喷管

Laval喷管内高速混合气的流场研究

Flow Field of High - speed Mixture in Laval Spray Tube

喷管末端设有清理口，当料浆堵塞喷嘴时，可通过清理口用铁条将堵塞的喷管疏通。

The end of spray tube is arranged with a clean opening , therefore , when the nozzle is blocked by slurry , user can use iron bar to clean the blocked nozzle tube from the clean opening .

截断的喷管具有较大的推力。

The truncated nozzle is found to have a higher thrust .

在暴风雨季，这东西被用作喷管来排水。

This acts as a spout to drain off water during a rainstorm .

固体火箭喷管排气中的粒子分布关于｛x／n｝的分布

Distribution of the particle diameters in the jet exhaust of solid rocket motor

喷管流场数值仿真CFD／Nozzle软件包设计

Design of cfd / nozzle software for numerical nozzle flow simulation

通过进行ADAMS与ANSYS之间的双向数据交换，对该喷管弹性机构构件进行了动态应力分析。

Through bidirectional data interchange between ADAMS and ANSYS , dynamic stress analysis of this elastic mechanism is conducted .

通过基于Fluent软件的流体仿真证明了在实验条件下拉伐尔喷管能够处于系统需要的工作状态。

Through Fluent , I prove that under experiment condition , de Laval nozzle can be in the working status .

CCD探测器在多维动态测量中的应用（柔性喷管六自由度光电实时测量系统）

The Application of CCD Detectors to the Multi-dimensional Dynamic Measurement ( The Opto-Electronic Real Time Measuring System for Six-Freedom Motion Parameters of Flexible Nozzle )

在试验基础上定量地提出了考虑喷管内的流动损失时Wilson点位置的确定方法。

The method of rationally defining the Wilson point based on experiments is given with due consideration of flow loss in nozzle .

本文描述了列阵喷管喉道高度为0.8毫米，马赫数为4.3的CO2气动激光器的实验装置和测量结果。

An experimental device of CO2 gasdynamic laser having an array of nozzles with a throat height of 0.8mm and a Mach number of 4.3 is described and its test results presented .

重点介绍了EFE型发动机的风扇加力燃烧室、喷管系统设计改进的特点。

Design improvement characteristics of EFE fan afterburner and nozzle system are particularly discussed .

从NS方程出发，采用二阶精度的NND格式对塞式喷管的流场进行了数值模拟。

The numerical simulations of the flow field around and aerospike nozzle cell were completed base on N S equations with Second order NND scheme .

用小型电弧加热器对筛形喷管CO2-N2超音速混合气动激光器进行了实验研究。

Experimental study on a CO_2-N_2 supersonic mixing GDL with a screen nozzle was performed on a small scale electric-ar (?) heater .

本文运用NND显式差分格式，计算了三维喷管气流场。

Non-oscillatory and Non-free parameter Dissipation ( NND ) difference scheme was used to calculate three dimensional nozzle flows .

采用时间推进求解N-S方程的方法数值模拟了二维推力矢量喷管内流场和性能。

The flow field and performance of the nozzle were also analyzed by the computation of Reynolds averaging N S equations with the time marching finite volume method .

利用RTR技术发展了一种新的研究热试车条件下SRM喷管两相流的实验方法。

A new experimental method combined with RTR techniques was developed to study the distribution pattern of particles in SRM nozzle during static firing test .

喷管口用Prandtl-Meyer流公式；

In the exits of the nozzle the Prandtl-Meyer flow formula is used .

针对矢量喷管和发动机综合控制系统，本文采用了PID控制算法和基于单神经元自适应控制，有效的减小矢量喷管偏转对发动机工作状态的影响。

Both the PID control and the single neutral cell based self-adaptive control algorithm are adopted in the integrated control system . These two control methods are satisfied to minimize the effects on engine 's working conditions as the nozzle is deflexed .

基于化学平衡和化学动力学理论，用C++和FORTRAN编写了液体火箭发动机喷管性能一维计算软件。

Based on the theory of chemical equilibrium and kinetic methods , one software for one dimensional nozzle performance calculation written by C + + and FORTRAN is introduced in this paper .

用激光诱导碘荧光的方法对高超音速低温喷管的混合性能进行了测量，并用CFD软件FLUENT模拟了喷管的流场。

The flowfield of hypersonic low temperature ( HYLTE ) nozzle in continuous wave DF / HF chemical lasers was visualized by laser induced iodine fluorescence ( LIIF ) and simulated by the CFD software FLUENT .

通过数值仿真，对设计推力为1N的微推进器喷管在高空工况的内流场和真空羽流场进行了研究。

The numerical simulation was used to analyze the flow field of inner nozzle and its vacuum plume for 1N thruster in a vacuum .

采用FLUENT流动计算软件对某空射型导弹发动机的喷管及羽流流场进行了一体化的数值仿真研究，分析了导弹飞行高度和马赫数对喷管羽流流动的影响。

The numerical simulation of the nozzle and plume flow field of a rocket motor launched from air was performed using FLUENT software . The influence of flying altitude and Ma number on the plume flow was analyzed .

用Fluent计算流体力学软件对固体火箭发动机喷管流场进行了数值计算，研究了喷管收敛半角、喷管喉部上游圆弧曲率半径和喉部圆柱段长度对喷管流场的影响。

Nozzle flow field of SRM was numerically simulated with Fluent software . The effects of nozzle convergent half angle , radius of curvature on upstream of throat section and length of throat cylinder on flow field are investigated .

该算法是M.C.有摩阻渐缩喷管的计算

The algorithm is an extension of the two-valued cover-most algorithm proposed by M. C. The Calculation of Tapered Nozzle with Friction

全文取得了如下成果：（一）用特征线加附面层修正的方法设计了M8型面喷管，并在M8喷管的基础上采用喉道拟合的方法生成M7喷管。

The main achievements are summarized as follows : ( I ) The M8 nozzle contour is designed by the characteristic line and the bound layer correction .

C-103铌合金可延伸喷管成形工艺及冷展试验

The manufacturing process and the cold deployment test of an extendible nozzle exit cone made of niobium alloy

主喷管喉道直径为35mm，进口总温和总压分别为800K及274.4kPa。

The nozzle throat diameter was 35 mm , and the inlet stagnation temperature and pressure were 800 K and 274 4 kPa , respectively .

以10kW级脉冲式CO2激光器为光源，三次反射激光推力器为对象，进行了两种方式下两种喷管的热防护初步实验研究。

Initial investigation was carried out on the two types of thermal protection of the two nozzle types , in which a pulsed 10 kW CO_2 laser and a three-reflection laser thruster were employed .

用此程序对低压范围的Laval喷管流动进行了计算，所得结果与已有结果符合较好。

When it is used to calculate the wet steam flow in a low pressure Laval nozzle , the results obtained for the position of the Wilson point and wetness fraction agree quite well with existing experimental data .