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Academic literature on the topic 'Aero-Structural coupling'

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Published: 4 June 2021
Last updated: 21 February 2023

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Journal articles on the topic "Aero-Structural coupling"

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Zuo, YingTao, ZhengHong Gao, Gang Chen, XiaoPeng Wang, and YueMing Li. "Efficient aero-structural design optimization: Coupling based on reverse iteration of structural model." Science China Technological Sciences 58, no. 2 (December 29, 2014): 307–15. http://dx.doi.org/10.1007/s11431-014-5744-5.

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Yang, Wenjun, Huiqun Yuan, and Tianyu Zhao. "Multi-field coupling dynamic characteristics based on Kriging interpolation method." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 6 (May 16, 2016): 1088–99. http://dx.doi.org/10.1177/0954410016648350.

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Multi-field coupling problems are taken more and more attention mainly because of the higher requirement of load, efficiency, and reliability in aero-engine operation. This research takes an aero-engine compressor as the research object, 3D flow field and structural models are established. For the method of cyclic symmetric, single-sector model is selected as the calculation domain. Considering the influence of former stator wakes, compressor flow field is simulated. The article analyzes the distribution law of unsteady aerodynamic load on rotor blade. Based on Kriging model, load transfer of aerodynamic pressure and temperature is achieved from flow field to blade structure. Then the effects of centrifugal force, aerodynamic pressure and temperature load are discussed on compressor vibration characteristic and structural strength. The results show dominant fluctuation frequencies of aerodynamic load on rotor blade are manly at frequency doubling of stator–rotor interaction, especially at one time frequency (1 × f0). Magnitude and pulsation amplitude on pressure surface are far greater than that on suction surface. Load transfer with Kriging model has a higher precision, it can meet the requirement of multi-field coupling dynamic calculation. In multi-field coupling interaction, temperature load makes the natural vibration frequencies decrease obviously, centrifugal force is the main source of deformation and stress. Bending stress induced by aerodynamic pressure and temperature load can counteract part of bending stress induced by centrifugal force. However, temperature load causes the maximum displacement of blade-disk system to increase.
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Chudý, Peter, and Vladimír Daněk. "DYNAMICS OF AN ELASTIC AIRPLANE." Aviation 9, no. 1 (March 31, 2005): 8–13. http://dx.doi.org/10.3846/16487788.2005.9635890.

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This paper presents the work performed by the Institute of Aerospace Engineering at the Brno University of Technology. The purpose of the project was to compare the results obtained from classical analytical solutions and a complex numerical simulation of an airplane's aero elastic response. Compared to the analytical solution, which reduces the entire process to a straightforward manipulation with time‐proven graphs and tables, the numerical simulation offers a more complex description of the dynamic processes. A complex simulation, in contrast to the analytical solution providing us with only one estimated parameter, allows monitoring selected quantities in the time domain, thus giving us a tool for a visual qualification of the investigated process. In the past, dynamic aeroelastic properties were estimated utilizing simplified stick beam models. The desire for more complex aero elastic simulations led to the concept of the advanced aero elastic model, coupling advanced 3D structural FEM models with proven aerodynamic theory in the form of the DLM panel method.
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Ma, Yingqun, Qingjun Zhao, Kai Zhang, Meng Xu, and Wei Zhao. "Effects of mount positions on vibrational energy flow transmission characteristics in aero-engine casing structures." Journal of Low Frequency Noise, Vibration and Active Control 39, no. 2 (May 17, 2019): 313–26. http://dx.doi.org/10.1177/1461348419845506.

