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Recent development of a CFD-wind tunnel correlation study based on CAE-AVM investigation

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Chinese Journal of Aeronautics 2018年第3期31卷 419-428页

作者： Jun HUA Sui ZHENG Min ZHONG Ganglin WANG Georg EITELBERG Sinus HEGEN Roy GEBBINK Chinese Aeronautical Establishment Beijing 100012 China German-Dutch Wind Tunnels Marknesse 8316 PR The Netherlands

This paper starts with brief introduction to the open topic of the CFD and wing tunnel correlation study, followed by a description of the Chinese Aeronautical Establishment（CAE） –aerodynamic Validation Model（AVM） and its wind tunnel test in the German-Dutch Wind tunnels（DNW）. The features of the aerodynamic design, the CFD approach, the wind tunnel model fabrication and the experimental techniques are discussed along with the motivation of the CAEDNW workshop on CFD-wind tunnel correlation study. The workshop objective is focused on the interference from the aero-elastic deformation of the wind tunnel model and the model support system to the aerodynamic performance and CFD validations. The four study cases, geometry and mesh preparation of the workshop are introduced. A comprehensive summary of the CFD results from the organizer and the participants is provided. Major observations, both CFD to CFD and CFD to wind tunnel, are identified and summarized. The CFD results of the participants are in good agreement with each other, and with the wind tunnel test data when the wing deformation and a Z-sting system are included in the CFD, indicating the importance of considering such interference at high subsonic Mach number of 0.85.

关键词： aerodynamic design CFD validation CFD-wind tunnel correlation Model deformation Model support interference

aerodynamics design of Two-stage Vane-less Counter-rotating Turbinec

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Journal of Thermal Science 2011年第5期20卷 406-412页

作者： Yang Zhou Huoxing Liu Wei Li Jun Zeng National Key Lab. on Aero-Engines Aero-Engines Simulation Research Center Beijing Univ. of Aero. ＆ Astro. Beijing 100191 China Zhuzhou Aviation Powerplant Research Institute Zhuzhou 412002 China China Gas Turbine Establishment Chengdu 610500 China

It is one of the most efficient ways to greatly improve aero-engines' performance by utilizing vaneless counterrotating turbine(VCRT) *** supply sufficient power,VCRT turns to be high Mach number,large flow angle at high-pressure turbine(HPT) rotor exit,and low blade camber angle,which increase difficulties to turbine *** the axial velocity ratio of HPT rotor is much larger than the conventional ones,the optimal selection of VCRT velocity triangles based on theoretical analysis is developed,and how the efficiency varied by HPT stator/rotor exit flow angle is also figured *** key points to design a high efficient practicable VCRT are to select velocity triangles that are characterized by low flow coefficient,high outlet flow angle and large axial velocity ratio of HPT ***,performance comparison between convergent blade and convergent-divergent blade shows the latter is more appropriate for VCRT.

关键词： counter-rotating turbine vaneless velocity triangle aerodynamic design

Hypersonic Waverider Surface Development Using aerodynamic Flow Around Conical Bodies

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Computer Aided Drafting,design and Manufacturing 2006年第1期16卷 63-69页

作者： Najam-us-Saqib School of Astronuatics Beijing University of Aeronautics and Astronautics Beijing 100083 China

Developing the waverider based hypersonic vehicles is an inverse design process in which shape is developed from a known flow field by tracing of streamlines to form a stream surface. The flow field can be based on a solution of Taylor Maccoll equation for a specified shock or cone angle. This Paper discusses the development of waverider shapes for hypersonic reentry vehicles.

关键词： aerodynamic design hypersonics waveriders surface generation

The development and application of an inviscid inverse method

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Propulsion and Power Research 2013年第2期2卷 131-138页

作者： Jinguang Yang Hu Wu School of Power and Energy Northwestern Polytechmical UniversityXian 710072Chinal

A two-dimensional inviscid inverse method is developed,verified and applied inthis *** method solves the Euler equation in absolute reference frame by a cell-centeredfinite volume method,and the hybrid Runge-Kutta method ls used for time *** from the direct method,the inverse method imposes a unique"transpiration"boundary condition on the blade *** inputs of inverse method are pressure loadingand blade tangential thickness distribution along the blade *** the time marchingprocess,the blade shape is periodically *** the solution is converged,the bladeshape will be *** the paper,the principle of the inverse method is described in *** the developed inverse method is verified against a consistence test:recover an axialcompressor cascade from a different ***,to demonstrate the powerful capability ofthe method,it is used to redesign the cascade,and final results give an improved aerodynamicperformance.

关键词： Inverse method Pressure loading aerodynamic design Turbomachinery

design and analysis of annular combustion chamber of a low bypass turbofan engine in a jet trainer aircraft

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Propulsion and Power Research 2016年第2期5卷 97-107页

作者： C.Priyant Mark A.Selwyn Department of Aerospace Engineering Karunya UniversityCoimbatoreT.N.India A.E.R.D.C. Hindustan Aeronautics Ltd.BangaloreKAIndia

The design of an annular combustion chamber in a gas turbine engine is thebackbone of this *** is specifically designed for a low bypass turbofan engine in a jettrainer *** combustion chamber is positioned in between the compressor and *** has to be designed based on the constant pressure,enthalpy addition *** presentmethodology deals with the computation of the initial design parameters from benchmarking ofreal-time industry standards and arriving at optimized *** is then studied for feasibilityand *** the various dimensions of the combustor are calculated based on differentempirical *** air mass flow is then distributed across the zones of the *** cooling requirement is met using the cooling *** the variations of parameters atdifferent points are *** whole combustion chamber is modeled using Siemens NX8.0,a modeling software and *** model is then analyzed using various parametersat various stages and levels to determine the optimized *** aerodynamic flowcharacteristics is simulated numerically by means of ANSYS 14.5 software *** air-fuelmixture,combustion-turbulence,thermal and cooling analysis is carried *** analysis isperformed at various scenarios and *** results are then presented in image outputsand graphs.

