15 results about "Nozzle geometry" patented technology

The invention discloses a water-air bimodal self-adaptive rocket engine system and a control method, and belongs to the technical field of rocket control. The system comprises an environment sensing recognition module, a thrust output regulation and control module, a fuel combination switching module, a heat exchange regulation module, an attitude propulsion control module and a modal coordination control module, and precise recognition and rapid classification of a rocket operation environment are realized through combined judgment of a multi-point distributed sensing unit, density and flow characteristics; by constructing a multi-level thrust adjusting system, the dynamic change of the geometrical shape of the spray pipe is achieved, combustion supply ratio adjustment and multi-parameter linkage control are fused, the self-adaptability and response sensitivity of thrust output are remarkably improved, rapid conversion between high-pressure short-range propulsion and efficient long-range flight is achieved, and the high-pressure short-range propulsion and high-efficiency long-range flight are achieved. Regulation and control commands are preloaded and distributed in parallel according to the current environment, so that all functional modules can respond cooperatively, the operation mode in the new environment can be quickly adapted, and the system can capture the execution state of the regulation and control commands in real time.

The embodiment of the invention discloses a uniformity prediction method suitable for a pure hydrogen micro-mixing combustion chamber nozzle array. A specific embodiment of the method comprises the following steps: acquiring a micro mixing pipe structure information set and nozzle structure information; for each micro mixing pipe in the micro mixing pipe set, the following generation steps are executed: carrying out grid division on the micro mixing pipes to obtain micro mixing pipe grid information; performing grid size evaluation processing on the micro mixing pipe grid information to obtain a grid evaluation value; generating a micro mixing tube uniformity coefficient group; determining a cold-state heat conduction physical property parameter set; generating a cold-state nozzle uniformity coefficient; generating a cold-state nozzle uniformity coefficient; and in response to the fact that the cold-state nozzle uniformity coefficient is larger than the preset nozzle uniformity coefficient threshold value, geometric structure adjustment is conducted on the nozzle. According to the implementation mode, the accuracy of nozzle array prediction can be improved, the tempering condition is avoided, the design reasonability of the micro mixing pipe and the nozzles is improved, and damage to the pure hydrogen gas turbine is avoided.

The invention belongs to the field of aero-engines and gas turbine combustion chambers, relates to an engine nozzle design technology, and provides a centrifugal nozzle design method which comprises the following steps: calculating a geometric constant initial value of a nozzle according to a given spray cone angle; according to the nozzle geometric constant initial value and the nozzle geometric constant increment, taking the relative radius of a hollow vortex as a constraint condition and taking a spray cone angle as a convergence condition, and obtaining a converged nozzle flow coefficient and a converged nozzle geometric constant; according to the flow coefficient of the nozzle after convergence, the geometric constant of the nozzle after convergence and the given flow number of the nozzle, the geometric dimension of the nozzle is obtained; and establishing a nozzle geometric model through the nozzle geometric dimension, and evaluating and correcting the nozzle geometric dimension by adopting a three-dimensional simulation method to obtain the final nozzle geometric dimension. According to the method, in the initial design stage of the nozzle, the main geometric parameters of the nozzle can be rapidly obtained, and the feasibility of the overall scheme of the combustion chamber can be evaluated.

The invention belongs to the technical field of nozzle atomization performance optimization, and discloses a pressure swirl nozzle atomization performance optimization method based on an NSWOA algorithm, and the method comprises the following steps: designing a nozzle structure, carrying out the numerical simulation according to the geometric parameters of the nozzle structure, obtaining the atomization performance of the nozzle, and carrying out the optimization if the requirements are not met; a Plackett-Burman screening test is utilized to screen significant factors influencing the atomization performance of the nozzle, Latin hypercube sampling is utilized to sample geometric parameters to be optimized to obtain a sample space, an RBF neural network is utilized to predict to obtain a mapping relation between the geometric parameters of the nozzle and the atomization performance, and an NSWOA algorithm is utilized to optimize the atomization performance of the nozzle. And obtaining a uniformly distributed Pareto solution set, selecting an optimal solution to carry out numerical simulation, and if the atomization performance of the optimized nozzle is better, completing optimization. Through numerical simulation, algorithm screening and optimization, the atomization performance of the nozzle can be accurately optimized, big data analysis is utilized, the optimization efficiency can be improved, and the optimization cost can be reduced.

