Flow control of micro-ramps on supersonic forward-facing step flow

The effects of the micro-ramps on supersonic turbulent flow over a forward-facing step(FFS) was experimentally investigated in a supersonic low-noise wind tunnel at Mach number 3 using nano-tracer planar laser scattering(NPLS)and particle image velocimetry(PIV) techniques. High spatiotemporal resolution images and velocity fields of supersonic flow over the testing model were captured. The fine structures and their spatial evolutionary characteristics without and with the micro-ramps were revealed and compared. The large-scale structures generated by the micro-ramps can survive the downstream FFS flowfield. The micro-ramps control on the flow separation and the separation shock unsteadiness was investigated by PIV results. With the micro-ramps, the reduction in the range of the reversal flow zone in streamwise direction is 50% and the turbulence intensity is also reduced. Moreover, the reduction in the average separated region and in separation shock unsteadiness are 47% and 26%, respectively. The results indicate that the micro-ramps are effective in reducing the flow separation and the separation shock unsteadiness.     

非定常环境下叶栅性能的数值研究

本文采用数值方法对叶轮机基元非定常流和排间匹配进行深入研究。结果表明流动非定常性产生额外损失,滞回现象存在于叶轮机中。而考虑基元非定常流动的叶型设计和排间缘线匹配技术将是未来叶轮机非定常气动设计的核心。     

来流边界层效应下斜坡诱导的斜爆轰波

以超声速预混气中的斜爆轰波为研究对象,对其在来流边界层效应下的特性进行了实验研究.在马赫数为3的超声速预混风洞中,通过斜坡诱导产生了斜爆轰波.当来流的当量比较低时,预混气中产生的是化学反应锋面与激波面非耦合的激波诱导燃烧现象.此时边界层分离区中的化学反应放热将使分离区尺度显著增大,流场非定常性显著增强,激波位置剧烈振荡.当来流的当量比较高时,预混气将产生斜爆轰波.此时边界层分离区会影响到斜爆轰波起爆时的形态.在小尺度分离区下,斜爆轰波起爆时呈突跃结构(有横波);在中等尺度分离区下,流场固有的非定常性使斜爆轰波呈间歇突跃结构;在大尺度分离区下,斜爆轰波起爆则呈完全的平滑结构(无横波).     

Aeroacoustics of duct junction flows merging at different angles

This paper reports an exploratory study of the aeroacoustics of a merging flow at a duct junction with the same width in all branches and different merging angles. The focus is put on the acoustic generation due to the flow unsteadiness. The study is carried out by the direct aeroacoustic simulation (DAS) approach, which solves the unsteady compressible Navier–Stokes equations and the perfect gas equation of state simultaneously using the conservation element and solution element (CE/SE) method. The Mach number based on the maximum inlet velocity of side branch is 0.1 and the Reynolds number of the flow based on duct width and this velocity is 2.3×10⁵. The numerical simulations are performed in two dimensions and the aeroacoustics at different merging angles (30°, 45°, 60° and 90°) are studied. Both the levels of unsteady interactions of merging flow structures and the efficiency of the acoustic generation are observed to increase with the merging angles, where the increase in acoustic efficiency can be up to three orders of magnitude. The major acoustic source is found to be the fluctuating wall pressure induced by the flow unsteadiness in the downstream branch. A scaling law between the wall fluctuating force and the acoustic efficiency is also derived.     

Phase Doppler Anemometer for Measurements of Deterministic Spray Unsteadiness

A method and analysis was developed to quantify the amplitude of deterministic spray unsteadiness based on Phase Doppler Anemometry (PDA), which sampled time‐dependent droplet velocity and size measurements, in order to determine the fluctuations of droplet data rate and number density, which are quantities relevant to fluctuations of droplet concentration. The data processing method of the PDA measurements was assessed in a pulsed spray at a frequency of 20 Hz injected in a swirl‐stabilised burner. Comparisons between quantities relevant to droplet concentration fluctuations, measured by PDA and a light scattering technique, quantified the deterministic spray unsteadiness and agreed to within 15%. The developed PDA approach was applied in the swirl‐stabilised burner to measure the amplitude of deterministic spray unsteadiness of an otherwise steady spray, which was caused by the instability of the atomisation process. The intensity of deterministic fluctuations of droplet data rate and number density, occurring at a frequency range around 600 Hz due to the atomisation process, was quantified to 15% of the corresponding mean value and this spray unsteadiness generated fluctuations on the air and droplet velocity fields. The deterministic spray unsteadiness could survive up to the end of the recirculation zone of the air flow at the burner exit and, therefore, could influence flame stability.     

