66 results about "Nozzle throat" patented technology

The embodiment of the invention discloses an ultrahigh compression ratio adjustable ejector and a variable working condition performance optimization design method thereof. The adjustable ejector comprises a nozzle, an adjusting cone, a suction chamber, a mixing chamber and a diffusion chamber, wherein working fluid is introduced into the nozzle, the adjusting cone is arranged at the throat part of the nozzle, and the fluid to be ejected is introduced into the suction chamber; the adjusting cone is formed by alternately and repeatedly connecting cylindrical surface sections and conical surface sections, and the adjusting cone can axially move; the method comprises the steps that the pressure of working fluid input into the adjustable ejector is monitored; when the pressure of the working fluid is changed between the first pressure and the second pressure, the adjusting cone is axially moved, and each cylindrical surface section directly faces the throat part in sequence, so that step type adjustment of the pressure of the working fluid is realized; when the pressure of the working fluid is changed between the second pressure and the fourth pressure, the adjusting cone is axially moved, and each conical surface section directly faces the throat part in sequence, so that the continuous adjustment of the pressure of the working fluid is realized; the mass flow of the ejected fluid in the adjustable ejector belongs to a preset range; the first pressure, the second pressure, the third pressure and the fourth pressure are gradually increased in sequence.

The invention discloses a sealing device for a jet pipe of a solid rocket engine. The sealing device comprises a front supporting body, a rear supporting cylinder and a sealing plug cover. The front section of the front supporting body is a circular-truncated-cone-shaped positioning cylinder, the rear section of the front supporting body is a circular-ring-shaped connecting cylinder, and internal threads are machined on the rear section of the inner wall of the circular-ring-shaped connecting cylinder. An external thread is machined on the outer wall of the rear supporting cylinder, a positioning circular plate is vertically fixed to the rear end of the rear supporting cylinder, and the outer edge of the positioning circular plate is machined to be a circular truncated cone face. The front supporting body and the rear supporting cylinder are inserted inwards from the two ends of the spray pipe respectively and then are in threaded butt joint, the outer wall of the front supporting body is tightly attached to the inner wall of a convergence section of the spray pipe and the inner wall of a spray throat, and the outer edge of a positioning circular plate of the rear supporting cylinder is tightly attached to the inner wall of an expansion section of the spray pipe. And the sealing blanking cap is in threaded connection with the front end of the rear supporting cylinder. According to the spray pipe sealing device, ignition pressure can be reliably established, and residues are few during separation.

The invention discloses an interference type focusing sensing probe based on an optical fiber built-in groove light splitting structure, an optical fiber groove structure is adopted in an optical fiber displacement sensing probe, so that reference light and measuring light are formed, the light path layout is optimized, the light collecting angle is increased, the contrast ratio of interference fringes and the signal-to-noise ratio of signals are improved, and the interference type focusing sensing probe has a wide application prospect. The design can effectively measure the complex morphology in the aero-engine part, has the characteristics of compact structure, small size, high measurement precision and the like, and can meet the test requirements of narrow and complex spaces such as an engine nozzle throat part and the like.

The invention discloses an adjustable dynamic and static ring for a coal mill, and relates to the technical field of coal mills.The upper portion of a millstone is provided with an annular milling channel, one side of the bottom of the millstone is connected with a dynamic ring mechanism through a bolt, the radial outer wall of the dynamic ring mechanism is in lap joint with a bearing mechanism, and the upper portion of the bearing mechanism is provided with a first static ring mechanism; a second static ring mechanism is arranged on the upper portion of the first static ring mechanism, the movable ring mechanism is located below the second static ring mechanism, gaps are reserved among the movable ring mechanism, the bearing mechanism, the first static ring mechanism and the second static ring mechanism, and an L-shaped channel is formed. According to the adjustable dynamic and static ring for the coal mill, an air duct and a nozzle are redesigned, the air duct nozzle is subjected to Venturi design, the air speed is gradually increased from an inlet to an outlet of the nozzle and reaches the maximum at the throat part of the nozzle, the ventilation resistance can be reduced, a sealing structure is redesigned, a dynamic and static gap can be ensured, primary air leakage is reduced, and primary air is efficiently utilized; pulverized coal can be carried more effectively, and the output of the coal mill is ensured.

