conducted on a damaged area on the surface of the to-be-repaired base body, and electrochemical activation treatment is conducted on the roughened damaged area; s3, supersonic speed cold spraying treatment is conducted on the treated damaged area, and gradient materials are deposited on the damaged area layer by layer till a compact repairing layer is deposited on the surface of the base body; s4, selective laser remelting treatment is conducted on the compact repairing layer of the damaged area; s5, carrying out laser shock on the dense repair layer subjected to the remelting treatment; and S6, the base body subjected to laser shock treatment is machined till the standard geometric dimension of the base body is recovered. The method can solve the problems of large heat input, matrix damage, insufficient bonding strength and the like in the process of repairing the damaged area of the matrix in the traditional hot working technology.

The invention discloses an optimization design method for a control surface of a wide-speed-range large-attack-angle reusable carrier, and relates to optimization design of aerodynamic configuration of an aircraft. The method comprises the following steps: S1, setting a control surface aerodynamic configuration design variable range, and generating an initial sample library by adopting Latin hypercube sampling; s2, aerodynamic parameters are obtained through CFD simulation, and a Kriging proxy model is trained; s3, evaluating the precision of the proxy model by taking a U learning function as a criterion, and stopping adding points when the minimum U function value is smaller than a threshold value; s4, constructing an optimization model which takes maximization of the lift-drag ratio and the static stability margin under the hypersonic speed as a target and takes the condition that the aerodynamic parameters of the supersonic speed / subsonic speed are not lower than a reference value and the hinge moment as constraints; and S5, performing iterative optimization by adopting an improved multi-target particle swarm algorithm based on genetic algorithm crossover mutation operation, updating the proxy model after the optimal solution of each generation is subjected to CFD verification, and outputting an optimal solution set. The problem of wide-speed-range aerodynamic configuration contradictions is solved, and the comprehensive performance of the carrier is remarkably improved.

The partial or full dehydration of organic or inorganic matter containing water by induction of matter into a vacuum and processing matter through a specially designed acceleration channel is disclosed. The inducted matter accelerates in air from zero speed to sub-sonic speed to reach supersonic speed. As the material transitions the sound barrier, it is subject to acoustic shock waves and an instant negative pressure drop occurs. The sound waves disintegrate, disinfect the material and extract part or all moisture from any organic or inorganic material.

The invention provides low-temperature supersonic airflow collision ultramicro equipment, which belongs to the field of material crushing and processing, and comprises a feeding device, an airflow collision device, a closed-loop type circulation grading device, a material receiving device, a gas cooling device and a gas inlet device, and the gas inlet device is used for providing a high-pressure gas source for the equipment; the gas cooling device cools the high-pressure gas to a preset low temperature, and then the high-pressure gas is fed into the gas flow collision device after being subjected to pressure regulation through the gas feeding pipeline; the airflow collision device comprises a collision chamber and at least one pair of opposite nozzles, the horizontal distance between the paired nozzles can be adjusted, the air supply pipeline and the feeding pipeline are connected with the nozzles after being intersected, and high-pressure air is sprayed out through the nozzles to form supersonic jet flow to drive materials to collide with each other in the collision chamber. And the collided materials are subjected to closed-loop circulation classification and then enter a material receiving device, and large particles are subjected to circulation collision crushing again. The ultramicro equipment disclosed by the invention can be used for crushing various plant raw materials into 1-10 microns, and has a good application prospect.

The invention relates to the technical field of bag type dust removal, in particular to a supersonic speed injection pulse injection pressure control method and system, which are used for evaluating the effectiveness of single ash removal operation and optimizing the subsequent injection pressure, and the method comprises the following steps: when at least one injection unit of a bag type dust removal system executes injection operation, the injection pressure of at least one injection unit of the bag type dust removal system is controlled; a pressure monitoring device arranged on a blowing gas path of the blowing unit is used for collecting a pressure signal in the blowing gas path to obtain pressure waveform data, and the pressure waveform data represents the pressure change at the moment of blowing; extracting at least one preset dynamic characteristic parameter from the pressure waveform data, wherein the dynamic characteristic parameter reflects the blowing airflow state or the air permeability change of the filter bag; the problems that in the prior art, dust removal control is extensive, and fine evaluation and adjustment cannot be achieved are solved by collecting a pressure signal of a blowing gas path, extracting dynamic characteristic parameters, evaluating the effectiveness grade of dust removal, adjusting the blowing pressure accordingly and updating the mapping relation online at the same time.