A compressed gas ejection assembly for a rotating wing aircraft blade comprising a compressed gas passage adapted to allow a substantially constant mass flow through the compressed gas ejection assembly across at least a portion of the width of the compressed gas ejection assembly.

This invention relates to a deep learning-based method for predicting the flow field inside a nozzle, comprising: constructing a variable-configuration nozzle geometry library based on parametric curves and performing CFD calculations to generate a flow field dataset; performing dual-channel encoding processing of the geometric boundaries using the signed distance field (SDF) and the identifier matrix (IM); constructing a deep learning model based on a U-Net backbone network with an embedded dual-ended convolutional compression excitation (DE-ConvSE) adapter; pre-training the model using a basic dataset; employing an incremental learning strategy for new nozzle configurations, freezing the backbone network parameters and fine-tuning only the adapter module; and finally, using the trained model to achieve real-time prediction of the velocity, temperature, and pressure fields inside the nozzle. This invention can significantly reduce CFD simulation computation time, achieve rapid and high-precision prediction of the nozzle flow field, and provide effective technical support for nozzle design optimization.

The embodiment of the present disclosure provides a kind of pre-rotation gas supply system temperature drop measurement method, device and equipment.It includes: determining the total temperature of the gas flow of nozzle inlet;Determine the static pressure and total pressure of nozzle outlet;According to the total temperature of the gas flow, static pressure and total pressure, determine the gas flow velocity of nozzle outlet;Determine the relevant parameters of nozzle, wherein the relevant parameters include nozzle geometric deflection angle, nozzle outlet center radius and gas supply hole outlet center radius;According to the relevant parameters and the gas flow velocity of nozzle outlet, determine the temperature drop of pre-rotation gas supply system.No need to arrange measuring point on turbine disk, reduce processing cost, simplify design process.Directly through pressure tube, nozzle outlet pressure signal is transmitted to pressure scanning valve, parameter transmission is more convenient and stable.Directly in nozzle outlet, pressure tube can be arranged, and more experimental working condition requirements can be adapted.

The invention provides a circular water film-based low-pressure nozzle impact performance optimization method, which comprises the following steps of: establishing a coordinate system by taking a jet flow impact point as an original point, and selecting at least four parameters from geometric parameter vectors of a nozzle to construct a joint objective function, the combined target value adopts a weighted product form of stagnation point pressure, water film area and jet flow hitting power; constructing a test matrix, changing at least four geometric parameters at the same time, and obtaining multi-dimensional response data of the joint target value through numerical simulation; building an explicit second-order model of the joint target value by using multivariate nonlinear regression; performing global optimization by adopting a genetic algorithm or a response surface method, and outputting an optimal geometric parameter combination which maximizes the joint target value; the improved nozzle is obtained through machining according to the optimal geometric parameter combination; and if the hitting power coefficient of the improved nozzle is greater than that of the original nozzle, the optimization is completed. According to the method, parallel search can be carried out in a multi-dimensional parameter space, and the optimization period is remarkably shortened.

The invention discloses a simulation method of an orbit control thermal jet disturbance effect containing temperature influence, which comprises the following steps: determining parameters such as incoming flow Mach number, momentum and total enthalpy according to real flight incoming flow conditions, and determining parameters such as real fuel gas jet total pressure, total enthalpy, specific heat ratio and nozzle outlet momentum according to real orbit control engine fuel gas jet parameters; the method comprises the following steps: determining the geometric dimension of a ground research scaling model according to ground research incoming flow conditions under the condition of ensuring that the research appearance is geometrically similar to a spray pipe, simulating the gas of a real orbit control engine by using gas jet flow such as air or gas, and simulating the momentum ratio and the total enthalpy ratio of the jet flow to incoming flow; a ground wind tunnel test or a numerical simulation method is adopted to obtain a force interference factor and an orbit control offset of orbit control thermal jet interference. The method can be used for a thermal spray interference wind tunnel test or numerical simulation.

