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Parametric structure optimization of a main rotor blade as an application for FSI analysis in main rotor optimization process

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AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY 2025年第1期97卷 37-51页

作者： Kocjan, Jakub Rogolski, Robert Mil Univ Technol Doctoral Sch Warsaw Poland Mil Univ Technol Fac Mechatron Armament & Aerosp Warsaw Poland

PurposeModern warfare and modern battlefield are very demanding. The recent conflicts showed that the usage of the helicopters is very limited and only the best constructions are able to provide support for the operations. The purpose of this research is to show the possibilities of new design tool for main rotor aerostructural optimization. It is a next chapter of the research that is aimed at finding new solutions for rotorcraft ***/methodology/approachThis work presents a method of preliminary structure optimization of the main rotor blade using parametric modeling. It is the next step in the main rotor optimization studies. It is the next step after preparing the parametric model for the external shape CFD analysis. As a basis for parametric blade structure calculations, the analytical model is provided in this paper. The equations of rigid blade loads and, as a consequence of the strength elements, stresses are shown. The parametric blade modeling is conducted using the Graphic Integrated Programming language. The parametric design method is shown to be used for various blade planform models and different section airfoils. The structure of a blade is generated automatically after the user enters the parameters. The code-inbuilt analysis systems provide a quick inertia examination of the generated geometry, which is the basis for further optimization. The program calculates the blade loads and verifies them with the given material conditions and proposed safety factors. In the analysis, composite materials for the strength elements were *** results of this research showed the application of parametrization into the main rotor blade design loop. It was presented that the main rotor blade structure can be enhanced using fluid-structure interaction (FSI) methods. The time saving with the implementation the process into design loop is *** implicationsThis work can be practically used in the main rotor blade design proces

关键词： Helicopter Rotorcraft Optimization Main rotor fluid-structure interaction

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A discrete Immersed Boundary Method for the numerical simulation of heat transfer in compressible flows

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EUROPEAN JOURNAL OF MECHANICS B-fluidS 2025年 111卷 61-71页

作者： Riahi, H. Errante, P. da Silva, E. Goncalves Meldi, M. Univ Lille CNRS UMR 9014 Centrale LilleONERAArts & Metiers ParisTechLMFL F-59000 Lille France Univ Poitiers CNRS ENSMA UPR 3346Inst PprimeDept Fluid Flow Heat Transfer SP2MI Teleport211 Bd Marie & Pierre Curie F-86962 Chasseneuil France

In the present study, a discrete forcing Immersed Boundary Method (IBM) is proposed for the numerical simulation of high-speed flow problems including heat exchange. This class of tools is relevant for several applications in engineering studies for aerospace applications, notably for atmospheric reentry. The flow field is governed by the compressible Navier-Stokes equations, which are resolved by using the open source library OpenFOAM. The numerical solver is modified to include source terms in the momentum equation and in the energy equation, which account for the presence of the immersed body. The method is validated on some benchmark test cases dealing with forced convection problems and moving immersed bodies. The results obtained are in very good agreement with data provided in the literature. The method is further assessed by investigating three-dimensional high Mach flows around a heated sphere with different wall temperature. Even for this more complex test case, the method provides an accurate representation of both thermal and velocity fields.

关键词： Immersed boundary method Heat transfer Forced convection Compressible flows fluid-structure interaction OpenFOAM

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Image-based simulation of mitral valve dynamic closure including anisotropy

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MEDICAL IMAGE ANALYSIS 2025年 99卷 103323页

作者： Khaledian, Nariman Villard, Pierre-Frederic Hammer, Peter E. Perrin, Douglas P. Berger, Marie-Odile Univ Lorraine CNRS INRIA LORIA Nancy France Boston Childrens Hosp Dept Cardiac Surg Boston MA USA Harvard Med Sch Boston MA USA

Simulation of the dynamic behavior of mitral valve closure could improve clinical treatment by predicting surgical procedures outcome. We propose here a method to achieve this goal by using the immersed boundary method. In order to go towards patient-based simulation, we tailor our method to be adapted to a valve extracted from medical image data. It includes investigating segmentation process, smoothness of geometry, case setup and the shape of the left ventricle. We also study the influence of leaflet tissue anisotropy on the quality of the valve closure by comparing with an isotropic model. As part of the anisotropy analysis, we study the influence of the principal material direction by comparing methods to obtain them without dissection. Results show that our method can be scaled to various image-based data. We evaluate the mitral valve closure quality based on measuring bulging area, contact map, and flow rate. The results show also that the anisotropic material model more precisely represents the physiological characteristics of the valve tissue. Furthermore, results indicate that the orientation of the principal material direction plays a role in the effectiveness of the valve seal.

