Prediction of incidence effects on oscillating airfoil aerodynamics by a locally analytical method

A complete mathematical model is formulated to analyse the effects of mean flow incidence angle on the unsteady aerodynamics of an oscillating airfoil in an incompressible flow field. A velocity potential formulation is utilized. The steady flow is independent of the unsteady flow field. However, the unsteady flow is coupled to the steady flow field through the boundary conditions on the oscillating airfoil. The numerical solution technique for both the steady and unsteady flow fields is based on a locally analytical method. In this method, analytical solutions are incorporated into the numerical technique, with the discrete algebraic equations which represent the differential flow field equations obtained from analytic solutions in individual local computational grid elements. This flow model and locally analytic numerical solution method are then verified through the excellent correlation obtained with the Theodorsen oscillating flat plate and Sears transverse gust classical solutions. The effects of mean flow incidence on the steady and oscillating airfoil aerodynamics are then investigated.     

Dämpfung von Rotating Stall in Radialverdichterstufen

In part load span centrifugal compressors incline rotating stall in the impeller, which often causes transient pressure oscillations and surge. Operation in part load span with transient processes has to be avoided, because it can endanger the compressor and the plant by vibrations. Active devices like an upstream or downstream side channel stage can influence flow and unsteady gas pressure oscillations in centrifugal compressor stages and shift rotating stall to lower flow or entirely avoid it. This article shows experimental results for characteristic lines and unsteady gas pressure oscillations in centrifugal compressor stages, which where coupled with an downstream side channel stage. The enforced turbulent eddy flow with unsteady gas pressure oscillation in side channel stages diminishes unsteady gas pressure oscillation in the centrifugal compressor stage and limits pressure gradient as well as the maximum reachable value of gas pressure oscillation at rotating stall.     

叶栅内非定常不可压流动的数值模拟

基于SMAC(SimplifiedMarkerandCell)方法推导出直接求解二维非定常、不可压N-S方程的隐式数值方法。求解的基本方程是任意曲线坐标系中以逆变速度为变量的N-S方程和椭圆型的压力Poisson方程。采用该方法,对二维叶栅非定常分离流场进行了数值模拟,叶栅表面压力的计算结果与试验结果相比比较吻合,从而验证了这种方法的可靠性。同时对叶栅非定常流场的流场结构和流动机理做了初步的探讨。在均匀来流和定常边界条件下,叶栅内部流动表现出强烈的非定常性;在小冲角和高雷诺数时,叶栅尾部产生类似卡门涡街的周期性流动。     

环型扩压叶栅中应用弯曲叶片的研究

在环型扩压叶栅实验风洞上进行了弯曲叶栅出口测量实验 ,研究了零冲角附近下常规直叶栅、正倾斜叶栅、正弯曲叶栅、S型叶栅对出口总压损失分布情况和二次流速度矢量的影响并进行了分析。     

用可压缩流涡方法模拟叶轮机动静叶的相互作用

本课题组发展了一种扰动涡方法,用以研究叶轮机内动、静叶相互作用。其优点是物理图画清楚,计算收敛快。它采用了一个重要假设：扰动胀量为零,从而大大简化 了计算过程。文章的目的是研究此假设的影响,并取消此假设,使扰动涡方法建立在完全严格的数学基础上。由于取消了“扰动胀量为零的假设,需要耦合求解扰动质量方程、扰动涡量输运方程和扰动能量输运方程。这是文章与文献[1,2]的主要区别。     

