涡轮叶栅气热耦合数值方法与验证

应用三阶精度TVD格式和自由型曲面阿格技术,对涡轮内冷叶片进行气热耦合数值模拟.结合商用软件采用多种湍流模型计算方法的结果进行实验验证和对比分析,结果表明,商用软件采用传统湍流模型对温度边界层的模拟是不合理的,采用考虑转捩的湍流模型,调整转捩起始雷诺数,可以较好地模拟温度边界层的热传导.本文对非转捩区边界层温度的计算结果与实验结果吻合较好.     

内螺纹强化管传热和阻力特性

本文提供了7个内径为15.54mm的内螺纹粗糙管单相流动的传热和阻力数据,为当前商用粗糙管常用尺寸提供了一系列新的内部强化数据.螺纹管结构参数为螺纹数(18～45),螺旋角(25°～45°)、螺纹高(0.33mm至0.55 mm).测试管由于螺纹处流动分离及表面积的显著增加而得到强化.测试数据范围为5.08≤Pr≤6.29.利用两种关联式来预测不同几何变量和雷诺数下St和摩擦系数.多重回归传热关联式的平均差分别为2.9%和3.8%.传热和摩擦关联式基于粗糙表面热量-动量传输比拟,标准差为分别是1.4%和5.4%.关联式能够合理地预测商用螺纹粗糙管的传热和摩擦.     

Vortex Structures and Behavior of a Flow Past Two Rotating Circular Cylinders Arranged Side-by-Side

We present a study on the vortex structures and behavior of a flow past two rotating circular cylinders arranged side-by-side at a range of absolute rotational speeds （｜a｜≤2） for two different gap spacings g＊= 1.5 and 0.7 at Reynolds numbers Re = 160 and 200. The results show that the flow becomes stabilized and finally steady beyond the critical rotational speed as ｜a｜ increases, regardless of the variation in Re and g＊. The value of critical rotational speed increases with increasing Re. The wake patterns change in the unsteady regimes for g＊ =1.5 and 0.7. With increasing ｜a｜, the time-averaged drag coemcient CD decreases and the lift coemcient CL increases, respectively. CD at Re = 160 and g＊ = 0.7 decreases rapidly, resulting in the smallest value at the same ｜a｜ for 1 ≤ ｜a｜≤ 2. CD augments with increasing g＊ at the same ｜a｜. For g＊=1.5, CD has a little disparity between the cases of Re= 160 and 200. For the flow past two still cylinders, CL is inversely proportional to g＊ of two cylinders for a fixed ｜a｜, and is not dependent on Re.     

建立微尺度蒸发冷凝的通用准则

蒸发冷却模式以及微换热器,是最具有潜力的冷却高热流密度电子器件的方法之一。总结和研究微尺度蒸发冷凝相变机理,是本文研究目的。我们在参阅大量文献和提取大量精确数据的基础上,发现了新的区分常规通道与微通道的临界准则Bo×Re1^0.5=200;在此基础上,我们归纳出了新的预测微通道压降、传热系数和临界热流量的关联式,与以前...     

Scale-adaptive simulation of flow past wavy cylinders at a subcritical Reynolds number

The Xu & Yan scale-adaptive simulation (XYSAS) model is employed to simulate the flows past wavy cylinders at Reynolds number 8 × 10 3.This approach yields results in good agreement with experimental measurements.The mean flow field and near wake vortex structure are replicated and compared with that of a corresponding circular cylinder.The effects of wavelength ratios λ/D m from 3 to 7,together with the amplitude ratios a /D m of 0.091 and 0.25,are fully investigated.Owing to the wavy configuration,a maximum reduction of Strouhal number and root-meansquare (r.m.s) fluctuating lift coefficients are up to 50% and 92%,respectively,which means the vortex induced vibration (VIV) could be effectively alleviated at certain larger values of λ/D m and a /D m.Also,the drag coefficients can be reduced by 30%.It is found that the flow field presents contrary patterns with the increase of λ/D m.The free shear layer becomes much more stable and rolls up into mature vortex only further downstream when λ/D m falls in the range of 5-7.The amplitude ratio a /D m greatly changes the separation line,and subsequently influences the wake structures.     