A theoretical study on the unsteady aerothermodynamics for attached flow models

The principle of the unsteady aerothermodynamics was theoretically investigated for the attached flow. Firstly, two simplified models with analytic solutions to the N-S equations were selected for the research, namely the compressible unsteady flows on the infinite flat plate with both time-varying wall velocity and time-varying wall temperature boundary conditions. The unsteady temperature field and the unsteady wall heat flux (heat flow) were analytically solved for the second model. Then, the interaction characteristic of the unsteady temperature field and the unsteady velocity field in the simplified models and the effects of the interaction on the transient wall heat transfer were studied by these two analytic solutions. The unsteady heat flux, which is governed by the energy equation, is directly related to the unsteady compression work and viscous dissipation which originates from the velocity field governed by the momentum equation. The main parameters and their roles in how the unsteady velocity field affects the unsteady heat flux were discussed for the simplified models. Lastly, the similarity criteria of the unsteady aerothermodynamics were derived based on the compressible boundary layer equations. Along with the Strouhal number Stu, the unsteadiness criterion of the velocity field, StT number, the unsteadiness criterion of the temperature field was proposed for the first time. Different from the traditional method used in unsteady aerodynamics which measures the flow unsteadiness only by the Stu number, present results show that the flow unsteadiness in unsteady aerothermodynamics should be comprehensively estimated by comparing the relative magnitudes of the temperature field unsteadiness criterion StT number with the coefficients of other terms in the dimensionless energy equation.     

跨音速轴流风扇转子叶顶泄漏流的数值研究

采用数值模拟方法研究了不同间隙,不同流量工况下叶顶泄漏流非定常流动特征,发现在研究的三个间隙中,只有当间隙大于或等于设计间隙时,流动才会出现非定常性.随着流量的减小,泄漏涡轨迹前移,当泄漏涡轨迹到达相邻叶片压力面时,影响压力面压力分布,打破流场静态平衡,引起叶顶流场及激波位置、强度发生非定常波动.     

On flow unsteadiness induced by structural vibration

In this paper, the effects of structural vibration on flow unsteadiness are investigated numerically. A fully coupled model, that solves the unsteady flow equations as well as the dynamic equations of the structure, is used. Numerical experiments are carried-out for flow over a backward-facing step, where a large number of numerical and experimental data exist for comparisons. The flexible structure is upstream of the step and is excited by a plane acoustic wave from the side opposite to the flow. Three Reynolds number cases are studied: 300 for a laminar flow, 3000 for a transitional flow and 15 000 for a turbulent flow. The results obtained are in good agreement with experimental observations and show the strong coupling between structural vibration and the resulting flow unsteadiness.     

Dynamical systems and complex systems theory to study unsteady combustion

Reacting flow fields are often subject to unsteadiness due to flow, reaction, diffusion, and acoustics. Further, flames can also exhibit inherent unsteadiness caused by various intrinsic instabilities. Interaction between various unsteady processes across multiple scales often makes combustion dynamics complex. Characterizing such complex dynamics is essential to ensure the safe and reliable operation of high efficiency combustion systems. Tools from nonlinear dynamics and complex systems theory provide new perspectives to analyze and interpret the data from real systems. They could also provide new ways of monitoring and controlling combustion systems. We discuss recent advances in studying unsteady combustion dynamics using the tools from dynamical systems theory and complex systems theory. We cover a range of problems involving unsteady combustion such as thermoacoustic instability, flame blowout, fire propagation, reaction chemistry and flow flame interaction.     

