15 results about "Supersonic nozzle" patented technology

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 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 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 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 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 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 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.

This invention discloses a supersonic nozzle and planar blade cascade tester, comprising a nozzle box, an inlet flange disposed at the air inlet of the nozzle box, and an outlet flange disposed at the air outlet of the nozzle box. The nozzle box includes two symmetrically arranged side plates and two symmetrically arranged profiled panels. The two side plates and the two profiled panels together form the flow channel of the nozzle box. The inner wall surface of the profiled panels is a continuously changing arc surface, causing the flow channel to have a structure of first contraction and then expansion along the air inlet direction. The minimum distance between the flow channels is the throat. An adjustment mechanism is disposed on the profiled panels. The adjustment mechanism is used to drive the inner wall surface of the profiled panels to move perpendicular to the air inlet direction to adjust the size R of the throat. The size R is the distance between the flow channels of the two profiled panels at the throat. The supersonic nozzle of this invention can realize the area adjustment of the throat flow channel surface, and can ensure that the Mach number and flow field uniformity at the nozzle box exit meet the design requirements.

The present application relates to a kind of steam flow control device in well, including center tube, it is provided with wedge groove and step portion;Cap, it is installed on center tube;Nozzle assembly, it includes nozzle seat and supersonic nozzle installed on nozzle seat, nozzle assembly is installed on wedge groove;Screen assembly, it includes screen rib and screen installed on screen rib, one end of screen assembly is sleeved at the step portion of center tube and the other end extends along center tube;Cap, one end is connected on cap and the other end is abutted on screen assembly, cap is in contact with nozzle assembly and compresses nozzle assembly;Lower retaining ring, it is provided on center tube and is connected with the other end of screen assembly.The present application also relates to a string with the above device.The present application can realize effective and accurate control of steam flow;Can play a protective role to oil well;And can realize the steam flow control of multilayer section.