关键词： fluid-structure interaction Mitral valve Constitutive model Fiber model Immersed boundary Segmentation

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Propagation study of distorted flow along rotor blades and its impact on blade vibration

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2025年

作者： Chen, Fu-qiang Wei, Xue-yang Li, Fu-dong Wang, Wei-min Beijing Univ Chem Technol Beijing Key Lab Hlth Monitoring & Selfrecovery Hig 15 North Third Ring East Rd Beijing 100029 Peoples R China Beijing Univ Chem Technol State Key Lab Highend Compressor & Syst Technol Beijing Peoples R China Tsinghua Univ Dept Energy & Power Engn Key Lab Thermal Sci & Power Engn Minist Educ Beijing Peoples R China Compressor Technol Lab Anhui Prov State Key Lab Compressor Technol Hefei Peoples R China

Inlet distortion can reduce the compressor's stability margin and, in severe cases, lead to blade flutter. However, the mechanisms how inlet distortion, after being mitigated by Inlet Guide Vanes (IGV), affects the vibration characteristics of rotor blades (R1) remain unclear. To address this issue, the present study constructs an integrated model of the inlet duct and the compressor. Initially, using Particle Image Velocimetry (PIV) technology and Computational fluid Dynamics (CFD) simulations, the study quantitatively characterizes swirl distortion and total pressure distortion at the outlet of the inlet duct. Subsequently, it explores how distorted inflow propagates along the rotor blades, revealing that the low-speed wake generated by the distortion and the tangential flow at the blade tip acts as excitation sources for R1 vibration. Finally, distortion suppression strategies are explored from the perspective of mitigating these excitation sources. The research findings indicate that combined distortion alters the force acting on the blades around their circumference. Significant variations in the flow state on the blade's suction surface lead to differing vibration amplitudes. Specifically, the lowest tip amplitude increases by 68 mu m compared to the case with uniform inlet flow, while the highest tip amplitude rises by 296 mu m. Adjusting IGV angle forward effectively suppresses swirl distortion. When beta = 10 degrees, zeta is minimized, resulting in an efficiency increase from 88.6% to 91%. Changes in the structural parameters significantly impact DC60, where increasing both c and D0 leads to a rise in DC60. Considering both R1 efficiency and zeta, the I-1 group proves to be optimal.

关键词： Compressor L-inlet duct distortion flow blade vibration fluid-structure interaction computational fluid dynamics (CFD)

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A displacement formulation for coupled elastoacoustic problems that preserves flow irrotationality

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JOURNAL OF SOUND AND VIBRATION 2025年 597卷

作者： Deng, Jie Guasch, Oriol Maxit, Laurent Chongqing Ind Polytech Coll Chongqing 401120 Peoples R China Univ Ramon Llull Human Environm Res HER Grp Dept Engn C-Quatre Camins 30 Barcelona 08022 Catalonia Spain INSA Lyon Lab Vibrat Acoust LVA 25 bis Ave Jean Capelle F-69621 Lyon France

Two-way fluid-structure interaction (FSI) problems, in the sense that a flow induces the motion of a solid, which in turn modifies the flow boundary conditions, have been approached with very different strategies, the most common of which is probably the finite element method (FEM). In the case of elastoacoustics, the flow consists of an acoustic field interacting with a vibrating structure. When the problem is discretized with the FEM, an algebraic block matrix system is obtained and the coupling between the acoustic field and the structure takes place through a coupling matrix with off-diagonal terms. Usually the structure is characterized by its displacement field, while for the acoustics several options are available, ranging from pressure to acoustic displacement or velocity/displacement acoustic potentials. Depending on the formulation, symmetric or asymmetric systems are obtained and different types of numerical stability problems have to be faced. In this work, a monolithic strategy based on the Rayleigh- Ritz method is proposed. The displacement is used as the primary variable for both the structure and the acoustic field and is expanded in terms of Gaussians as basis functions. This provides an algebraic block matrix system for the global uncoupled problem. However, instead of resorting to a coupling matrix, the essential continuity conditions at the acoustic-structure interface are imposed by the nullspace method (NSM). That is, the solution of the uncoupled system is expanded in terms of a basis of the nullspace generated by the essential conditions of the problem, including the displacement continuity constraints at the interface, thus giving the solution of the coupled problem. As for natural conditions, they are imposed in a weak sense. For ease of explanation, a one-dimensional (1D) case is first introduced, followed by the coupling of a 2D acoustic cavity with a beam and a 3D one with a plate. The proposed method is validated with FEM simulations on

关键词： fluid-structure interaction Vibroacoustics Elastoacoustics Displacement continuity Nullspace method

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Comparative study on the oblique water-entry of high-speed projectile based on rigid-body and elastic-plastic body model