The invention relates to the technical field of metal wire processing, and discloses a high-performance metal wire plastic coating process for aerospace engineering, which comprises the following steps: carrying out base material type selection on a metal wire, and carrying out surface treatment of precise cleaning, etching and depth gradient activation; a Ti-Cr alloy and graphene-copper composite transition layer is deposited through a magnetron sputtering technology, and a multi-layer coating structure is formed through electrostatic spraying of a base coating, a fluidized bed dipping function layer and high velocity oxy-fuel spraying of a nano composite coating in sequence; the molybdenum-gold composite sealing layer is prepared by adopting an electric arc spraying technology, and is subjected to vacuum ultraviolet curing enhancement, high-temperature gradient annealing, gradient sintering and vacuum curing treatment; and heat radiation on the surface of the coating is enhanced through laser-induced micro-nano structure regulation and silicon nitride film sputtering. Through collaborative optimization of base material treatment, coating construction, function strengthening and quality control, the interface bonding strength, the comprehensive performance and the environmental adaptability of the spaceflight metal wire coating are remarkably improved, and the service life of the spaceflight metal wire coating is remarkably prolonged.

The invention discloses an aerodynamic configuration structure of a precision guidance assembly and a design method, and belongs to the technical field of precision guidance, an assembly precursor adopts continuous three-section curve design: a supersonic speed section adopts a parabola profile, is provided with ribs on the surface, and is used for optimizing shock wave control under a supersonic speed working condition; the transonic speed section adopts a hyper-ellipsoid curved surface, ribs are arranged on the surface of the transonic speed section, and metamaterials are attached to the ribs and used for restraining transonic speed separation; the subsonic speed section adopts arc transition, and ribs are arranged on the surface and used for improving the lift force efficiency of the control surface; wherein the curvatures at the joints of the three sections of curves are continuous. According to the method, supersonic velocity-transonic velocity-subsonic velocity three-section collaborative design is realized, and meanwhile, a boundary layer is improved from a microscopic level by combining a collaborative drag reduction design of a microscopic rib and metamaterial technology, and the performance of a guidance assembly is optimized and improved.

The invention belongs to the technical field of turbine engine design, and particularly relates to a turbine interstage combustion chamber supersonic cruise engine and a control method thereof.The turbine interstage combustion chamber supersonic cruise engine comprises a fan adopting a FLADE fan; the gas compressor is arranged behind the fan; the main combustion chamber is arranged behind the gas compressor; the high-pressure turbine is arranged behind the main combustion chamber and is connected with the gas compressor through a high-pressure shaft; the mixing chamber is arranged behind the high-pressure turbine and is communicated with the fan through an outer duct; the interstage combustion chamber is arranged behind the mixing chamber; the low-pressure turbine is arranged behind the combustion chamber and is connected with the fan through a low-pressure shaft; the spraying pipe is arranged on the low-pressure turbine; and after the injection valve is arranged on the high-pressure turbine, the injection valve deflects to the inner runner surface of the outer duct when the injection valve is opened, and deflects to the outer runner surface of the outer duct when the injection valve is closed.

An airfoil for an aircraft having an airfoil geometry. The airfoil geometry includes an upper surface and a lower surface, the upper and lower surfaces are in accordance with Cartesian coordinate values of X and Y. The Cartesian coordinate values of X and Y are non-dimensional values from 0 to 1 convertible to dimensional values by multiplying the Cartesian coordinate values of X and Y by a chord length of the airfoil. The upper surface and the lower surface form an enclosed airfoil shape. The aircraft is a supersonic aircraft, and the airfoil has a thickness-to-chord ratio of about 10%.