关键词： aerodynamic design Annular combustion chamber CFD(computational fluid dynamics)analysis Gas tur bine engine Optimization Real-time model

Study of Wind Turbine aerodynamic Performance Using Numerical Methods

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Study of Wind Turbine Aerodynamic Performance Using Numerica...

Numerical Investigation of the Effects of Swept Blade on the aerodynamic Performance of A Highly Loaded Transonic Two-Stage Fan

作者： S.Derakhshan A.Tavaziani Iran University of Science and Technology

design of wind turbine blades strictly depends on high precision, reliable and robust numerical predictions of its performance in all of operation conditions. This paper aims to simulate the flow around horizontal wind turbine blade with Computational Flow Dynamics(CFD) using a validated 3D Navier–Stokes flow solver. The main objectives of this study are investigating of different turbulence models and aerodynamic performance of wind turbine blades. The NREL Phase VI rotor used for CFD simulations and testing. Three different turbulence models included of Spalart-Allmaras, k-epsilon(Launder Sharma) and k-ω SST tested and the best model for prediction of wind turbine performance is provided. Since Mach number is less than 0.3, the flow around wind turbine blade is incompressible and precondition used. For all cases the structure grid used for Fluid reticulation grid. For results more accuracy, use of preconditioning is necessary. Outputs of flow solver are t power and pressure coefficients for each section. At the final the k-epsilon with preconditioning code is selected the best model for simulation of flow around wind turbine blades.

关键词： Computational fluid dynamics(CFD) horizontal wind turbine(HWT) aerodynamic design turbulence models

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Numerical Investigation of the Effects of Swept Blade on the...

Towards Efficient High-Dimensional aerodynamic Shape Optimization:Surrogate Modeling Via Gradient-Enhanced Kriging

2010亚太航空航天技术研讨会

作者： Jin Hailiang Jin Donghai~* Gui Xingmin Aeroengine Numerical Simulation Research Center Beihang University Beijing 100191 China

＜正＞Both conventional and swept schemes are adopted to design a highly-loaded transonic two-stage *** effects of swept blade on the aerodynamic performance of the fan are investigated using the three-dimensional numerical simulation *** results indicate that: the adiabatic efficiency and the stall margin of the swept scheme are increased by 0.63%and 7.1%respectively than the conventional scheme;the corner separation of the flow in the second stator passage is suppressed effectively by the swept stator;the stage matching problem that the second stage has already reached its stall condition while the first stage still has certain levels of stall margin at near design point in the conventional scheme has been improved by the swept design in the swept scheme;in this highly-loaded two-stage fan,the first stage does not start its stalling process until the second stage reaches its near stall condition and the fan starts to stall when both the first and second stages reach their stall conditions;the distance of the shock location from the leading edge of the forward-swept rotor is farther, and the shock moving upstream velocity due to the increasing backpressure is slower than that in the conventional rotor.

关键词： swept blade highly loaded transonic two-stage fan aerodynamic design numerical investigation

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Towards Efficient High-Dimensional Aerodynamic Shape Optimiz...

MULTI-OBJECTIVE SHAPE design IN aerodynamicS USING GAME STRATEGY

2010亚太航空航天技术研讨会

作者： Han Zhonghua~* Zhang Keshi National Key Laboratory of Science and Technology on aerodynamic design and Research School of Aeronautics Northwestern Polytechnical University 710072 Xi’an

＜正＞This paper presents a novel surrogate modeling method that can be potentially used for higher-dimensional aerodynamic shape optimization based on high-fidelity Computational Fluid Dynamics（CFD） *** key idea of this method is to use gradient to enhance the prediction of a kriging *** gradient can be efficiently computed by adjoint *** give number of samples points. the prediction accuracy of the surrogate model can be *** turn,the total computational cost of building a surrogate model at a give accuracy level can be *** presented method is validated by analytical function and demonstrated for building the surrogate model for the object function of an airfoil inverse design problem,with 20 design *** is preliminarily shown that gradient-enhanced kriging is promising for high-dimensional aerodynamic problems.

关键词： surrogate model kriging model gradient-enhanced kriging transonic flow aerodynamic design airfoil

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Transactions of Nanjing University of Aeronautics and Astronautics 2005年第3期22卷 195-199页

作者：唐智礼南京航空航天大学航空宇航学院

Multi-objective optimization for the optimum shape design is introduced in aerodynamics using the Game theory. Based on the control theory, the employed optimizer and the negative feedback are used to implement the constraints. All the constraints are satisfied implicitly and automatically in the design. Furthermore,the above methodology is combined with a formulation derived from the Game theory to treat multi-point airfoil optimization. Airfoil shapes are optimized according to various aerodynamics criteria. In the symmetric Nash game, each “player” is responsible for one criterion, and the Nash equilibrium provides a solution to the multipoint optimization. design results confirm the efficiency of the method.

关键词： Game theory multi-objective optimization aerodynamic design constrained optimal control theory