围压下自振空化射流冲蚀性能实验研究

自振空化射流是利用瞬态流和水声学原理调制而成的一种新型射流,为研究围压下自激振荡空化射流的冲蚀破碎规律,利用高压釜装置测量了1.0mm出口直径的风琴管自振空化喷嘴在各种射流参数情况下冲蚀铝试样的冲蚀质量,并与同等条件下锥形喷嘴冲蚀效率进行了对比。测量结果表明,冲蚀质量基本与射流压力成正比;存在最优喷距和围压,使得冲蚀效果最佳,在本实验条件,分别为喷嘴出口直径的5～7倍和2MPa左右;相同条件下,自振空化喷嘴冲蚀质量约为同等条件下锥形喷嘴冲蚀的1～2倍,这为自振空化射流提高钻井速度等实际应用提供了实验依据。     

Contouring spike nozzles and determining the optimal direction of their primary flows

Problems related with the optimal contouring of two-dimensional and axisymmetric spike nozzles providing maximum thrust for given dimensions and external pressure are studied. The nozzles under consideration are self-adjustable which is ensured by the non-zero inclination of their primary supersonic flow to the plane (axis) of symmetry. Along with the optimal contouring of the spike, the optimal orientation of the “primary” nozzle producing the primary flow is obtained. In the exact formulation, its optimal inclination is determined by an exhaustive search for the configurations providing maximum thrust for a given spike length and various fixed inclinations of the primary nozzle. The spike and primary nozzle contours of these configurations are generally joined through a bend with the formation of an expansion fan in the flow around the bend. The efficiency of a simpler approximate method for contouring the spike and determining a near-optimal inclination of the primary nozzle is demonstrated. The method is based on passage to a modified formulation of the problem differing from the original one in that it is only the part of the spike extending beyond the primary nozzle edge that is preassigned rather than its entire length. In the modified formulation, there is no a bend in the flow around which an expansion fan could be formed, while the inclination of the primary nozzle is determined in the process of designing the unique optimal configuration.     

A procedure for the design of nozzles used for the production of turbulent liquid jets

Where turbulent liquid jets are used for cutting and mining purposes the pressure generated by impact must be maximized. Initial jet behaviour has an important influence on subsequent jet impact pressures at medium range. Nozzle wall boundary layer history has a strong influence on the initial jet, and certain boundary layer features can be linked to poor jet performance. The procedure outlined in this paper was developed to eliminate new nozzle designs or changes in operating conditions on the grounds of badly behaved nozzle boundary flow. The design procedure consists of a potential flow analysis and a boundary layer analysis coupled to empirical correlations for boundary layers in accelerated flows. The procedure is exemplified by application to the design of a nozzle to be used for the specific purpose of mining china clay.     

Extension of Ovsyannikov's Analytical Solutions to Transonic Flows

The solution of the equation of the velocity potential of a steady axisymmetric ideal-gas flow in the neighborhood of a given point at the axis of symmetry in the form of a double series in powers of the distance to the axis of symmetry and its logarithm is considered. Recurrent chains of equations with arbitrariness in two analytical functions of the streamwise variable are obtained for coefficients of the series. Convergence of the constructed series is proved by the method of special majorants. The theorem of existence and uniqueness of the solution of the initial-boundary problem for this nonlinear differential equation in partial derivatives with a singularity at the axis of symmetry is obtained as an analog of Kovalevskaya's and Ovsyannikov's theorems. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 46, No. 6, pp. 14–25, November–December, 2005.     