The invention relates to the technical field of atomization conveying devices, in particular to a pneumatically-controlled atomization leading-in device which comprises a shell, a liquid guiding device, an air pump, a controller and an injection mixing assembly, the shell is provided with a bottle neck connecting cavity, and the bottle neck connecting cavity is used for being detachably connected with a bottle neck of a liquid storage bottle in a sealed mode; the bottle mouth connection cavity is provided with a one-way gulp valve, and the one-way gulp valve is communicated with the outside and the interior of the liquid storage bottle so as to supplement air to the liquid storage bottle; the injection mixing assembly is provided with a gas inlet, a suction inlet and a mixing outlet and comprises a gas nozzle, a throat part and a diffusion section which are communicated in sequence, the gas inlet is communicated with the gas nozzle, the suction inlet is communicated with a low-pressure area of the throat part, and the mixing outlet is communicated with the diffusion section; and the mixed gas-liquid two-phase mixture flows through the mixing outlet, enters the liquid guide inlet and is atomized and output by the atomizing nozzle, so that the effects of more continuous spray output and more uniform atomization are realized.

The application relates to a preparation method of a high-density graphite-based dissipation heat-resistant composite material. In order to solve the problems of high cost of the existing dissipation heat-resistant composite material and poor ablation resistance of the graphite dissipation heat-resistant composite material, the preparation method comprises the following steps: mixing multi-element dissipation agent raw materials, uniformly mixing the multi-element dissipation agent raw materials, loading the multi-element dissipation agent raw materials into a graphite crucible, processing a high-density graphite base into a shape to be prepared, mounting the high-density graphite base on a lifting rod of a vacuum infiltration furnace, preparing a dissipation agent alloy melt, and immersing the graphite base in the dissipation agent alloy melt to obtain the high-density graphite-based dissipation heat-resistant composite material. The high-density graphite-based dissipation heat-resistant composite material is prepared by using the vacuum infiltration method, high-purity graphite is used as the base, the composition of the dissipation agent alloy is adjusted, the dissipation agent is wetted with the graphite base, and the ablation resistance of the workpiece is improved. The application can be used for preparing aircraft engine nozzle throat liners, aircraft nose cones and wing leading edges and the like components.

This application belongs to the field of turbofan engine starting design technology, specifically involving a turbofan engine backwind starting method, including: Step 1, identifying whether the turbofan engine is starting under high-speed backwind conditions by whether the low-pressure rotor reverses; if the low-pressure rotor reverses, the turbofan engine is identified as starting under high-speed backwind conditions; Step 2, after identifying that the turbofan engine is starting under high-speed backwind conditions, determining the wind pressure resistance PdX of the turbofan engine starting under high-speed backwind conditions by the low-pressure rotor reverse rotation speed and the correspondence between the low-pressure rotor reverse rotation speed and wind pressure resistance; Step 3, after the low-pressure rotor changes from reverse rotation to forward rotation under the starter motor, reducing the nozzle throat area A8, adjusting the nozzle exit area A9 and vector angle δA9 to shield the nozzle throat, increasing the ignition speed to ignite the turbofan engine, and increasing the fuel supply speed to supply fuel to the turbofan engine, thereby starting the turbofan engine.

The invention relates to the technical field of gas flow measurement, and discloses a deposition early warning method and system for a sonic nozzle gas flow standard device, and the method comprises the steps: collecting a dynamic pressure signal of upstream gas of a sonic nozzle, and recognizing and segmenting a transient risk window; transmitting an ultrasonic detection signal to the airflow in the sonic nozzle, receiving a penetration signal of the airflow, and extracting a coherent acoustic characteristic quantity used for representing the state of a boundary layer of the throat wall surface of the nozzle; and performing comparative analysis on the coherent acoustic characteristic quantity and a pre-established reference characteristic spectrum to generate early warning information. According to the method, a progressive accurate diagnosis chain from macroscopic fluid dynamic capture to microscopic surface effect detection to metering risk quantitative evaluation is constructed, so that the fundamental technical difficulty that silence misalignment caused by deposition of a sonic nozzle gas flow standard device is difficult to perceive and quantitatively evaluate is solved; and the reliability of the detection result of the device is improved.