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Defence Technology(防务技术) 2025年第4期46卷 133-155页

作者： Xiangyan Liu Xiaowei Cai Zhengui Huang Yu Hou Jian Qin Zhihua Chen National Key Laboratory of Transient Physics Nanjing University of Science and TechnologyNanjing210094China National Key Laboratory of Hydrodynamics China Ship Scientific Research CenterWuxi214082China School of Electrical Engineering and Automation Nantong UniversityNantong226019China

To examine the similarities and differences in the evolution of cavity,wetting and dynamics of a highspeed,oblique water-entry projectile with different positive angles of attack,a comparative analysis has been conducted based on the numerical results of two mathematical models,the rigid-body model and fluid-structure interaction *** addition,the applicable scope of the above two methods,and the structural response characteristics of the projectile have also been *** results demonstrate that:(1) The impact loads and angular motion of the projectile of the rigid-body method are more likely to exhibit periodic variations due to the periodic tail slap,its range of positive angles of attack is about α<2°.(2) When the projectile undergone significant wetting,a strong coupling effect is observed among wetting,structural deformation,and projectile *** the applied projectile shape,it is observed that,when the projectile bends,the final wetting position is that of Part B(cylinder of body).With the occu rrence of this phenomenon,the projectile ballistics beco me completely unstable.(3) The force exerted on the lower surface of the projectile induced by wetting is the primary reason of the destabilization of the projectile traj ectory and structu ral deformation *** deformation is most likely to appear at the junction of Part C(cone of body) and Part D(tail).The safe angles of attack of the projectile stability are found to be about α≤2°.

关键词： fluid-structure interaction Rigid-body model Elastic-plastic model Structural deformation Impact loads Structural safety of projectile

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Differentiability Properties for Boundary Control of fluid-structure interactions of Linear Elasticity with Navier-Stokes Equations with Mixed-Boundary Conditions in a Channel

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APPLIED MATHEMATICS AND OPTIMIZATION 2023年第2期87卷 15-15页

作者： Hintermueller, Michael Kroener, Axel Weierstrass Inst Appl Anal & Stochast Mohrenstr 39 D-10117 Berlin Germany Martin Luther Univ Halle Wittenberg D-06099 Halle An Der Saale Germany

In this paper we consider a fluid-structure interaction problem given by the steady Navier Stokes equations coupled with linear elasticity taken from (Lasiecka et al. in Nonlinear Anal 44:54-85, 2018). An elastic body surrounded by a liquid in a rectangular domain is deformed by the flow which can be controlled by the Dirichlet boundary condition at the inlet. On the walls along the channel homogeneous Dirichlet boundary conditions and on the outflow boundary do-nothing conditions are prescribed. We recall existence results for the nonlinear system from that reference and analyze the control to state mapping generalizing the results of (Wollner and Wick in J Math fluid Mech 21:34, 2019) to the setting of the nonlinear Navier-Stokes equation for the fluid and the situation of mixed boundary conditions in a domain with corners.

关键词： fluid-structure interaction Boundary control Differentiability properties Navier Stokes equation Mixed boundary conditions Domain with corners

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Numerical study of relationships between flows and structural characteristics of the rotor in a rim-driven hubless thruster using a strongly-coupling FSI algorithm

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OCEAN ENGINEERING 2025年 323卷

作者： Yang, Chun Yao, Hua-Dong Sun, Cong Wang, Chao Guo, Chunyu Lin, Jianfeng Harbin Engn Univ Coll Shipbldg Engn Harbin 150001 Peoples R China Chalmers Univ Technol Dept Mech & Maritime Sci Div Marine Technol S-41296 Gothenburg Sweden Harbin Engn Univ Qingdao Innovat & Dev Ctr Qingdao 266000 Peoples R China Chinese Acad Sci Inst Mech State Key Lab Nonlinear Mech Beijing 100190 Peoples R China

The shaftless rim-driven thruster (RDT), as a new type of ship propulsion method, has attracted more and more attention in recent years. In this study, RDT was employed. Firstly, the open water performance of RDT with rigid blade was numerically studied based on the Detached Eddy Simulation (DES). Subsequently, A two-way fluid- structure interaction (FSI) method was adopted to simulate the effects of four flexible blades on the hydrodynamic performance and pulsating pressure. The differences between the hydrodynamic coefficients, flow fields, von Mises stress (VMS), blade deformation, and excitation forces of the flexible and rigid RDT were analyzed. The results show that the blade deformation leads to the loss of thrust and overall efficiency, and the smaller the Young's modulus, the greater the loss of thrust and overall efficiency. As the Young's modulus decreases, the blade deformation in the axial, tangential and radial directions increases, and blade deformation in the axial plays a dominant role in the three directions. Compared with the rigid RDT, blade deformation increases the pulsating pressure of the upstream freestream of blade and weakens the pulsating pressure of the downstream freestream of blade. These findings will provide a reference for the design and optimization of RDT rotor.