模型昆虫翼作非定常i运动时的气动力特性

基于Navier-Stokes方程的数值解,研究了一模型昆虫翼在小雷诺数(Re=100)下作非定常运动时的气动力特性.这些运动包括翼启动后的常速转动,快速加、减速转动,常速转动中快速上仰(模拟昆虫翼的上挥或下拍、翻转等运动).有如下结果在小雷诺数下,模型昆虫翼以大攻角(α=35°)作常速转动运动时,由于失速涡不脱落,可产生较大的升力系数.其机理是翼转动时,翼尖附近(该处线速度大)上翼面压强比翼根附近(该处线速度小)的小得多,因而存在展向压强梯度,同时存在着沿展向的离心力,此展向压强梯度和离心力导致的展向流动在失速涡的轴向方向,其可避免失速涡脱落.模型昆虫翼在快速加、减速转动和快速上仰运动中,虽然雷诺数小,但由于在短时间内产生了大涡量,也可产生十分大的气动力,例如在快速上仰运动中,升力系数可大于10.     

返回舱高雷诺数再入过程底部流动稳定性

返回舱高雷诺数再入过程中存在肩部高热流、底部阻力无法准确预测以及非定常振动等问题,解决此类问题的关键是分离和转捩等物理现象的准确识别. 本文采用大涡模拟方法细致刻画了返回舱类钝体外形在高雷诺数再入过程中的分离和转捩等物理现象,获得了返回舱底部流动形态以及稳定性特征. 从肩部剪切失稳、底部流动结构失稳、尾迹发展区以及远尾迹区的耦合失稳等多个角度分析了返回舱外形的底部流动失稳机制.研究发现, 返回舱类外形底部流动稳定性主要存在两类失稳模式即肩部剪切失稳模式以及底部流动结构失稳模式,二种模式存在耦合效应, 同时在远尾迹湍流区域存在类卡门涡街的振荡行为.这些认识为理解返回舱外部扰动因素对底部流动的作用机理及返回舱稳定性控制提供了基础理论支撑.      

Slip effects on streamline topologies and their bifurcations for peristaltic flows of a viscous fluid

We discuss the effects of the surface slip on streamline patterns and their bifurcations for the peristaltic transport of a Newtonian fluid. The flow is in a two-dimensional symmetric channel or an axisymmetric tube. An exact expression for the stream function is obtained in the wave frame under the assumptions of long wavelength and low Reynolds number for both cases. For the discussion of the particle path in the wave frame, a system of nonlinear autonomous differential equations is established and the methods of dynamical systems are used to discuss the local bifurcations and their topological changes. Moreover, all types of bifurcations and their topological changes are discussed graphically. Finally, the global bifurcation diagram is used to summarize the bifurcations.     

雷诺数效应对翼型抖振特性的影响

飞行器抖振是一种非线性气动弹性问题,当飞行器进入抖振阶段时,将会对飞行器的性能产生严重影响。而在跨声速条件下,激波附面层相互作用会诱导机翼抖振。本文开展了跨声速条件下翼型抖振特性雷诺数效应的实验研究,揭示了翼型跨声速抖振起始迎角、激波运动前缘边界、频谱特性、抖振频率与雷诺数变化的基本规律。结论如下:雷诺数变化会导致抖振起始边界的改变,对抖振起始迎角下的功率谱密度峰值有明显影响;随着雷诺数的增大,激波运动的前缘后移。雷诺数变化对抖振频率有明显影响,随着马赫数增大,雷诺数效应增强。     

比萨斜塔实验中两球落地时间的计算

考虑空气阻力的影响,计算了比萨斜塔实验中两小球的落地时间.