A fluid inhalation device, comprises a casing having therein a fluid reservoir, a fluid-air outlet connected to a top end of the fluid reservoir, a vacuum channel, having a bottom end connected to a bottom end of the fluid reservoir, an air duct having an air inlet at a first air duct end, and a nozzle connected to a second air duct end through a nozzle throat and connected to the fluid reservoir through a nozzle exit, a top end of the vacuum channel is connected to the nozzle. The fluid inhalation device may also include a filling port, fluidly connected to the fluid reservoir; and / or one or both of an air duct valve, and the fluid-air channel valve.

The present application relates to a kind of hypersonic carbon dioxide profile nozzle design method, belong to wind tunnel test field;Hypersonic carbon dioxide nozzle is set by expansion section, throat and contraction section three parts;Contraction section is determined by straight line plus circular arc curve;Expansion section is determined by circular arc curve and straight line;Smoothly connect the circular arc curve of contraction section and expansion section, i.e. get conical nozzle curve;The junction of contraction section and expansion section is throat;Nozzle throat diameter is by equivalent specific heat ratio and numerical calculation;Expansion section is determined by characteristic method and numerical correction;Contraction section is determined by straight line plus circular arc curve;The present application provides high-quality hypersonic wind tunnel test aerodynamic data for Mars reentry vehicle development, can simulate Mars flight environment.

The application discloses an aero-engine thrust fast response redundant control method and system considering combustion delay, and belongs to the technical field of aero-engine control. The method steps are as follows: an open-loop transfer function L of main fuel flow and tail nozzle throat area respectively controlling thrust is established based on a desired thrust closed-loop bandwidth; a decoupling condition between the variable tail nozzle throat area and the thrust is set to eliminate the mutual influence between them; four undetermined RTM controller functions in the transfer function L are solved; the actuator transfer functions of the main fuel flow and the tail nozzle throat area are set as first-order systems for solving; system identification is carried out at an engine steady-state working point to obtain a transfer function of a difference between the main fuel flow and the tail nozzle throat area relative to a steady-state value to a difference between the thrust and the steady-state value; the transfer function L is solved, and then the RTM control is completed according to the transfer function L, so that the fast response control of the thrust is realized. The application solves the key technical problems in the prior art.

The invention discloses a design method of a wedge-shaped grain for testing a combustion rate by an impulse method based on a pressurization rate boundary. The problem that in an impulse method experiment, when an inner hole surface-increased combustion tubular grain is adopted for measuring the dynamic combustion speed of a solid propellant under different pressure intensities, the pressurization rate of a high-pressure-index propellant in the later stage of combustion is too high, and consequently the combustion speed cannot respond to pressure intensity changes in time is mainly solved. The method has the innovation points that (1) a mathematical relationship between the combustion surface area size and the change rate and the influence of the nozzle throat diameter on the pressurization rate is established, and a design method for controlling the pressurization process by regulating and controlling the combustion surface area is provided; (2) an outer wedge-shaped grain is designed on the basis of a traditional tubular grain, the combustion surface area and the change rate of the combustion surface area in the later stage of combustion are reduced, and the pressurization rate in the later stage of combustion is inhibited; and (3) in the design process of the wedge-shaped grain, the specific design process of the wedge angle of the wedge-shaped grain, the thickness of the cylinder section and the sizes of other grains is given in combination with the pressurization rate, and the design process of the wedge-shaped grain is standardized.

The application belongs to the technical field of engine control, and particularly relates to a deceleration control method and device for improving fan stability margin. The method comprises the following steps: S1, obtaining an engine deceleration start time, a low-pressure conversion speed after deceleration and a nozzle throat area; S2, discretizing a low-pressure conversion speed change interval into a plurality of low-pressure conversion speed control amounts; S3, superimposing a nozzle throat area increase amount on the basis of an initial value of the nozzle throat area to form a first nozzle throat area, and simultaneously determining a second nozzle throat area for maintaining stable operation of the fan; S4, selecting a minimum value from the two nozzle throat areas and a maximum value of the nozzle throat area to form a nozzle throat area adjustment amount corresponding to the low-pressure conversion speed control amount; and S5, adjusting the nozzle throat area according to the corresponding relationship between the low-pressure conversion speed control amount and the nozzle throat area adjustment amount. The application can ensure that the deceleration time meets the index requirement and improve the aircraft maneuvering performance.

