Experimental investigation of the effect of nozzle numbers on Ranque–Hilsch vortex tube performance

The present study investigates the effects of the orifice nozzle number and the inlet pressure experimentally on the cooling performance of the counter flow-type vortex tube. The energy generation has been conducted using a stream-tek generator (model GNMD-KIT) with different numbers of nozzles (2, 3, and 6), an aspect ratio of 1:6, and an inner diameter of 7.5 mm. In the experiments, for each of the orifices, inlet pressures have been adjusted from 200–600 kPa. The energy separation investigated here focuses on the cold temperature difference and coefficient of performance for cooling. The experimental results concluded in this article prove that the greatest effect of nozzle number is for three nozzles, and hence, that nozzle number could affect the energy separation efficiently. A comparison of the present experiments with other published works has been conducted. An analytical study of the characteristics equation has been carried out to evaluate the best correlation of the ratio of cold temperature difference to the inlet temperature as a function of pressure, cold mass fraction, and nozzle number.     

三流道喷嘴涡流管能量分离特性的研究

涡流管是一种可以产生冷热分离效应的结构简单的装置,尽管其在结构和操作上非常简单,但管内发生的能量交换过程却极其复杂。以压缩空气作为涡流管的工作介质,对涡流管能量分离特性进行了实验研究,获得了涡流管制热效应、制冷效应与进气压力以及冷流率之间的关系。研究结果表明:在冷流率 μ_c<85％时,喷嘴进口压力愈高,三流道喷嘴涡流管的制冷效应愈好,制热效应也愈好;冷流率愈高,三流道喷嘴涡流管的制冷效应愈差,但三流道喷嘴涡流管的制热效应愈好。     

涡流管性能的热力学分析

涡流管是一种新型的能量分离装置,热力学参数和几何参数对其的性能影响很大。该文依据热力学第一、第二定律,建立了涡流管能量分离过程热力学模型,将不可逆过程可用能损失归结为热量火用收益和压力损失两部分,获得了一种基于热力学火用分析的涡流管性能优化新途径。结合不同进气压力、喷嘴数和冷端出口直径的涡流管能量分离性能实验,得到上述诸因素对涡流管能量分离过程中火用变化的影响,通过对能量分离过程中热量火用收益和压力损失的比较,实现了涡流管能量分离性能的优化设计。     

基于涡流管能量分离效应的温度分布实验研究

在入口温度、压力不变的条件下,改变冷流比,分别对不同冷流比工况下的涡流管内温度分布进行了实验测试,同时对不同冷流比工况下的实验结果进行比较,研究表明:在同一轴向端面处,温度由轴心向壁面呈现不断增大的趋势,在壁面附近处达到最大值;在同一径向位置处,温度随着轴向位置的增大不断增大,在涡流室的轴心处,温度达到最低,而在热端出口的壁面处,温度达到最大。在冷流比为0.1563时,温度沿径向呈增大趋势,而在冷流比为0.7158时,温度沿径向呈现先降低后增大的趋势;在实验研究范围内,同一测点处,温度随冷流比的增大而增大。     

新型涡流管的制冷特性研究

以新型涡流管为研究主体,通过实验,研究涡流管操作参数对涡流管性能的影响。根据实验数据,分析改变温度压力等操作参数对涡流管能量分离效应的影响。试验结果表明:当提高涡流管进气温度,其冷热两端出气温度升高,但并不影响涡流管的制冷效率;增加涡流管进气压力会提高涡流管制冷效应,并在冷流率为0.2时效果最明显;制冷效率随节流阀开度增加而增加且最终趋于稳定,而制热效率则随节流阀开度增加而减小并最终趋于稳定。     

小流量涡流管特性的实验研究

本文用实验方法研究了小流量涡流管制冷的特性。实验中分别对入口压力和工质等因素对涡流管特性的影响进 行研究。在实验中发现了涡流管冷端制热和热端制冷的反常现象,并对其进行了解释。     

Numerical study on combustion of H2—O2 in a supersonic reactive expansion in a nozzle