小口径轴对称收缩喷嘴射流冲击大平板噪声指向特性研究

实验研究了3毫米口径轴对称收缩喷嘴在各种压比下射流垂直冲击和倾斜冲击坚固大平板产生的噪声的指向特性。发现噪声在过平板法线和喷嘴轴线的平面内呈近似四瓣分布，当喷嘴与平板距离减小时，指向壁射流下游的瓣得到增强，反之，指向喷嘴上游的瓣得到增强。喷嘴压比增加时，指向壁射流下游的瓣得到增强，反之，指向喷嘴上游的瓣得到增强。根据自由射流噪声的基本指向特性、射流冲击噪声基本指向特性、声波在平板处发生镜面反射和声波能量叠加的设定，建立了一个冲击射流总体噪声指向特性的模型，成功解释了实验结果，并揭示了形成冲击射流总体噪声指向特性的内在机理。     

基于超声振动的微液滴生成装置设计与实验研究

设计了一种基于V型直线超声电机驱动的微液滴生成装置用于制备具有微米级尺寸的微液滴.此装置由基于V型直线超声电机驱动的微液滴生成部件、基于V型直线超声电机的三维位移控制平台和基于压电振子的微液滴分离部件组成.其中,生成部件包含超声电机、医用注射器、硅胶软管和自制的玻璃基微喷嘴.利用控制器驱动直线超声电机高精度地移动,由滑台推动注射器,在玻璃基喷嘴尖端产生附着的微小液滴;再利用压电振子激发杆状喷嘴的固有振型,使得附着的液滴克服粘性力从微喷嘴尖端分离,落在一定的范围内, 并计算生成的球形微液滴的半径.以蒸馏水作为初始液体,探究此装置生成的微液滴的特性.研究结果表明,蒸馏水在直线电机的精密驱动下,在微喷嘴尖端形成附着的球冠状液滴.通过分离部件的振动,附着的液滴克服自身的粘性力从喷嘴尖端分离, 形成球形液滴,通过测量得出此装置生成的球形液滴的半径小于40 μm.     

Calculating the Thrust Characteristics of Nozzles from Their Outlet Cross-Section Parameters

Within the framework of boundary-layer theory, simple formulas are presented for finding the viscous loss from the gas parameters in the nozzle outlet cross-section. The analysis is performed for ordinary Laval nozzles and spike nozzles. It is found that for nozzles with large expansion ratios the viscous loss is almost independent of the outlet cross-section parameters and is determined only by the parameter values on the nozzle contour. The effect of the longitudinal nozzle curvature on this loss is investigated. It is shown that the viscous losses calculated from the nozzle outlet parameters and by integrating along the nozzle contour with account for the longitudinal curvature fully coincide.     

电流串联双调压喷嘴试验台测控系统设计

喷嘴是发动机推进室的重要组成元件,通过研究其工作原理,根据流量特性检测需求,设计了一套集硬件线路设计和工艺采集于一体的喷嘴试验台测控系统。针对系统电路进行改造,利用信号传输特性设计了电流串联回路,解决了传感器重复使用的问题。建立以太网通信,利用Labview创建共享变量调用PLC数据,设计了阶梯式双调压采集系统,提高了试验工况和参数采集的精度。实验表明,系统可以通过上位机界面实现信号的实时采集以及数据处理、记录与分析等功能,试验工况误差达到1%。     

Bending-torsional stability analysis of aerodynamically covered pipes with inclined terminal nozzle and concurrent internal and external flows

Stability analysis of a cantilevered pipe with an inclined terminal nozzle as well as simultaneous internal and external fluid flows is investigated in this study. The pipe is embedded in an aerodynamic cover with negligible mass and stiffness simply to streamline the external flow and avoid vortex induced vibrations. The structure of pipe is modeled as an Euler–Bernoulli beam and effects of internal fluid flow including flow-induced inertia, Coriolis and centrifugal forces and the follower force induced by the exhausting jet are taken into account. In addition, neglecting the compressibility effect and using the unsteady Wagner model, aerodynamic loading is determined as a distributed lateral load for any generic structural state. The integral form of coupled equations of motion are obtained using the Hamilton’s principle. Solution to the coupled flexural–torsional equations of motion is realized via the extended Galerkin method. After discretization of the equations of motion, an eigenvalue representation of the problem is obtained. Several parameter studies are then conducted to examine the effects of concurrent fluid flows and other related parameters on the stability margins of the system.