The present application relates to atomization delivery device technical field, especially in pneumatic control's atomization guide device, including casing, liquid guide device, air pump, controller and injection mixing assembly, the casing is equipped with bottle mouth connection cavity, the bottle mouth connection cavity is used for with the bottle mouth of liquid storage bottle can be detached seal connection;The bottle mouth connection cavity is equipped with one-way air supplement valve, the one-way air supplement valve is communicated with the outside and the inside of the liquid storage bottle, in order to be supplemented to the liquid storage bottle air;The injection mixing assembly has gas inlet, suction inlet and mixing outlet, and includes the gas nozzle, throat and pressure recovery section that are communicated in turn, wherein, the gas inlet is communicated with the gas nozzle, the suction inlet is communicated with the low pressure area of the throat, and the mixing outlet is communicated with the pressure recovery section;Mixed gas-liquid two-phase mixed flow through the mixing outlet enters the liquid guide inlet and is atomized by the atomizing nozzle and is output, realizes the effect that spraying output is more continuous, atomization is more uniform.

The invention relates to the field of oil and gas production engineering, in particular to a jet pump process parameter design method considering gas and liquid phases and related products. Calculating the suction pressure of the jet pump; the minimum cavitation area of the jet pump is calculated, and multiple nozzle-throat combinations of the jet pump are determined; determining the power hydraulic pressure; calculating the flow of the power liquid, and determining the discharge pressure; calculating a dimensionless mass flow ratio; calculating a dimensionless pressure ratio; iterative calculation is carried out, and an optimal combination is obtained through screening from various nozzle-throat combinations; determining process parameters of the jet pump; determining ground pump parameters based on the process parameters of the jet pump; according to the method, the optimal operation parameters of the jet pump are determined by calculating the flow characteristics of the gas-liquid mixed fluid in the well, the accuracy of pump parameter design when the jet pump lifts the gas phase and the liquid phase can be improved, and the negative influence of the gas phase proportion on the operation performance of the pump is reduced by introducing correction calculation of the dimensionless pressure ratio and the dimensionless mass flow ratio.

The application belongs to the field of aircraft design and is a method for subsonic cruise state fuel consumption of a small-bypass-ratio turbofan engine. The method comprises the following steps: obtaining initial performance record results of the whole machine in a subsonic cruise state, analyzing and judging whether the working state of the small-bypass-ratio turbofan engine is in an optimal state, and optimizing a preliminary design of a cruise fuel consumption debugging scheme to determine a preliminary adjustment scheme of an optimal fan guide vane angle a1 and a preliminary adjustment scheme of an optimal compressor guide vane angle a2; further adjusting a nozzle throat area A8 and a nozzle outlet area A9 to different areas to determine an optimal nozzle throat area A8 and an optimal nozzle outlet area A9; and finally judging installation fuel consumption under the condition of the whole aircraft to obtain an optimal installation fuel consumption state when the installation fuel consumption is optimal. The method systematically and normatively proposes a debugging step for optimizing subsonic cruise state fuel consumption, which can effectively reduce engine installation fuel consumption.

A spin-die manifold includes a nozzle throat having long sides and short sides, in which a spinning pack is arranged with a spinneret arranged underneath, and at least one distribution block having a spinning pump. Liquid plastic is conveyed to the spinning pump via an extruder, which conveys the liquid plastic to the spinning pack via the at least one distribution block via distribution lines arranged inside the distribution block. At least one distribution block is arranged on a long side of the nozzle throat. The nozzle throat has at least one surface heating element on each of its vertical flat long and short sides. The at least one distribution block has at least one surface heating element on at least one part of its upper or lower outer surface. The surface heating elements electrically heat at least this part of the long and short sides and outer surface.

This invention discloses a tie-rod type nozzle structure with adjustable throat area, relating to the field of fluid machinery, aiming to solve the technical problem that existing fixed nozzles cannot achieve stepless adjustment of the throat area. It includes a fixed nozzle, a movable nozzle sleeved on the rear section of the fixed nozzle, an inner cone forming an exhaust channel, and multiple tie-rod assemblies distributed circumferentially. The two ends of each tie-rod assembly are connected to the fixed nozzle and the movable nozzle respectively, and their lengths are adjustable. By synchronously rotating the double-ended studs of each tie-rod assembly, the movable nozzle can be driven to slide axially relative to the fixed nozzle, changing the axial relative position of the movable nozzle outlet and the inner cone, thereby achieving stepless and continuous adjustment of the nozzle throat area. This invention has a simple and reliable structure, is convenient and flexible to operate, and only requires one device to meet a wide range of flow rate adjustment needs, significantly reducing the cost and cycle of multi-scheme matching tests, making it particularly suitable for application scenarios such as matching tests of aero-engine exhaust systems.