The invention relates to the technical field of rocket engine simulation tests, in particular to a vertical high-altitude simulation test bed compatible with a ground test and a test method. Comprising a vacuum chamber which is provided with a ventilation assembly capable of being opened and closed; and the diffuser is communicated with the vacuum cabin and is vertically arranged at the tail end of the engine, and engine gas enters the diffuser. When a high-altitude simulation test is carried out, the long-nozzle engine is arranged in the vacuum cabin, and the openable and closable ventilation assembly is closed, so that the inner side of the vacuum cabin is isolated from the outside. Engine fuel gas enters the diffuser and is expanded in the diffuser to form supersonic airflow to suck the vacuum chamber, the fuel gas is injected to the injection expansion section under injection of the injection working medium, the fuel gas is mixed with the injection working medium airflow to continue to be pressurized in the supersonic speed state, and finally the fuel gas is exhausted from the injection expansion section when the pressure is higher than the atmospheric pressure. The air pressure in the vacuum chamber is lower than the atmospheric pressure, and high-altitude simulation test conditions are met.

The invention provides a wing-body fusion wide-speed-range aircraft layout design method based on consideration of an afterbody effect. The method comprises the following steps: firstly, generating a cone-guided waverider precursor of a wide-speed-range aircraft for supersonic flight; then, based on the basic airfoil profile, performing pneumatic optimization on the basic wing profile and the strake wing profile of the wide-speed-domain aircraft to obtain a multi-section wide-speed-domain waverider airfoil profile; then calculating the length of a waverider afterbody and designing a symmetry plane of the wide-speed-range aircraft; and finally, based on an osculating cone method and transonic speed strake wing constraints, obtaining three-dimensional layout parameters by using the waverider precursor parameters and the waverider afterbody length, and assembling the basic wing optimized airfoil profile, the strake wing optimized airfoil profile and the symmetry plane to generate the layout of the wide-speed-domain aircraft. According to the method, the cone-guided waverider generation method, the wide-speed-range airfoil optimization method and the osculating cone double-sweepback waverider generation method are coupled, and the aerodynamic design of the afterbody is considered, so that the aerodynamic performance of the wide-speed-range aircraft under the subsonic / transonic / supersonic speed is improved.

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a self-adaptive supersonic speed target drone fuel oil system and a control method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, an overflow valve, a pressurization oil tank, a fuel pump, an engine pump, a monitoring module and a control module. The body fuel tank comprises a main fuel tank and an auxiliary fuel tank which are arranged in a fuel tank in the middle of the target drone body and located in front of and behind the theoretical mass center of the target drone respectively. The pressurization oil tank is additionally arranged in the fuel oil cabin, fuel oil in the engine body oil tank enters the pressurization oil tank for pressure maintaining after being pressurized by the fuel oil pump, and then oil is supplied to the engine from the pressurization oil tank, so that stable oil supply to the engine is achieved by establishing a local pressure environment instead of a large pressure environment of the whole fuel oil cabin, and therefore when a fuel oil system works, the fuel oil can be stably supplied to the engine. The oil supply flow and pressure are controlled in a closed-loop mode in real time through the control system according to the engine state.

The invention relates to the technical field of metallurgical furnace charge conveying and control, and discloses a top-blown furnace multi-channel supersonic jet type feeding control method and system.The method comprises the steps that flow distribution in a nozzle is achieved through a piezoelectric ceramic high-speed valve installed at a pipeline inlet, and a nozzle servo motor is controlled at the top of a spray gun to adjust the spray angle of the spray gun; the feeding speed, pressure and temperature are monitored in real time through a pressure sensor and a flow sensor arranged in an inlet area of the pipeline and an infrared thermometer mounted at the top of the furnace; the carrier gas flow, the nozzle opening degree and the spraying angle are dynamically adjusted through control of the PLC executing mechanism, and collaborative optimization of the material flow vector, the flow field in the hearth and the heat and mass transfer process is achieved. The system comprises a spray gun, a piezoelectric ceramic high-speed valve, a flow sensor, an infrared thermometer, a nozzle control servo motor, a temperature measurement control small servo motor and a control room. The comprehensive operation efficiency of energy density distribution optimization, reaction efficiency improvement and energy consumption index reduction of the molten pool reactor is finally realized.

