A comparative study of jet formation in nozzle‐ and nozzle‐less centrifugal spinning systems

Centrifugal spinning, a recently developed approach for ultra‐fine fiber production, has attracted much attention as compared with the electrospinning, due to its high yield, no solution polarity and high‐voltage electrostatic field requirements, etc. In this study, the jet formation process and spinning parameters on jet path are explored and compared in nozzle‐ and nozzle‐less centrifugal spinning systems. For nozzle‐less centrifugal spinning, fingers are formed at the front of thin liquid film due to the theory of Rayleigh–Taylor instability. We find that the lower solution concentration and higher rotational speed favor the formation of thinner and longer fingers. Then, the critical angular velocity and initial jet velocity for nozzle‐/nozzle‐less centrifugal spinning are obtained in accordance with the balance of centrifugal force, viscous force, and surface tension. When jet leaves the spinneret, it will undergo a series of motions including necking and whipping processes, and then, a steady spiral jet path is formed with its radius getting tighter. Finally, we experimentally study the effect of rotational speed and solution concentration on jet path, which shows that the higher rotational speed results in a larger radius of jet path while the solution concentration has little effect on it. © 2014 Wiley Periodicals, Inc. J. Polym. Sci., Part B: Polym. Phys. 2014 , 52, 1547–1559     

Steady-State MHD Flows in Nozzles with an External Longitudinal Magnetic Field

Steady-state MHD flows in channels of the nozzle type in the presence of an external longitudinal magnetic field can be divided into two significantly different classes. Subcritical flows, in which the Alfvén velocity calculated from the longitudinal magnetic field is less than the plasma velocity, have mainly the same properties as flows in a transverse magnetic self-field and their quantitative characteristics depend only slightly on the longitudinal magnetic field strength. Supercritical flows with the opposite inequality for the velocities correspond to strong longitudinal magnetic field. The main difference is the transitions between different forms of energy (kinetic, thermal, and electromagnetic). The present study contains a classification of possible flows, namely, sub- and supercritical and sub-, super-, and transonic flows with respect to the fast and slow magnetosonic and Alfvén velocities. Examples of these flows are given. The effect of the problem parameters on the flow properties is investigated.     

THE INTERACTION OF PLANE SH－WAVES AND NON－CIRCULAR CAVITY SURFACED WITH LINING IN ANISOTROPIC MEDIA

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Distinctive features of the flow past high-speed flight vehicles with air-breathing engines on subsonic,transonic, and low supersonic velocity ranges

The aerodynamic characteristics and distinctive features of the flow past hypersonic integral-layout flight vehicles with air-breathing engines intended for cruise flight in the atmosphere are experimentally investigated. The experiments were conducted on a simplified model designed with regard for the general principles of integration of vehicles of the class considered. The tests were performed in a wind tunnel over the Mach and Reynolds number ranges 0.6 ≤ M ≤ 4 and 6.3 × 10⁶ ≤ Re ≤ 16 × 10⁶, respectively. Balance testing was carried out, the pressure distributions over the vehicle surface were measured, and the flowfields on the model surface were photographed. The effects of mounting a nacelle and contouring the internal duct are considered. The effect of the corrections on the duct flow in the absence of jet modeling is estimated. The results obtained can be used as a basis for developing the aerodynamic configurations of integral-layout flight vehicles, for forming their thrust and aerodynamic parameters under full-scale flight conditions, and for testing computation methods.     

小口径轴对称收缩喷嘴射流冲击大平板噪声特性的实验研究

为研究小口径喷嘴冲击射流的噪声特性，测定了3mm口径的轴对称收缩喷嘴在各种压比情况下产生的亚音速和超音速射流冲击坚固大平板产生的噪声。发现噪声在空间呈近似四瓣分布，当喷嘴与平板距离减小时，噪声指向壁射流下游的瓣到增强，反之，噪声指向喷嘴上游的瓣得到增强。噪声随喷嘴距平板距离的增加呈增强的趋势，在距平板一定距离内有锯齿现象。噪声随喷嘴压比的增加而增强，相应于各种工况，存在一不同的压比值，此压比之前，噪声随压比的增大而迅速提高，但有起伏现象，在此压比之后，噪声平缓地随压比的增大而增强。     