A study on expansion flow inside a nozzle considering full mechanism chemistry of hydrogen and oxygen was carried out. In this study, a full implicit scheme for turbulent reactive flow was obtained by combining the second order TVD scheme of Yee and Harten (1987, Implicit TVD schemes for hyperbolic conservation laws in curvilinear coordinates. American Institute of Aeronautics and Astronautics Journal, 25(2), 266–274) with the efficient implicit lower-upper scheme of Shuen and Yoon (1989, Numerical study of chemically reacting flows using a lower-upper symmetric successive overrelaxation scheme. American Institute of Aeronautics and Astronautics Journal, 27(12), 1752–1756). The species equations, Navier–Stokes equations and turbulence model were implemented in the numerical scheme and solved in conjunction with full detailed finite rate chemistry. The numerical scheme is verified by comparison with experimental results of a converging–diverging nozzle. Effects of inlet pressure, temperature and fuel-oxidant mass ratio on nozzle flow field were studied. Variation of chemical species under different conditions was investigated by considering a chemical mechanism. Results show that increasing inlet pressure increases the rate of reactions due to increasing the concentration of reactants. For lower inlet pressure the radical H increases slightly in the diverging part of the nozzle, while for higher pressures it decreases along the nozzle. Inlet fuel–oxidant mass ratio affects the variation of all species with a greater effect for a near stoichiometric ratio. It was also shown that a higher inlet temperature provides a more enhanced reaction zone in the diverging part of the nozzle.     

涡流管能量分离过程实验研究

利用涡流管部分轴线温度测量实验装置,考虑到进气压力和涡流室结构对涡流管能量分离过程的影响,针对不同进气压力和不同涡流室结构的涡流管部分轴线温度分布进行了实验研究。根据实测结果,得到了进气压力及涡流室几何结构对涡流管部分轴线温度分布的影响曲线。在此基础上,根据实验结果并结合热力学原理对涡流管制冷的物理行为作了分析。结果表明:涡流导致涡流室中心区域气流膨胀是涡流管产生制冷效应的一个重要原因。     

微通道脉管非线性交变振荡微观机理的分子动力学研究

采用分子动力学方法,对He在微通道脉管内的非线性交变振荡的热力学响应进行仿真,研究气体振荡诱导管内轴向压力梯度、温度场的形成,并阐述微通道长径比对温差与相位的影响.结果表明：微通道内伴随压差驱动力在管内形成类似正弦函数压力波、速度波、质量流量波与半正弦的温度波.振荡周期随脉管管径的增大而缩短,随脉管长度的增加而增长,受直径影响很小;微通道两端的时均温差随长度的增加而增大,受直径的影响很小.预测针对不同的脉管直径存在一个最佳长径比与振荡周期,其数值随直径的增大而增大,为优化脉冲管的性能提供理论依据.     

翅片管气化器管内相变传热流动数值模拟

采用Fluent多相流混合物模型,通过用户自定义程序(UDF)实现了液氮相变模拟,模拟了不同进口流速对翅片管气化器管内流体换热量、压力降、含气率及汽化体积的影响,并分析了各参数随进口流速改变而变化的原因。由数值模拟可知,翅片管内流体进出口焓差、含气率及单位质量汽化体积随进口流速的增加而减少,而压力降和总换热量随进口流速的增加而增大,其中压力降增大的主要原因是由加速压降引起。     

垂直圆管内顶部骤冷过程骤冷温度特性实验研究

本文研究了低压低质量流速条件下垂直圆管管内顶部骤冷过程中骤冷温度的分布特性。采用瞬态热块实验技术和非稳态两维数值分析技术，得到了实验段内壁温度随时问的分布规律：以此为基础，采用双切线交点模型，确定骤冷前沿点的位置，温度和时间，以相应的骤冷温度理论关系式为基础，同时考虑管道内流动参数对骤冷温度的影响，建立了本文的骤冷温度半经验关系式模型和半经验关系式。     