A fire extinguishing system nozzle includes a housing. Two or more orifices in the housing emit an extinguishing agent. Each of these orifices emits the extinguishing agent in the form of a rotating vortex.

The invention relates to the field of numerical simulation, and discloses a nozzle optimization method of a urea direct injection system for waste heat boiler denitration, which is used for improving the denitration efficiency and the operation stability of the urea direct injection system and reducing the ammonia escape rate and the operation cost. Comprising the following steps: establishing a three-dimensional parameterized CFD nozzle model based on parameters such as a waste heat boiler flue structure, generating a plurality of distribution diagrams, screening out a candidate scheme set of which the mixing uniformity reaches the standard, processing and manufacturing a replaceable nozzle physical sample unit according to parameters of the candidate scheme set, and measuring a denitration efficiency value and an ammonia escape rate value of each model machine under an actual operation condition. And performing correlation analysis on various distribution diagrams, denitration efficiency values and ammonia escape rate values, delimiting an effective mixing zone boundary based on a flue gas flow velocity field and the like, and outputting optimal nozzle geometric dimension parameters meeting engineering application. According to the method, through multi-dimensional modeling, calculation, experiment and correlation analysis, the optimal nozzle geometric dimension parameters meeting engineering application are accurately output, the denitration efficiency is effectively improved, and the ammonia escape rate is reduced.

Techniques for determining a damping rate of unforced oscillations of a meniscus are disclosed. An example method includes receiving input describing a shape of a container, physical parameters of a liquid inside the container, and an equilibrium shape of the meniscus. The method also includes generating a mesh conforming to the shape of the container and generating a discrete version of a continuous eigenvalue problem based on this mesh. The method also includes computing, at appropriate mesh nodes, values for pressure, velocity components, and meniscus surface deformation corresponding to a suitable number of least-damped late-time oscillation modes of the liquid and computing an angular frequency and damping rate of these least-damped late-time oscillation modes from the discrete version of the continuous eigenvalue problem. The method also includes identifying the mode that has the lowest damping rate and computing a liquid relaxation time by inverting the damping rate of the identified mode.

The invention discloses a near-field electrospinning temperature control spray head for solving local electric field gathering and a printing method thereof, belongs to the technical field of near-field electrospinning spray heads, and is suitable for a polymer solution or melt near-field electrospinning process. The spray head device comprises a nozzle module, a temperature control module, a feeding barrel and a shell, uniform electric field distribution is formed by optimizing the geometrical shape of a nozzle, jet flow stability is improved, the electric field gathering phenomenon is reduced, and then fiber arrangement precision and interlayer stacking consistency are improved; the temperature of the spinning material is accurately adjusted, and it is ensured that the material is subjected to spinning operation at the optimal temperature. The electrospinning nozzle module can be used as an electrospinning nozzle module to be combined with any three-dimensional motion platform, the requirement for manufacturing high-precision fiber structures is met, the electrospinning nozzle module is particularly suitable for preparing micro-nano fiber structures in biomedicine, flexible electronics and the like, and the problems that in the prior art, jet flow is unstable, and fiber accumulation is uneven are solved.

The invention discloses a method for designing a fuel nozzle of a pre-combustion chamber of an engine, which comprises the following steps of: determining the fuel flow and the fuel supply pressure range of the nozzle, and determining the atomization taper angle of the nozzle according to the fuel distribution; determining the effective section coefficient of the nozzle; determining the geometric characteristic number and the flow coefficient of the nozzle; calculating the area of a nozzle and the radius of a cyclone chamber of the centrifugal nozzle; calculating the size of a rotational flow port; calculating the performance of the fuel nozzle; the atomization taper angle and the atomization quality are adjusted through the nozzle structure. According to the centrifugal nozzle, the divergence angle structure is designed at the straight section of the nozzle so that fuel distribution can be adjusted conveniently, the atomization quality can be improved, a cavity is formed by fuel at the divergence angle of the nozzle, the temperature of the fuel is reduced, the cavity is gradually filled, the fuel distribution range is enlarged, and the low-temperature atomization performance of the centrifugal nozzle can be improved.