The disclosed assembly includes an exhaust gas turbine housing having inner and outer walls defining first and second exhaust gas channels to a turbine wheel space where an inner wall includes an inner wall end and an outer wall includes an outer wall end, both at the turbine wheel space. A first flow body is disposed adjacent to the inner wall end. A second flow body is disposed adjacent to the outer wall end. At least one set of adjustable variable geometry nozzle vanes define nozzle throats that direct flow of exhaust gas from at least one of the exhaust gas channels to the turbine wheel space At least one of the first flow body and the second flow body includes a concave trailing surface defined in part by an extension of an airfoil surface.

Munition comprising a base and an insert. The present invention relates to ammunition comprising a projectile (1), a propellant charge (3), and a priming device (5) held together by a case, the case forming a nozzle, a nozzle throat, a combustion chamber (4j), and a primer channel. The ammunition is characterized in that the case consists of at least two parts: a base (4b) and an insert (4a), said parts being assembled together after the propellant charge (3) has been inserted into the combustion chamber (4j). Figure for the abstract: Figure 2

The invention discloses a gas flow measurement error correction method and system based on a critical flow sonic nozzle, and relates to the technical field of gas flow measurement, and the method comprises the following steps: carrying out logarithmic operation on a sharpened average power spectrum, executing inverse discrete Fourier transform to obtain a real cepstrum sequence, and extracting the characteristics of a low cepstrum interval to obtain the gas flow measurement error. Calculating a characteristic factor representing the state of the boundary layer of the nozzle throat; meanwhile, the Reynolds number under the current flowing working condition is calculated on the basis of static pressure and static temperature data, the ISO standard outflow coefficient is dynamically corrected in combination with a pre-calibrated Reynolds number partition sensitivity coefficient, and the corrected outflow coefficient is obtained. By performing autocorrelation analysis on a real cepstrum high delay interval, judgment on a critical flow state of a nozzle is realized, and actual mass flow is calculated based on a corrected outflow coefficient under a stable critical flow condition, so that the accuracy and stability of flow measurement under a wide working condition are improved, and a system error introduced by a traditional static correction model is reduced.

A fluid inhalation device, comprises a casing having therein a fluid reservoir, a fluid-air outlet connected to a top end of the fluid reservoir, a vacuum channel, having a bottom end connected to a bottom end of the fluid reservoir, an air duct, having an air inlet at a first air duct end, and a nozzle connected to a second air duct end through a nozzle throat, and connected to the fluid reservoir through a nozzle exit. The nozzle throat is narrower than the nozzle exit, and a top end of the vacuum channel is connected to the nozzle.

This invention discloses a method for determining the operating point position of a continuous wind tunnel compressor during variable speed operation, relating to the field of wind tunnel testing. This invention obtains a general performance curve of the compressor through experimentation; it performs parametric modeling on discrete constant-speed total pressure ratio performance curves to obtain a continuous parametric mathematical model; it determines the total pressure, total temperature, and nozzle profile state in the wind tunnel's stable section and calculates the nozzle mass flow rate; it records the compressor inlet total pressure, outlet total pressure, and equivalent speed at the inflection point where the nozzle throat reaches the speed of sound; and it uses an iterative solution method, assuming the inlet total pressure at the new speed, calculating the equivalent flow rate, substituting it into the parametric model to obtain the total pressure ratio, back-calculating the inlet total pressure, and determining convergence, ultimately determining the operating point position at the new speed. This invention can determine the operating point position of the compressor after variable speed operation in advance, solving the unpredictable problem in existing technologies, improving the efficiency of wind tunnel commissioning and operation, and reducing operational risks.