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The main goal of the study is to apply the structural intensity method to analyze the effects of positions of the main-mount and the sub-mount on the vibrational energy flow transmission characteristics in aero-engine casing structures, so as to attenuate the vibration of the casing and the whole aero-engine. Structural intensity method, indicating magnitude and direction of the vibrational energy flow, is a powerful tool to study vibration problems from the perspective of energy. In this paper, a casing-support-rotor coupling model subjected to the rotor unbalanced forces is established by the finite element method. Formulations of the structural intensity of a shell element and the structural intensity streamline are given. A simulation system consisting of the finite element tool and the in-house program is developed to carry out forced vibration analysis and structural intensity calculation. The structural intensity field of the casing is visualized in the forms of vector diagram and streamline representation. The vibrational energy flow behaviors of the casing at the rotor design rotating speed are analyzed, and the vibrational energy flow transmission characteristics of the casing with different axial positions of the main-mount and the sub-mount are investigated. Moreover, some measures to attenuate the vibration of the casing are obtained from the numerical results, and their effectiveness is verified in the frequency domain and the time domain. The results shed new light on the effects of the mount positions on the vibration energy transmission behaviors of the casing structure. The structural intensity method is a more advanced tool for solving vibration problems in engineering. Furthermore, it may provide some guidance for the vibration attenuation of the casing and the whole aero-engine.
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Tang, Hong, Guo Guang Chen, and Hui Zhu He. "An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model." Applied Mechanics and Materials 215-216 (November 2012): 438–42. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.438.

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Coupling between the vibration frequencies and the unsteady aerodynamic will reduce the flutter speed and ride quality through the aerodynamic heat transfer. As the flight speed improved, the aeroelastic analysis has become an essential means of aircraft design. The method of aero-thermo-elastic (ATE) analysis is coupled with aircraft aeroelastic analysis and thermal deformation, and is more realistic reflection of the actual flight of the aircraft. In this paper, an ATE analysis of aircraft adopted by computational fluid dynamics/computational structural dynamics (CFD/CSD) methods, and compared with the traditional analysis, to provide analytical tools for the supersonic aircraft design.
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Jin, Zhu, Moli Chen, Gui-Huo Luo, and Lin Yue. "Analysis of the effect of squeeze film damper on the bending-torsional coupling vibration characteristics of dual-rotor system." 59th International Conference on Vibroengineering in Dubai, United Arab Emirates, October 22, 2022 45 (October 22, 2022): 1–7. http://dx.doi.org/10.21595/vp.2022.22902.

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The study of the vibration reduction characteristics of SFD to the bending-torsional coupled vibration of the dual-rotor system can provide support for the structural design of aero-engines. Based on the overall eccentric disc model, the bending-torsional coupling dynamic equation of the dual-rotor system is established in this paper. The amplitude and nonlinear periodic characteristics of the dual-rotor system are obtained by combining Newmark-β method and Newton-Raphson method. The results show that the vibration reduction effect of SFD on bending-torsional coupling vibration is closely related to the speed. The vibration reduction effect of SFD is weak at the first-order critical speed range and below, and reduces the torsional amplitude by 70 % at the second-order critical speed range and above. SFD kept the bending-torsional coupling vibration of the dual-rotor system stable in a stable 5-period motion state.
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Shi, Ao, Bo Lu, Dangguo Yang, Xiansheng Wang, Junqiang Wu, and Fangqi Zhou. "Study on model design and dynamic similitude relations of vibro-acoustic experiment for elastic cavity." Modern Physics Letters B 32, no. 12n13 (May 10, 2018): 1840047. http://dx.doi.org/10.1142/s021798491840047x.

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Coupling between aero-acoustic noise and structural vibration under high-speed open cavity flow-induced oscillation may bring about severe random vibration of the structure, and even cause structure to fatigue destruction, which threatens the flight safety. Carrying out the research on vibro-acoustic experiments of scaled down model is an effective means to clarify the effects of high-intensity noise of cavity on structural vibration. Therefore, in allusion to the vibro-acoustic experiments of cavity in wind tunnel, taking typical elastic cavity as the research object, dimensional analysis and finite element method were adopted to establish the similitude relations of structural inherent characteristics and dynamics for distorted model, and verifying the proposed similitude relations by means of experiments and numerical simulation. Research shows that, according to the analysis of scale-down model, the established similitude relations can accurately simulate the structural dynamic characteristics of actual model, which provides theoretic guidance for structural design and vibro-acoustic experiments of scaled down elastic cavity model.
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Aye, Moe Moe, and Uwe Ritschel. "Global Dynamic Response of a Medium-Sized Floating Offshore Wind Turbine with Stall Regulation." Energies 15, no. 1 (December 27, 2021): 166. http://dx.doi.org/10.3390/en15010166.