基于转静干涉效应的压气机叶片气动载荷分析

转静叶排的相互作用会使压气机内部流场存在复杂的非定常性。为深入研究压气机叶片的气动载荷特性,以某型航空发动机压气机为研究对象,考虑叶排间的转静干涉效应,利用滑移网格技术对整个叶盘的三维流场展开模拟,求解干涉周期T_b内压气机转子内部的流动规律。同时对叶片气动载荷的非定常特性进行进一步分析,讨论了不同压比、转速对压气机叶片气动载荷的影响。结果表明叶片压力面和吸力面气动载荷波动峰值的主导频率皆为转静干涉频率f₀的倍频,其中一倍频（1×f₀）分量占主导地位。在干涉周期T_b内,叶片表面压力涡发生周期性的迁移与耗散,压力面和吸力面气动载荷的变化呈相反趋势。随着压比的增加,压气机叶片气动载荷逐渐增大,但其脉动幅值和频谱峰值基本不变。转速的升高使得转静干涉的频率增大,增强了压气机叶片气动载荷的非定常特性。研究结果能够应用于叶盘结构的气动优化设计,可为高性能航空发动机压气机的研制提供支持和参考。     

轴流压气机叶排干扰所引起转子叶片的振动应力

 轴流压气机中上游导叶排与下游转子叶排相互干扰,这一非定常流动诱发了叶片振动.由此,利用有限元法,对所造成的振动应力进行了数值分析.建立了轴流压气机工程设计中求解作用于叶片非定常气动力的近似方法.讨论了叶型几何和静叶数对叶片振动应力的影响.给出由此所造成的叶片动应力分布图,与实验结果基本接近,得到了有益的结论.     

Endwall boundary layer separation in a single-stage axial-flow low-speed compressor and a high-stagger compressor cascade

The paper describes an investigation of the overtip endwall flow in a single-stage axial-flow low-speed compressor (absolute flow) and in a corresponding compressor cascade (simulated relative flow) with a tip clearance on one side. The clearance to chord ratio is 3% in both cases. Oil flow pictures of the rotor casingwall and cascade endwall are used to visualize and analyse the boundary layers on the walls at various flow rates and corresponding inlet angles, respectively. The results enable the different sources of endwall blockage to be identified and changes with flow rate or inlet angle to be determined.     

Endwall boundary layer separation in a single-stage axial-flow low-speed compressor and a high-stagger compressor cascade

The paper describes an investigation of the overtip endwall flow in a single-stage axial-flow low-speed compressor (absolute flow) and in a corresponding compressor cascade (simulated relative flow) with a tip clearance on one side. The clearance to chord ratio is 3% in both cases. Oil flow pictures of the rotor casingwall and cascade endwall are used to visualize and analyse the boundary layers on the walls at various flow rates and corresponding inlet angles, respectively. The results enable the different sources of endwall blockage to be identified and changes with flow rate or inlet angle to be determined.     

The optimal control of unsteady flows with a discrete adjoint method

This paper presents a general framework to derive a discrete adjoint method for the optimal control of unsteady flows. The complete formulation of a generic time-dependent optimal design problem is introduced and it is outlined how to derive the discrete set of adjoint equations in a general approach. Results are shown that demonstrate the application of the theory to the drag minimization of viscous flow around a rotating cylinder, and to the remote inverse design of laminar flow around the multi-element NLR 7301 configuration at a high angle of attack. In order to reduce the considerable computational costs of unsteady optimization, the use of bigger time steps over transitional or unphysical adjusting periods as well as omitting time steps while recording the flow solution are investigated and are shown to work well in practice.     

Continuous-time state-space unsteady aerodynamic modeling based on boundary element method

In this paper a continuous-time state-space aerodynamic model is developed based on the boundary element method. Boundary integral equations governing the unsteady potential flow around lifting bodies are presented and modified for thin wing configurations. Next, the BEM discretized problem of unsteady flow around flat wing equivalent to the original geometry is recast into the standard form of a continuous-time state-space model considering some auxiliary assumptions. The system inputs are time derivative of the instantaneous effective angle of attack and thickness/camber correction terms while the outputs are unsteady aerodynamic coefficients. To validate the model, its predictions for aerodynamic coefficients variations due to the various unsteady motions about different wing geometries are compared to the results of the direct BEM computations and verified numerical and theoretical solutions. This comparison indicates a good agreement. Since the resulting aerodynamic model is in the continuous-time domain, it is particularly useful for optimization and nonlinear analysis purposes. Moreover, its state-space representation is the appropriate form for an aerodynamic model in design or control applications.     