Acoustic disturbance from gas non-uniformities convected through a nozzle

The non-steady flow generated by convection of gas containing non-uniform temperature regions or “entropy spots” through a nozzle is examined analytically as a source of acoustic disturbance. The first portion of the investigation treats the “compact nozzle”, the case where all wave lengths are much longer than the nozzle. Strengths of transmitted and reflected one-dimensional waves are given for supersonic and subsonic nozzles and for one configuration of supersonic nozzle with normal shock at the outlet. In addition to a wave reflected from the nozzle inlet, the supersonic nozzle discharges two waves, one facing upstream and the other facing downstream. For reasonable values of the nozzle inlet Mach number, the pressure amplitude of each wave increases directly as the discharge Mach number.The acoustic perturbations from a supercritical nozzle of finite length, in which the undisturbed gas velocity increases linearly through the nozzle, are analyzed for several inlet and discharge Mach number values and over a wide frequency range. The results which agree with the compact analysis for low frequency, deviate considerably as the frequency rises, achieving pressure fluctuation levels of several times the compact values. It is shown that this result originates in a phase shift between the two waves emitted downstream and that the pressure fluctuations for moderate frequencies may be approximated from the compact analysis with an appropriate phase shift.In all cases, the pressure fluctuations caused by a 2% fluctuation in absolute inlet temperature are large enough to require consideration in acoustic analysis of nozzles or turbine blade channels.     

喷雾腔压力及喷嘴孔径对相变喷雾冷却性能的影响

为了满足大功率激光器件高热流密度及低表面温度的冷却需求,以R22为冷却工质,实验研究了在闭式系统中改变喷雾腔压力及喷嘴孔径对相变喷雾冷却中临界热流密度、冷却温度等冷却性能的影响,实验结果表明:在喷雾入口压力为0.8 MPa,喷雾高度为22 mm,入口温度为-3 ℃的实验条件下,当喷雾腔压力在0.2~0.4 MPa范围内变化时,随着喷雾腔压力的升高,临界热流密度值（CHF）先增大后减小,存在最优的临界热流密度,冷却壁面温度随着喷雾腔压力的升高而上升;当改变喷嘴孔径时,CHF存在最优值,过小及过大的孔径均会影响喷雾冷却性能;当喷嘴孔径为 0.4 mm,喷雾腔压力为0.34 MPa时, CHF值最高,为276.1 Wcm-2,其对应的被冷却表面温度为26.8 ℃,表面换热系数为 66 640 Wm-2K-1。     

微通道脉冲管中He气交替振荡的分子动力学模拟

使用非平衡分子动力学模拟方法分析了微通道脉冲管(MPT)中由正弦速度活塞提供驱动力时He气交替振荡的微观动力学过程,并对MPT的冷却机制进行了分析.结果表明,MPT的压缩和膨胀过程之间存在一个交替的振荡过程,两个过程具有不对称的属性分布,膨胀过程具有比压缩过程更大的轴向压力梯度.当充气压力较低时,循环时间对冷端温度的影响很小,但是当充气压力高于20 bar时,冷端温度对时间较为敏感,随着时间的减少,冷端温度进一步降低,而冷端瞬时平均温度随着充气压力的增加而增加.另外,压比随着时间的减少而增加,并且明显不受充气压力的影响,但它会在MPT的轴向上产生较大的温度梯度.综上所述,在热端使用不同形式的换热器和调相元件会释放或回收额外的声功率.固定工作模式和尺寸参数的MPT具有最佳频率,可以在冷端获得最低的空载温度.仿真结果增进了对脉冲管制冷机的认识,并为微通道脉冲管制冷机的优化设计提供理论支持.     

Characteristics of a magnetogasdynamic diffuser under different modes of electric current switching

This paper elaborates upon a previous investigation into the influence of external electric and magnetic fields on a flow through a supersonic diffuser. The aim of the present study is to correlate a change in the configuration of a shock wave emerging near the diffuser inlet at magnetohydrodynamic interaction with the amount of force and energy actions and with total pressure losses. For this purpose, the main parameters of the shock wave structure and the total pressure are measured at the diffuser outlet when the flow is subjected to magnetic and electric fields of various strengths at different routes of current passage. In the experiments, a shock tube with a supersonic nozzle is employed. The shock tube forms a flow behind the shock wave reflecting from the end of the tube, which terminates in the nozzle. The diffuser is located directly downstream of the nozzle. The investigation is carried out in xenon. The flow is subjected to external fields at the inlet of the diffuser. The shock wave structure is visualized by frame sweeping of Schlieren patterns of the flow. The total pressure is measured with a piezoelectric transducer located at the end of the channel. The results obtained make it possible to optimize the action on the flow in terms of power consumption and total pressure losses for a given design of the diffuser.     