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In this paper, a two-bladed medium-sized floating wind turbine with variable speed and power regulation by stall is studied. For floating offshore wind turbines, the major challenges are related to the dynamical behavior of the system in response to combined wind and wave loading. Especially for smaller systems, the coupling of aerodynamic and wave forces may lead to large amplitude motions. Coupled aero-hydro-servo-elastic simulations are carried out in OpenFAST. The goal of the study is to investigate the global dynamic response of the hypothetical wind turbine with stall regulation. Stall regulation concept is proposed and the structural loads are computed and results are presented and discussed.
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Shi, Yu, Shuiting Ding, Peng Liu, Tian Qiu, Chuankai Liu, Changbo Qiu, and Dahai Ye. "Swirl Flow and Heat Transfer in a Rotor-Stator Cavity with Consideration of the Inlet Seal Thermal Deformation Effect." Aerospace 10, no. 2 (January 31, 2023): 134. http://dx.doi.org/10.3390/aerospace10020134.

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In the typical structure of a turboshaft aero-engine, the mass flow of the cooling air in the rotor-stator cavity is controlled by the inlet seal labyrinth. This study focused on the swirl flow and heat transfer characteristics in a rotor-stator cavity with considerations of the inlet seal thermal deformation effect. A numerical framework was established by integrating conjugate heat transfer (CHT) analysis and structural finite element method (FEM) analysis to clarify the two-way aero-thermo-elasto coupling interaction among elastic deformation, leakage flow, and heat transfer. Simulation results showed that the actual hot-running clearance was non-uniform along the axial direction due to the temperature gradient and inconsistent structural stiffness. Compared with the cold-built clearance (CC), the minimum tip clearance of the actual non-uniform hot-running clearance (ANHC) was reduced by 37–40%, which caused an increase of swirl ratio at the labyrinth outlet by 5.3–6.9%, a reduction of the Nusselt number by up to 69%. The nominal uniform hot-running clearance (NUHC) was defined as the average labyrinth tip clearance. The Nusselt number of the rotating disk under the ANHC was up to 81% smaller than that under the NUHC. Finally, a clearance compensation method was proposed to increase the coolant flow and decrease the metal temperature.
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Pei, Xi, Min Xu, and Dong Guo. "Aeroelastic-Acoustics Numerical Simulation Research." Applied Mechanics and Materials 226-228 (November 2012): 500–504. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.500.

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The generation of aerodynamic noise of aircraft in flight is due to dynamical system and aerodynamic .The response of aircraft subjected to High acoustic loads and aerodynamic loads can produce fatigue and damage. In this paper a new Aeroelastic- Acoustics which adds acoustic loads in aeroelastic is presented. The emphasis of the study is the discipline of displacement and load of the flexible structure under the unsteady aerodynamic, inertial, elastic and aero-acoustic. The CFD/CSD/CAA coupling is used to simulate rockets cabin. Sound generated by a rocker is predicted numerically from a Large Eddy simulation (LES) of unsteady flow field. The Lighthill acoustic analogy is used to model the propagation of sound. The structural response of rocket cabin was given. The boundary-layer transition on the pressure side of the cabin is visualized, by plotting to better illustrate the essential interaction between fluctuating pressure and structure.CFD/CSD/CAA coupling compute method is validated in low and middle frequency.
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Dissertations / Theses on the topic "Aero-Structural coupling"

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Vesel, Richard W. Jr. "Aero-Structural Optimization of a 5 MW Wind Turbine Rotor." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1331134966.

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Damp, Lloyd Hollis. "Multi-Objective and Multidisciplinary Design Optimisation of Unmanned Aerial Vehicle Systems using Hierarchical Asynchronous Parallel Multi-Objective Evolutionary Algorithms." Thesis, The University of Sydney, 2007. http://hdl.handle.net/2123/1858.