Influences of Marangoni convection and variable magnetic field on hybrid nanofluid thin-film flow past a stretching surface

Investigations on thin-film flow play a vital role in the field of optoelectronics and magnetic devices. Thin films are reasonably hard and thermally stable but quite fragile. The thermal stability of a thin film can be further improved by incorporating the effects of nanoparticles. In the current work, a stretchable surface is considered upon which hybrid nanofluid thin-film flow is taken into account. The idea of augmenting heat transmission by making use of a hybrid nanofluid is a focus of the current work. The flow is affected by variations in the viscous forces, along with viscous dissipation effects and Marangoni convection. A time-constrained magnetic field is applied in the normal direction to the flow system. The equations governing the flow system are shifted to a non-dimensional form by applying similarity variables. The homotopy analysis method is employed to find the solution to the resultant equations. It is noticed in this study that the flow characteristics decline with augmentation of magnetic, viscosity and unsteadiness parameters while they increase with enhanced values of thin-film parameters. Thermal characteristics are supported by increasing values of the Eckert number and the unsteadiness parameter and opposed by the viscosity parameter and Prandtl number. The numerical impact of different emerging parameters upon skin friction and the Nusselt number is calculated in tabular form. A comparison of current work with established results is carried out, with good agreement.     

Investigation of the benefits of unsteady blowing actuation on a 2D wind turbine blade

This paper investigates the benefit of unsteady blowing actuation over a two-dimensional (2D) airfoil specially designed for wind turbine applications. The experiments were carried out in Syracuse University’s anechoic wind tunnel, both with and without large-scale unsteadiness in the free stream generated by a 2D cylinder upstream of the airfoil. By analyzing both surface pressure through wavelet analysis and Particle Image Velocimetry (PIV) velocity field measurements, we found a drastic change in the flow physics and the aerodynamic loading on the airfoil between steady and unsteady free-stream conditions. When there was no large-scale unsteadiness introduced in the flow, under open-loop flow control conditions with unsteady blowing, the leading-edge separation was delayed and the maximum lift coefficient was increased. For the cases where large-scale unsteadiness was introduced into the flow, the experiments showed that both open-loop and closed-loop control cases were capable of reducing load fluctuations by a measurable amount. However, only the closed-loop control case that utilized dynamic surface pressure information from the airfoil suction side near the leading edge was capable of consistently mitigating the fluctuating load.     

关于叶轮机时均(准四维)和非定常(四维)气动设计体系的初步诠释

本文以考虑非定常流动的完整性为线索,总结概述了先前气动设计体系的困难与限制,在此基础上,以描述叶轮机流动的时均和时间精确模型为核心分别从其构成和标志性技术对叶轮机时均和非定常气动设计体系进行了初步诠释。文章认为促成时均(准四维)和非定常(四维)气动设计体系现实应用是叶轮机发展的最后契机。     

轴向间隙对动 /静相干叶排内部非定常特性的影响

本文采用文献［3,4］所发展的滑移界面技术,求解了不同轴向间隙时某一透平级内的非定常流场, 发现轴向间隙由0.152倍栅距变化到0.533倍栅距时,监测点速度u的相对振幅由26.27%下降为7.94%; 速度v的相对振幅由21.34%下降到7.3%。计算结果表明轴向间隙的增大将使动/静叶排间的相互干扰作用减弱,从而使其内部非定常流动特性减小,为设计工作提供了参考依据     

Effects of transpiration on unsteady MHD flow of an upper convected Maxwell （UCM） fluid passing through a stretching surface in the presence of a first order chemical reaction

The aim of this article is to present the effects of transpiration on the unsteady two-dimensional boundary layer flow of non-Newtonian fluid passing through a stretching sheet in the presence of a first order constructive/destructive chemical reaction. The upper-convected Maxwell （UCM） model is used here to characterize the non-Newtonian behavior of the fluid. Using similarity solutions, the governing nonlinear partial differential equations are transformed into ordinary ones and are then solved numerically by the shooting method. The flow fields and mass transfer are significantly influenced by the governing parameters. The fluid velocity initially decreases as the unsteadiness parameter increases and the concentration decreases significantly due to the increase in the unsteadiness. The effect of increasing values of transpiration （suction） and the Maxwell parameter is to suppress the velocity field; however, the concentration is enhanced as transpiration （suction） and the Maxwell parameter increase. Also, it is found that the fluid velocity decreases as the magnetic parameter increases; however, the concentration increases in this case.     

Oscillatory motion of a viscoelastic fluid past a stretching sheet

Summary The boundary layer flow of a viscoelastic fluid (Walters' B model) past a stretching sheet is considered for investigation. The solution of the equation of motion is obtained using the power series method. The effects of the viscoelastic parameterk ₁ on the flow have been investigated. It is also found that the effects of unsteadiness in the wall velocity and skin-friction are appreciable.     