Study of the Aerodynamic Characteristics of Chevron Nozzles on the Basis of a Numerical Calculation of the Flowfield

The flow in a convergent nozzle equipped with chevrons and the flow around the chevrons are numerically simulated and studied on the basis of the numerical integration of the system of Reynolds equations closed by a differential model for the turbulent viscosity. From the calculated results, the flow pattern, the action of the chevrons on the flow, the circulation generated, and the values of the parameters characterizing the streamwise vorticity are determined. The results of calculations of the thrust and flow-rate characteristics of nozzles equipped with chevrons are presented. The data for chevron and conical nozzles are compared.__________Translated from Izvestiya Rossiiskoi Academii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, 2005, pp. 76–88.Original Russian Text Copyright © 2005 by Brailko and Krasheninnikov.     

Modal dispersion curves of an optical waveguide with a core cross-section partially bounded by one turn of an equiangular spiral under weak guidance approximation

In this paper, we present a theoretical analysis of propagation of electromagnetic waves through a fiber with a spiral shape core cross-section with two cases. In one case the remaining unbounded part closed by a straight line and in other case remaining part not bounded by well defined line. Using Goell's point matching method under weak guidance condition modal characteristic equations for the lowest order modes are derived. The comparison of dispersion curves for two cases is also shown and interpreted.     

低功率电弧加热发动机喷管扩张段内壁面温度测量

采用滤光成像,摒弃电弧及羽流干扰,实验获得了采用纯氮、纯氢以及氢-氮混合气为推进剂时,低功率电弧加热发动机喷管内壁面的热辐射强度分布。通过辐射强度-温度标定以及图像分析,导出了相应的温度分布。实验结果表明,喷管扩张段内壁面温度最高处位于喉道出口附近。采用不同推进剂时,喷管内壁面温度分布情况有显著区别。     

时间分辨原子发射光谱诊断脉冲放电气体束等离子体

建成了一套脉冲放电气体束和原子发射光谱等离子体诊断实验装置,利用这套实验装置测量了不同放电条件下等离子体的时间分辨发射光谱,并采用玻尔兹曼作图法和Hα谱线斯塔克展宽法研究了等离子体的原子温度、离子温度和自由电子密度等参数的演化。实验结果表明,脉冲放电的总电量对等离子体参数的演化有较大影响;脉冲放电气体束等离子体中的离子温度远高于原子温度,自由电子密度相对较低,等离子体处于非局域热平衡状态。A special designed pulsed discharge nozzle (PDN) ion source and a plasma diagnostics system based on the atomic emission spectroscopy were constructed. The time-resolved emission spectra of Argon atoms and ions in the region of 300-800 nm were observed and analyzed. The plasma temperatures, including atomic and ionic temperatures, were simulated by Boltzmann plot method, and the free electron density was simulated through the Stark broadening of Hα line. The evolution of these plasma parameters were investigated by high-resolution time-resolved emission spectra. The results show that the total energy struck on the pulsed gas beam is the most important factor which determines the plasma properties and its evolution. The plasma in PDN is concluded into non-local thermodynamic equilibrium (non-LTE) during the evaluation because of the low electron density and the big difference between the temperatures of Argon atoms and ions in all discharge conditions.     

IR signature study of aircraft engine for variation in nozzle exit area

In general, jet engines operate with choked nozzle during take-off, climb and cruise, whereas unchoking occurs while landing and taxiing (when engine is not running at full power). Appropriate thrust in an aircraft in all stages of the flight, i.e., take-off, climb, cruise, descent and landing is achieved through variation in the nozzle exit area. This paper describes the effect on thrust and IR radiance of a turbojet engine due to variation in the exit area of a just choked converging nozzle (M_e = 1). The variations in the nozzle exit area result in either choking or unchoking of a just choked converging nozzle. Results for the change in nozzle exit area are analyzed in terms of thrust, mass flow rate and specific fuel consumption. The solid angle subtended (Ω) by the exhaust system is estimated analytically, for the variation in nozzle exit area (A_ne), as it affects the visibility of the hot engine parts from the rear aspect. For constant design point thrust, IR radiance is studied from the boresight (ϕ = 0°, directly from the rear side) for various percentage changes in nozzle exit area (%ΔA_ne), in the 1.9–2.9 μm and 3–5 μm bands.