Basic dynamics of split Stirling refrigerators

The basic features of the split Stirling refrigerator, driven by a linear compressor, are described. Friction of the compressor piston and of the regenerator, and the viscous losses due to the gas flow through the regenerator matrix are taken into account. The temperature at the cold end is an input parameter. The general equations are derived which are subsequently treated in the harmonic approximation. Examples are given of application of the relations for describing optimum-performance conditions as well as the interrelationship between cooler and heat-engine operation.     

Modelling of the non-reactive deposits impact on centrifugal compressor aerothermo dynamic performance

The centrifugal compressor blockage is considered an important issue in compressor operation and one of the main causes of machine failure. This is normally initiated by the presence of deposits with the process gas yielding to reduce the effective flow area, increase the frictional losses and distort the pressure distribution profile. The influences of flow blockage cover the thermodynamic, aerodynamic and rotordynamic performance parameters of centrifugal compressor as will be investigated further in this study. Accordingly, this paper introduces a novel approach to model the impact of non-reactive deposits flow on the centrifugal compressor aerothermodynamics performance. The developed set of empirical equations in this study provides a new way to derive the equivalent compressor performance map at various degrees of fouling with a consideration of gas properties and stage efficiency variation and without a prior knowledge of the detailed geometrical features. In order to emphasize the validity of the new method, it has been tested with two operating cases and the obtained results were compared with the internal inspection findings from the stage overhauling process. Besides, this approach has been proven to be valid for the modelling of flow blockage effect at the suction side, compressor internals and downstream equipment. Furthermore, a new methodology has been established to assess the possibility of deposits accumulation in the gas path of the compression system based on the operational data of the discharge parameters.     

Flow visualization applied to a small refrigeration compressor

This paper describes a flow visualization technique that was used to evaluate qualitatively the gas flow pattern inside a small, hermetically sealed, reciprocating refrigeration compressor. The applicable compressor designs are those in which the suction gas from the evaporator is dumped into the compressor shell, and is then drawn through a muffler into the suction plenum of the compressor. The physical separation of the muffler inlet from the suction gas inlet serves to reduce compressor noise and also provides an easy and convenient means of separating any liquid (compressor oil or liquid refrigerant) from the refrigerant gas. For the flow visualization studies the compressor housing was replaced by a clear plastic shell. Atmospheric air seeded with white smoke was the working fluid. The suction inlet and muffler were parts from a commercial compressor. The flow pulsations were modelled by connecting the muffler outlet to the input plenum of an auxiliary compressor. The flow patterns near the muffler inlet were recorded with a video camera. The mixing of the inlet gas with the gas circulating inside the muffler was studied. The effect of alignment and offset of the muffler inlet relative to the suction inlet, the effect of muffler size, and the effect of a shroud around the muffler were studied. The results were used to guide a companion study of detailed temperature and pressure measurements inside a working compressor.     

Hydrodynamic interaction of axial turbomachine cascades

Hydrodynamic interaction of mutually moving airfoil cascades is investigated. It is shown that the semi-empirical theory of potential-vortical interaction of two mutually moving cascades in incompressible flow allows one to describe correctly the features of their mutual effect for various gaps between cascades and relations of their pitches. Application of the above theory to a flow around three cascades of the stator-rotor-stator type allows to determine the basic mechanism of the stators’ mutual shift effects (clocking effects). To close the theory regarding the vortical interaction of cascades, a semi-empirical model of turbulent diffusion in a non-uniform flow of the periodic vortices descending from airfoils is proposed. Theoretical results are compared with data from numerical and physical experiments. Comparison with results of numerical modeling is based on the solution of the Reynolds equations for a viscous gas closed by the (q-ω) model of turbulence. Results published here and elsewhere are used for comparison with measurement data     