关键词： Rim-driven thruster fluid-structure interaction Hydrodynamic performance Pulsating pressure Detached eddy simulation

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Effects of sweep angle and flexural stiffness of a tuna-like caudal fin on its swimming performance

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OCEAN ENGINEERING 2025年 326卷

作者： Xie, Menghua Pu, Tianmei Zhou, Chunhua Guo, Chengpeng Zhang, Yang Nanjing Univ Aeronaut & Astronaut Coll Astronaut Nanjing 211106 Peoples R China Yangzhou Univ Coll Elect Energy & Power Engn Yangzhou 225127 Peoples R China AVIC Aerodynam Res Inst Shenyang 110034 Peoples R China

Tuna, renowned for their efficient swimming capabilities, feature flexible lunate caudal fins with a wide range of sweep angles. However, the interplay of sweep angle and flexibility on its swimming performance remains largely unexplored. In this work, a high-fidelity immersed-boundary/finite-element fluid-structure interaction solver is employed to investigate the combined effects of sweep angle and uniform/non-uniform spanwise flexural stiffness on the swimming performance of a tuna-like caudal fin. The swimming performance of the caudal fin is evaluated for three sweep angles across three distinct Strouhal numbers. For the uniform flexibility distribution, efficient swimming of a tuna's caudal fin depends significantly on its sweep angle, flexibility, and locomotion frequency. When the surface area of the caudal fin remains constant, smaller sweep angles generally improve thrust production and swimming efficiency by altering the caudal fin wake. For each sweep angle, greater flexural stiffness and higher Strouhal numbers enhance thrust production, though this does not always correspond to improved swimming efficiency. For the non-uniform flexibility distribution, the cupping and heterocercal profiles are analyzed at St = 0.4, and their swimming performance is compared to that of the uniform profile. The results indicate that the heterocercal profile, characterized by its asymmetric flexibility distribution, consistently achieves the highest efficiency across all sweep angles compared to the cupping and uniform profiles.

关键词： Caudal fin Sweep angle Swimming performance Structural flexibility fluid-structure interaction

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A novel ROM-based FSI model of composite blisk with blades-disk coupling for flutter analysis

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AEROSPACE SCIENCE AND TECHNOLOGY 2025年 159卷

作者： Xu, Qian Hou, Lei Hou, Lixian Li, Zhonggang Ren, Shuangxing Duraihem, Faisal Z. Awwad, Emad Mahrous Saeed, Nasser A. Harbin Inst Technol Sch Astronaut Harbin 150001 Peoples R China Shanghai Space Prop Technol Res Inst Shanghai 201109 Peoples R China King Saud Univ Coll Sci Dept Math POB 2455 Riyadh 11451 Saudi Arabia King Saud Univ Coll Engn Dept Mech Engn POB 800 Riyadh 11421 Saudi Arabia Menoufia Univ Fac Elect Engn Dept Phys & Engn Math Menoufia 32952 Egypt Appl Sci Private Univ Appl Sci Res Ctr Amman 11937 Jordan

With the trend of blisk becoming lightweight, compact, and material-composite, fluid-structure interaction (FSI) in blisk flutter analysis becomes increasingly unignorable. Direct numerical simulation of FSI consumes a large amount of computing resources, and there has been very little research on the mechanism of influence of blades- disk coupling on the flutter characteristics of blisk. This paper proposes a novel low-dimensional FSI model which is integrated with blades-disk coupling and composite materials, for the study of composite blisk flutter analysis. The structural dynamics subsystem is built using a semi-analytical global modal method, while the aerodynamic subsystem is built using a reduced-order method based on system identification. The FSI model proposed in this paper is firstly validated by existing blisk aeroelastic examples, and then extended to study blades-disk coupling, modes coupling, bending-torsion coupling, and material parameter studies. The results show that the dramatic increase in the degree of blades bending-torsion coupling caused by blades-disk coupling is the main reason for the sharp decrease of aeroelastic stability of flexible-disk blisk, especially in the low nodal diameter (ND) mode of each modes set, the modes coupling occurs in the double combination modes of blisk which are time- depend orthogonal in FSI modes, and the dual regulation of material parameters on density and elastic constants makes the effects of material parameters on the two blisk mode sets different. The FSI model and analysis results presented in this paper provide meaningful theoretical guidance for the aeroelastic design of composite blisk.

关键词： fluid-structure interaction Flutter Blades-disk coupling Composite blisk Reduced-order model

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