The application discloses a design method and system of a critical mode ejector suitable for a hydrogen circulation system of a fuel cell, and comprises the following steps: obtaining a primary flow mass flow rate of a nozzle throat based on a fuel cell anode channel mass conservation equation; calculating a nozzle throat diameter; determining a nozzle outlet diameter and a nozzle outlet position; judging whether a critical back pressure of the ejector is higher than a corresponding anode inlet pressure; if yes, judging whether a hydrogen recirculation ratio meets a requirement; otherwise, changing the highest and lowest working pressures of the primary flow of the ejector, and recalculating the nozzle throat diameter, the nozzle outlet diameter and the nozzle outlet position; if the hydrogen recirculation ratio meets the requirement, the design of the ejector is completed; otherwise, changing the diameter, length and length of a diffusion chamber of an equal-area mixing chamber until the hydrogen recirculation ratio meets the requirement, and the design of the ejector is completed. The application is helpful to the critical mode ejector design of a fuel cell system under variable working conditions.

The present application belongs to the technical field of aerodynamic heat protection ground test equipment of space vehicles, and discloses a variable Mach number telescopic conical nozzle and a using method thereof. The variable Mach number telescopic conical nozzle comprises a nozzle throat section, a first-stage nozzle expansion section, a second-stage nozzle expansion section and a nozzle exit section which are connected in turn from front to back, a sealing element is arranged on the contact surface of each section, and each section is installed with a matched electric hydraulic push rod to realize the pushing and pulling and positioning of the corresponding section. The variable Mach number telescopic conical nozzle and the using method thereof utilize the sleeve type sandwich water-cooled nozzle, combine with the movable heater base, realize the change of the nozzle exit diameter during the operation of the arc wind tunnel, and thus change the pressure, heat flow and other parameters of the nozzle exit flow field in a large range in the ground heat protection test of the hypersonic vehicle heat protection system, realize the simulation in a wide parameter range, widen the test capacity of the arc wind tunnel, and have the engineering practical value.

The present invention relates to ammunition comprising a projectile (1), a propellant charge (3) and a priming device (5), held together by a cartridge case, the cartridge case forming a nozzle, a nozzle throat, a combustion chamber (4j) and a primer channel. The ammunition is characterized in that the cartridge case consists of at least two parts: a base (4b) and an insert (4a), said parts being assembled together once the propellant charge (3) has been integrated into the combustion chamber (4j).

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 belongs to the technical field of aero-engine control, and particularly relates to an engine direct thrust control method and system based on thrust response trajectory optimization. According to the initial state parameter and the target state parameter of the engine, the thrust response time is used as a target function, and the target open-loop slope with the shortest thrust response time of the engine is iteratively searched under the constraint condition through an interior point method; and according to the fuel flow initial value, the nozzle throat area initial value and the target open-loop slope, the target thrust control quantity is obtained. According to the control method, on the premise of ensuring safe operation, the thrust response speed of the engine can be greatly increased, and the limit maneuverability of the aircraft is enhanced; compared with conventional proportional-integral control, the method has the advantages that the transfer process of state quantity of indirect control is avoided, and the thrust is directly controlled in a target range, so that the thrust response time is greatly shortened.

The present application relates to a kind of solid-liquid binding rocket two-phase jet particle phase loading method, belong to the field of launch vehicle;The throat of nozzle is regarded as particle inlet, and the throat is divided into multiple small areas as particle phase inlet;Determine the particle phase loading parameter of each small area, particle phase loading parameter includes particle phase molar mass C mr , particle phase average diameter d mr , particle phase average diameter distribution law, particle phase temperature, particle phase velocity c;By determining the particle phase loading parameter of each small area, realize the particle phase loading of each small area;Finally realize the particle phase loading of entire nozzle throat;The present application gives the loading method of particle phase at jet inlet in the simulation analysis of solid rocket engine two-phase flow.

The invention provides a nozzle throat structure of a supersonic high-temperature wind tunnel, which relates to the technical field of nozzle throats, and comprises an inner shell, and a nozzle which is gradually shrunk and then gradually expanded from one end to the other end is formed in the inner shell; the inner shell comprises a first section located on the throat portion of the spray pipe, second sections located on the two sides of the throat section and third sections located on the sides, away from each other, of the two second sections, the first wall thickness of the first section is smaller than the second wall thickness of the second sections, and the second wall thickness is smaller than the third wall thickness of the third sections. The reinforcing ribs are evenly distributed on the periphery of the inner shell and extend in the axial direction of the spray pipe. Each mounting block is arranged between every two adjacent reinforcing ribs, and the mounting blocks located on the two sides of each reinforcing rib are connected with the reinforcing ribs in a fastened mode; the problem of contradiction between the wall thickness and the heat conduction efficiency of a nozzle throat structure in the prior art is solved.