A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using anon-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members. For example it can be used to cool a computer chip, a skin of a hypersonic flying object, parabolic solar collector, turbine or engine blade, or any other heat source that requires high heat flux.

The invention relates to the technical field of thermal barrier coatings for gas turbines or aero-engines, and particularly discloses an ultra-thick and strong-bonding double-ceramic-layer thermal barrier coating and a preparation method thereof.The thermal barrier coating is composed of an MCrAlY bonding layer, a YSZ ceramic layer bottom layer and a high-entropy rare earth zirconate ceramic layer surface layer; the MCrAlY bonding layer is prepared through atmospheric plasma or hypersonic flame spraying, YSZ and high-entropy rare earth zirconate spherical powder serve as spraying raw materials, and the thermal barrier coating is prepared through an axial powder feeding high-energy plasma spraying system. The thermal barrier coating has the characteristics of super thickness (the coating thickness is 600-1200 microns), high bonding strength (gt; 19 MPa) and the like.

The invention discloses an anti-oxidation and anti-scouring heat prevention and insulation composite material, a preparation method and application, and belongs to the technical field of high-temperature thermal protection materials. According to the method, a two-step in-situ modification method is adopted, hydrolyzed organosilane reacts with phenolic resin to prepare silicon modified phenolic resin, then the silicon modified phenolic resin is bonded with an organoboron compound to obtain boron-silicon co-modified phenolic resin, a curing agent is added, then the boron-silicon co-modified phenolic resin is injected into a fiber reinforcement mold, and a finished product is obtained through a sol-gel reaction and normal-pressure drying. According to the invention, boron and silicon elements are embedded into phenolic aldehyde molecular chains through covalent bonds to form a boron-silicon-carbon hybrid network, a nano ceramic phase and a compact glassy protective layer are generated at high temperature, and the coating has excellent anti-scouring property, thermal stability and heat insulation property. The preparation process is simple and controllable, is suitable for large-scale production, can accurately regulate and control the performance, and is suitable for thermal protection parts of supersonic aircrafts.

The utility model belongs to a spraying device, and provides a supersonic spraying device, a non-invasive spraying device and a spraying instrument.The problems that spraying is not uniform and operation is inconvenient still exist in an existing instrument, and the supersonic spraying device, the non-invasive spraying device and the spraying instrument.The supersonic spraying device comprises a liquid section, a gas inlet section, a contraction section, a throat part and an expansion section, and the gas inlet section, the contraction section, the throat part and the expansion section are coaxially and sequentially connected; liquid enters from the liquid section, gas is accelerated through the contraction section, reaches the throat part and is continuously accelerated at the expansion section, the liquid entering from the liquid section is atomized under the action of the gas at the throat part, is brought into the expansion section and is finally sprayed out from the spraying opening along with continuous acceleration, and the uniform spraying effect is achieved. According to the supersonic jet device, the ratio of the axial length L1 to the axial length L2 is designed, the structure of the supersonic jet device is further optimized, and actual verification shows that under the optimized ratio, the jet force of the supersonic jet device is obviously improved, the particle size and the jet range of jetted liquid drops are better, and the flow speed of the liquid drops is more stable.

A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using a non-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members. For example it can be used to cool a computer chip, a skin of a hypersonic flying object, parabolic solar collector, turbine or engine blade, or any other heat source that requires high heat flux.