Kombination von Radial- und Seitenkanalstufen für Turboverdichter

Unsteady gas pressure oscillations occur at impeller outlet and diffuser of radial and side channel compressors, engendered by the blades grid of the impeller. They have effect beyond the limits of inlet and outlet. If a radial stage is coupled to a side channel stage, then the unsteady gas pressure oscillations of the side channel stage have an effect inside the radial stage affecting flow and characteristic curve. Because of that, the radial stages unstable characteristics and the limit of rotating stall can be moved to lower volume flows or completely suppressed by connecting a side channel stage before or behind it. Therefore the permissible range of operation of combined compressor stages can be extended compared with a radial compressor stage. Moving the limit of rotating stall of the radial compressor stage and lower the gas pressure oscillations caused by Rotating Stall as a result of the side channel stages unsteady gas pressure oscillations will be proved experimental. As a criterion for Rotating Stall in radial compressor stages also the proportion between RMS of gas pressure oscillations and the total pressure increase in the radial compressor stage can be used.     

R290/CO2复叠式制冷系统的性能实验

通过对R290／C02复叠式制冷系统的性能实验,对低温循环用CO2作为制冷工质,高温循环分别用R22和R290为制冷工质的性能进行比较,结果表明,随着蒸发温度的升高,冷凝温度的降低,R290／CO2复叠式制冷系统的最佳质量流量比增大,COP增加。随着高温循环压缩机入口温度的升高,R290压缩机的功耗略高于R22压缩机的功耗,R290循环的COPh要高于R22循环的COPh。结果表明自然工质R290／CO2复叠式制冷系统具有很好的发展前景。     

带尾板的倾斜扩压叶栅的实验研究

对由常规直叶片、正倾斜叶片、复合倾斜叶片在的三种矩型扩压叶栅在矩型叶栅低速风洞上进行了实验研究,详细测量了叶栅出口流场,研究和分析了零冲角下常规直叶栅、正倾斜叶栅、复合倾斜叶栅对出口能量损失分布情况和二次流速度矢量的影响,讨论了叶片倾斜对扩压叶栅出口流场的改善作用。     

Unsteady flows of a binary mixture of incompressible Newtonian fluids in an annulus

This paper is concerned with applying the mixture theory of two chemically inert incompressible Newtonian fluids to some simple unsteady flows in the annular region between two infinitely long coaxial cylinders. The equations governing the motion of the binary mixture under discussion are reduced to a system of coupled partial differential equations. With the help of finite Hankel transforms, the exact solutions of these equations are obtained in series form for the following three problems: (i) unsteady axial Couette flow in an annulus, (ii) unsteady Poiseuille flow in an annulus, (iii) unsteady circular Couette flow in an annulus.     

Investigation of fluid–structure interactions using a velocity‐linked P2/P1 finite element method and the generalized‐ α method

A velocity‐linked algorithm for solving unsteady fluid–structure interaction (FSI) problems in a fully coupled manner is developed using the arbitrary Lagrangian–Eulerian method. The P2/P1 finite element is used to spatially discretize the incompressible Navier–Stokes equations and structural equations, and the generalized‐ α method is adopted for temporal discretization. Common velocity variables are employed at the fluid–structure interface for the strong coupling of both equations. Because of the velocity‐linked formulation, kinematic compatibility is automatically satisfied and forcing terms do not need to be calculated explicitly. Both the numerical stability and the convergence characteristics of an iterative solver for the coupled algorithm are investigated by solving the FSI problem of flexible tube flows. It is noteworthy that the generalized‐ α method with small damping is free from unstable velocity fields. However, the convergence characteristics of the coupled system deteriorate greatly for certain Poisson's ratios so that direct solvers are essential for these cases. Furthermore, the proposed method is shown to clearly display the advantage of considering FSI in the simulation of flexible tube flows, while enabling much larger time‐steps than those adopted in some previous studies. This is possible through the strong coupling of the fluid and structural equations by employing common primitive variables. Copyright © 2012 John Wiley & Sons, Ltd.