三种膨胀装置不可逆损失的比较

本文利用熵法对涡流管、透平膨胀机及节流阀三种装置进行了研究.通过理论分析说明了在相同的工况下,节流阀的(火用)损失最大,涡流管次之,透平膨胀机最接近等熵膨胀.随着入口温度的升高,涡流管的(火用)效率明显的增大,而其它两个变化不大.研究结果对于膨胀制冷机的研究开发具有一定的指导意义.     

涡发生器对高超声速轴对称进气道外部流动的影响

采用三维CFD黏性模拟考察涡发生器对高超声速轴对称进气道外部流动的影响.针对前缘钝化半径0.8 mm和3.2 mm的轴对称进气道外部流场,以涡发生器高度与当地位移边界层厚度比值为影响参数,考察流场结构与性能参数的影响规律.结果表明,涡发生器产生的干扰波系使得前缘激波向外偏移,下游近壁面流动与主流区出现明显的交换,下游流动出现明显的展向非均匀性.涡发生器对流动的影响沿流向逐渐减弱.在气流压缩性能方面,涡发生器下游压比、动压比沿流向开始增大,随后逐渐恢复到无涡发生器工况;Mach数、总压恢复系数开始降低,随后逐渐向无涡发生器工况趋近.涡发生器高度与当地位移边界层厚度的比值h可作为衡量其影响的重要参数.当h≤1.5时,进气道流场结构、性能参数的变化几乎可忽略,h≤3.0时进气道入口处性能参数几乎能够恢复到无涡发生器工况.      

Performances of Transcritical Power Cycles with CO2-Based Mixtures for the Waste Heat Recovery of ICE

In the waste heat recovery of the internal combustion engine (ICE), the transcritical CO₂ power cycle still faces the high operation pressure and difficulty in condensation. To overcome these challenges, CO₂ is mixed with organic fluids to form zeotropic mixtures. Thus, in this work, five organic fluids, namely R290, R600a, R600, R601a, and R601, are mixed with CO₂. Mixture performance in the waste heat recovery of ICE is evaluated, based on two transcritical power cycles, namely the recuperative cycle and split cycle. The results show that the split cycle always has better performance than the recuperative cycle. Under design conditions, CO₂/R290(0.3/0.7) has the best performance in the split cycle. The corresponding net work and cycle efficiency are respectively 21.05 kW and 20.44%. Furthermore, effects of key parameters such as turbine inlet temperature, turbine inlet pressure, and split ratio on the cycle performance are studied. With the increase of turbine inlet temperature, the net works of the recuperative cycle and split cycle firstly increase and then decrease. There exist peak values of net work in both cycles. Meanwhile, the net work of the split cycle firstly increases and then decreases with the increase of the split ratio. Thereafter, with the target of maximizing net work, these key parameters are optimized at different mass fractions of CO₂. The optimization results show that CO₂/R600 obtains the highest net work of 27.43 kW at the CO₂ mass fraction 0.9 in the split cycle.     

实际气体喷管喉部尺寸的设计计算

由于天然气输送中的压力通常较高,因此,天然气不能按理想气体处理。本文详细介绍了采用BWRS方程计算天然气在喷管内流动时喷管喉部临界参数的计算方法、过程以及计算程序编制步骤,计算了不同喷管入口压力下喷管喉部面积,并将之与理想气体状态方程的结果进行了比较。结果表明,在喷管入口压力比较低,设计精度要求不高时,可以采用基于理想气体状态方程的喷管喉部计算公式。但如果天然气压力大,设计精度要求较高时,就必须采用实际气体方程进行喷管设计计算。     

环形HYLTE喷管耦合段及光腔区流场的数值模拟

参考传热学相关理论,估算燃烧室的传热损耗分数及相应的平衡温度,确定了主喷管的入口参数设置。在此基础上,对环形HYLTE喷管的耦合段及光腔区流场进行3维的数值模拟,给出了F原子质量分数、静温、静压的空间分布,得到了光腔区各支谱线的小信号增益系数变化曲线。将计算结果与实验结果进行比对,光谱测量结果及移动光轴实验证实了计算模型的合理性。