The invention discloses a thermal barrier coating with a double-bonding-layer structure and a preparation method thereof, and belongs to the field of thermal barrier coatings. According to the thermal barrier coating, nickel-based high-temperature alloy serves as a substrate, the thermal barrier coating sequentially comprises an MCrAlY lower bonding layer, a Cr2AlC upper bonding layer and an 8YSZ ceramic layer, the MCrAlY lower bonding layer and the Cr2AlC upper bonding layer are prepared through the high velocity oxy-fuel spraying technology, and the 8YSZ ceramic layer is prepared through the atmosphere plasma spraying technology. According to the thermal barrier coating system, through the synergistic effect of the oxidation resistance of the Cr2AlC upper bonding layer and the mutual diffusion inhibition characteristic of the MCrAlY lower bonding layer, the comprehensive performance of the thermal barrier coating is optimized, meanwhile, the anti-stripping capacity of the thermal barrier coating system is remarkably improved, and the thermal barrier coating system is suitable for various high-temperature alloy substrates, is not limited by alloy component differences, can further adapt to workpieces in complex geometrical shapes and is suitable for industrial production. The method can be used for protecting hot-end components such as aero-engine turbine blades and the like.

The invention provides a high-load supersonic cascade and a gas compressor, and belongs to the technical field of gas turbine gas compressors. The blade grid comprises blades and vortex generators, the vortex generators are installed in the front edge areas of the blades, and the vortex generators and the suction surfaces of the blades are located on the surfaces of the same sides of the blades. In the airflow direction corresponding to the blades, the height of the vortex generator is gradually reduced, the width of the vortex generator is gradually increased, and the width of the vortex generator is the size of the vortex generator in the spreading direction of the blades. The vortex generators in specific shapes are arranged on the surfaces of the blades, so that after airflow passes through the vortex generators, two reverse vortex pairs spaced by a certain distance can be generated, and the two reverse vortex pairs can entrain the airflow from a mainstream area with more gas and supplement the airflow to a shock wave / boundary layer interference separation area lacking gas; therefore, flow separation of the rear half section of the suction surface is inhibited, flow loss is reduced, and aerodynamic performance of the cascade is improved.

The invention provides a supersonic rotational flow atomization dust removal spray head device and a spray pipe optimization simulation analysis method, and relates to the technical field of supersonic rotational flow atomization spray heads, the device comprises an air inlet pipe, a liquid inlet, a shell, a Laval spray pipe, an outer rotational flow pipeline and an atomization spray nozzle, the Laval spray pipe is arranged in the outer rotational flow pipeline, and the atomization spray nozzle is arranged in the shell; a wave elimination section of the Laval nozzle is connected with the atomizing nozzle, a spirally distributed liquid film circular seam is formed in the side wall of a mixing chamber at the lower end of a throat part of the Laval nozzle, and a spiral flow deflector is arranged at an outlet of the atomizing nozzle. Efficient dynamic interaction with rotating liquid supplied by the outer ring spiral channel occurs at the outlet of the nozzle, efficient fog drop crushing and uniform spraying are achieved through airflow acceleration and kinetic energy conversion, and it is guaranteed that the particle size of fog drops meets the requirements of capturing coal dust, improving the atomization efficiency, strengthening the wind resistance and reducing water consumption; better fogdrop particle size matching is realized; and the blocking risk is reduced.

The invention relates to the technical field of tin smelting, and discloses a top-blowing supersonic rotational flow spray gun and a control system and method thereof.The top-blowing supersonic rotational flow spray gun comprises four layers of sleeves, and a flow channel formed by the outer layer sleeve and the supersonic layer sleeve is mainly used for blowing desulfurized concentrate; a flow channel between the supersonic speed layer sleeve and the cyclone layer sleeve is used for blowing oxygen-enriched air; a runner between the cyclone layer sleeve and the inner layer sleeve is used for blowing dry powder; and an internal runner of the inner-layer sleeve is used for injecting pulverized coal. The system comprises a Mach number acquisition module which is used for acquiring oxygen-enriched air flow, pressure, temperature and spray gun structure size parameters of real-time industrial application and finally required Mach number of a spray gun expansion flow channel outlet; the three-dimensional flow channel model building module is used for building a three-dimensional flow channel model and dividing the three-dimensional flow channel model into hexahedral grids; and when the preset deviation value is reached, the initial physical field is calculated. Oxygen-enriched air is effectively accelerated to a supersonic speed state, and the stirring efficiency of a molten pool and the penetration depth of material particles are remarkably improved.