Visualization of transient three-dimensional flow field with rotating stall in a diagonal flow fan

An Unsteady flow field with rotating stall cells in a high specific-speed diagonal flow fan has been investigated experimentally. Although a general feature of stall cells has already indicated, i.e., the number of stall cells is one and its propagating speed is approximately 80 percent of rotor speed, little has been known about the flow field when a rotating stall occurs because of its unsteadiness. In order to capture the behavior of the rotating stall cell, measurements of the flow field at the rotor inlet were carried out with a single slant hot-wire. Those data were processed by a so-called “double phase-locked averaging” (DPLA) technique, which enabled to capture the flow field of the cell in the reference co-ordinate system fixed to the rotor. As a result, time-dependent ensemble averages of the three-dimensional velocity components at the rotor inlet have been obtained and the behavior of the rotating stall cell has been illustrated with each velocity component.     

Numerical Analysis of Unsteady Magneto-Biphase Williamson Fluid Flow with Time Dependent Magnetic Field

Numerical investigation of the dusty Williamson fluid with the dependency of time has been done in current disquisition. The flow of multiphase liquid/particle suspension saturating the medium is caused by stretching of porous surface. The influence of magnetic field and heat generation/absorption is observed. It is assumed that particle has a spherical shape and distributed uniformly in fluid matrix. The unsteady two-dimensional problems are modeled for both fluid and particle phase using conservation of mass, momentum and heat transfer. The finalized model generates the non-dimensioned parameters, namely Weissenberg number, unsteadiness parameter, magnetic parameter,heat generation/absorption parameter, Prandtl number, fluid particle interaction parameter, and mass concentration parameters. The numerical solution is obtained. Locality of skin friction and Nusselt number is deliberately focused to help of tables and graphs. While inferencing the current article it is clearly observed that increment of Williamson parameter, unsteadiness parameter, magnetic parameter, volume fraction parameter, and mass concentration parameter reduces the velocity profile of fluid and solid particles as well. And increment of Prandtl number, unsteadiness parameter,volume fraction parameter, and mass concentration parameter reduces the temperature profile of fluid and solid particles as well.     

基于非线性谐波法的离心压气机确定应力场分析

本文采用非线性谐波法与定常计算方法,对离心压气机的内部流场进行了数值模拟,对比了时均流场与定常流场的差别,研究了离心压气机确定应力分布的特点。结果表明,采用非线性谐波方法所得到的压气机内部流场宏观结构与定常结果基本一致,但流场参数分布细节存在较明显差别,且这种差别与对应的确定应力场的分布特征吻合,验证了确定应力是引起时均流场与定常流场差别的原因。对确定应力的分布特征分析表明,离心压气机内确定应力在流向上呈现为从叶轮出口向上下游逐渐递减的趋势,在叶高方向上表现为从叶根到叶顶逐渐递增趋势;且在整体上,确定应力的空间不均匀特性在叶轮出口处最为强烈,表明离心压气机内部最强非定常效应同样位于叶轮出口。     

Theoretical simulation and experimental validation of inverse quasi-one-dimensional steady and unsteady glottal flow models

In physical modeling of phonation, the pressure drop along the glottal constriction is classically assessed with the glottal geometry and the subglottal pressure as known input parameters. Application of physical modeling to study phonation abnormalities and pathologies requires input parameters related to in vivo measurable quantities commonly corresponding to the physical model output parameters. Therefore, the current research presents the inversion of some popular simplified flow models in order to estimate the subglottal pressure, the glottal constriction area, or the separation coefficient inherent to the simplified flow modeling for steady and unsteady flow conditions. The inverse models are firstly validated against direct simulations and secondly against in vitro measurements performed for different configurations of rigid vocal fold replicas mounted in a suitable experimental setup. The influence of the pressure corrections related to viscosity and flow unsteadiness on the flow modeling is quantified. The inversion of one-dimensional glottal flow models including the major viscous effects can predict the main flow quantities with respect to the in vitro measurements. However, the inverse model accuracy is strongly dependent on the pertinence of the direct flow modeling. The choice of the separation coefficient is preponderant to obtain pressure predictions relevant to the experimental data.     

涡轮叶栅端壁区非定常流场显示

用氢气泡法流场显示技术,获得了不同攻角、不同径向间隙下涡轮平面叶栅端壁区内各种旋涡的发生、发展、涡－涡干涉、涡－附面层干涉的非定常流动图画,加深对涡轮端壁区流动结构的认识。