The invention discloses a rotating detonation afterburner based on centrifugal nozzle discrete injection, and belongs to the technical field of detonation propulsion. The combustion chamber comprises a gas collecting cavity, an injection unit, a centrifugal nozzle, an outer ring and an inner column, wherein an annular detonation combustion chamber is formed between the inner wall surface of the outer ring and the outer wall surface of the inner column. The centrifugal nozzles are uniformly arranged at the intersection of the gas collection cavity and the injection unit in the circumferential direction to realize primary atomization of the fuel oil; the air is accelerated by the injection unit from the air collection cavity and then is mixed with the atomized fuel oil, secondary atomization is achieved, the particle size of liquid drops is remarkably reduced, and the fuel activity and mixing uniformity are improved. The injection unit adopts a Laval nozzle profile, air is accelerated to supersonic speed in the injection unit, and pressure of a combustion chamber is prevented from being transmitted forwards. The rotary detonation engine is suitable for the high-temperature low-oxygen environment, supports the annular combustion chamber configuration and the empty cylinder combustion chamber configuration, can achieve stable rotary detonation detonation and propagation of liquid fuel and air, and provides technical support for engineering application of the rotary detonation engine.

The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and / or a cylindrical center body disposed in or upstream of the detonation chamber.

The invention discloses a supersonic speed laser spraying device and method, relates to the technical field of laser spraying, and realizes laser transmission and supersonic speed powder flow collaboration through cooperation of optical elements such as an output optical fiber, a collimating lens group and a convergent lens and a Laval nozzle structure. The method comprises the steps that multi-parameter closed-loop regulation and control are conducted, parameters such as the molten pool temperature and the powder flow divergence angle are monitored synchronously, and a process health index is constructed to trigger laser power, airflow pressure and powder feeding amount dynamic compensation; self-adaptive focus scanning is carried out, the focus position is adjusted in real time through a laser displacement sensor, and working modes are switched in linkage with a process health index; and lens abnormity diagnosis is carried out, a health index is constructed by using dual-wavelength transmissivity and wavefront distortion, and grading early warning and linkage powder feeding amount adjustment are carried out. According to the scheme, coating defects can be reduced, and the spraying precision and the system stability are improved.

A submunition assembly to be stored and deployed from an aerial vehicle, particularly a supersonic vehicle, includes a container having at least first and second walls that are joined at one end by a hinge that together define a volume along an axis perpendicular to the hinge that contains a submunition. The submunition assembly is suitably axially-shaped with a rigid parachute panel positioned around the hinge to separate and deploy a parachute. The container may have an internal volume that is conformal to the submunition. The container may have an exterior shape that is either optimized for free-fall or has a portion that provides a conformal surface for the aerial vehicle. The submunition assembly may be configured so that all processing, memory and data resides with the submunition, which issues any and all commands to control the container including separation of the rigid parachute panel and opening of the container to release the submunition.

The application provides a rotary impingement oblique flow centrifugal combined compressor and application thereof, and belongs to the technical field of turbine engines, and comprises an outer casing structure, an inner casing structure, a working mechanism and a diffuser mechanism, the outer casing structure and the inner casing structure are rotary bodies, the inner casing structure is located inside the outer casing structure, the inner casing structure and the outer casing structure form a working cavity, the working mechanism is installed in the working cavity and is used for pressurizing airflow. Compared with the compression mode of a conventional combined compressor, the application draws lessons from the pressurization mode of a supersonic inlet, and the Mach number of airflow relative to a rotating impeller reaches 2 or more through high-speed rotation; at this time, a series of weak oblique shock waves are constructed through the contraction of a passage, and a high-efficiency compression system is obtained through the pressurization of the shock wave system, the single-stage pressure ratio of the high-efficiency compression system is much higher than that of a conventional compressor, and the application has the advantages of compact structure, simple processing and long service life.

Ejector for use in a refrigeration circuit device, which features: a drive-side nozzle (31) designed to expand a drive-side coolant and accelerate it to a supersonic speed and inject the drive-side coolant as a drive-side injection coolant in a gas-liquid two-phase state; and a body (32) which includes: a coolant suction port (321) designed to draw suction-side coolant; a suction-side nozzle (322) designed to expand and inject the suction-side coolant, which is drawn in as suction-side injection coolant through the coolant suction port (321); a mixing section (323) designed to mix the suction-side injection coolant injected from the suction-side nozzle (322) and the drive-side injection coolant injected from the drive-side nozzle (31); and a diffuser section (324) designed to convert kinetic energy of the mixed coolant formed from the suction-side injection coolant and the drive-side injection coolant mixed in the mixing section (323) into pressure energy, wherein: the drive-side nozzle (31) has a converging section (31b), a neck section (31c) and a diverging section (31d), wherein the diverging section (31d) has a passage cross-sectional area for the passage of the coolant, which is progressively enlarged from the neck section (31c) to a drive-side injection port (31e); the drive-side nozzle (31) is arranged coaxially in a cylindrical space formed on an inside of the body (32); a coolant passage of the suction-side nozzle (322) is formed between an outer circumferential surface of the diverging section (31d) and an inner circumferential surface of the body (32) and has a cross-section that is formed in an annular shape; the drive-side injection port (31e) of the drive-side nozzle (31) and a suction-side injection port (322a) of the suction-side nozzle (322) are open such that an injection direction of the drive-side injection coolant injected by the drive-side injection port (31e) and an injection direction of the suction-side injection coolant injected by the suction-side injection port (322a) coincide; a pressure of the drive-side injection coolant is higher than a pressure of the suction-side injection coolant; and when the mixed coolant flows out of the mixing section (323) and into the diffuser section (324), a pressure of the mixed coolant measured on a central axis of the mixing section (323) and a pressure of the mixed coolant measured on a wall surface of the mixing section (323) are equal, while a flow velocity of the mixed coolant is a subsonic velocity.

The invention relates to the field of metal nano material preparation, and discloses a supersonic gas atomization preparation method of high-dispersity spherical nano aluminum powder, which comprises the following steps: establishing a constant-temperature aluminum melt flow, and constructing a supersonic gas-solid two-phase atomization jet flow; nitrogen with the temperature lower than the melting point of the particles is used for carrying flow, solid zinc stearate particles are carried and accelerated to supersonic speed, and the aluminum melt flow is impacted; solid rigid momentum of the particles penetrates through an aluminum liquid interface to enter liquid drops, thermal relaxation time difference is used for inducing the particles to generate phase change decomposition in the liquid drops, the liquid drops are broken from the inside through volume expansion, and a carbon-zinc composite isolation layer is formed in situ through decomposition products. And high-efficiency nanocrystallization crushing under low energy consumption is realized.

The present application belongs to the technical field of hypersonic wind tunnel test, and discloses a test checking method of hypersonic frictional resistance standard value. The test checking method of hypersonic frictional resistance standard value is carried out in a hypersonic quiet wind tunnel, and the model is stably kept in a laminar flow state by means of a quiet flow field provided by the hypersonic quiet wind tunnel, so that the interference of flow field noise on the hypersonic frictional resistance is eliminated, real near space flight test data is obtained, and the obtained hypersonic frictional resistance standard value can be used for related test calculation or theoretical analysis, thereby providing technical support for the research on the frictional resistance of a spacecraft.