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The overall objective of this research was to realise the practical application of Hierarchical Asynchronous Parallel Evolutionary Algorithms for Multi-objective and Multidisciplinary Design Optimisation (MDO) of UAV Systems using high fidelity analysis tools. The research looked at the assumed aerodynamics and structures of two production UAV wings and attempted to optimise these wings in isolation to the rest of the vehicle. The project was sponsored by the Asian Office of the Air Force Office of Scientific Research under contract number AOARD-044078. The two vehicles wings which were optimised were based upon assumptions made on the Northrop Grumman Global Hawk (GH), a High Altitude Long Endurance (HALE) vehicle, and the General Atomics Altair (Altair), Medium Altitude Long Endurance (MALE) vehicle. The optimisations for both vehicles were performed at cruise altitude with MTOW minus 5% fuel and a 2.5g load case. The GH was assumed to use NASA LRN 1015 aerofoil at the root, crank and tip locations with five spars and ten ribs. The Altair was assumed to use the NACA4415 aerofoil at all three locations with two internal spars and ten ribs. Both models used a parabolic variation of spar, rib and wing skin thickness as a function of span, and in the case of the wing skin thickness, also chord. The work was carried out by integrating the current University of Sydney designed Evolutionary Optimiser (HAPMOEA) with Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) tools. The variable values computed by HAPMOEA were subjected to structural and aerodynamic analysis. The aerodynamic analysis computed the pressure loads using a Boeing developed Morino class panel method code named PANAIR. These aerodynamic results were coupled to a FEA code, MSC.Nastran® and the strain and displacement of the wings computed. The fitness of each wing was computed from the outputs of each program. In total, 48 design variables were defined to describe both the structural and aerodynamic properties of the wings subject to several constraints. These variables allowed for the alteration of the three aerofoil sections describing the root, crank and tip sections. They also described the internal structure of the wings allowing for variable flexibility within the wing box structure. These design variables were manipulated by the optimiser such that two fitness functions were minimised. The fitness functions were the overall mass of the simulated wing box structure and the inverse of the lift to drag ratio. Furthermore, six penalty functions were added to further penalise genetically inferior wings and force the optimiser to not pass on their genetic material. The results indicate that given the initial assumptions made on all the aerodynamic and structural properties of the HALE and MALE wings, a reduction in mass and drag is possible through the use of the HAPMOEA code. The code was terminated after 300 evaluations of each hierarchical level due to plateau effects. These evolutionary optimisation results could be further refined through a gradient based optimiser if required. Even though a reduced number of evaluations were performed, weight and drag reductions of between 10 and 20 percent were easy to achieve and indicate that the wings of both vehicles can be optimised.
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Damp, Lloyd Hollis. "Multi-Objective and Multidisciplinary Design Optimisation of Unmanned Aerial Vehicle Systems using Hierarchical Asynchronous Parallel Multi-Objective Evolutionary Algorithms." University of Sydney, 2007. http://hdl.handle.net/2123/1858.

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Master of Engineering (Research)
The overall objective of this research was to realise the practical application of Hierarchical Asynchronous Parallel Evolutionary Algorithms for Multi-objective and Multidisciplinary Design Optimisation (MDO) of UAV Systems using high fidelity analysis tools. The research looked at the assumed aerodynamics and structures of two production UAV wings and attempted to optimise these wings in isolation to the rest of the vehicle. The project was sponsored by the Asian Office of the Air Force Office of Scientific Research under contract number AOARD-044078. The two vehicles wings which were optimised were based upon assumptions made on the Northrop Grumman Global Hawk (GH), a High Altitude Long Endurance (HALE) vehicle, and the General Atomics Altair (Altair), Medium Altitude Long Endurance (MALE) vehicle. The optimisations for both vehicles were performed at cruise altitude with MTOW minus 5% fuel and a 2.5g load case. The GH was assumed to use NASA LRN 1015 aerofoil at the root, crank and tip locations with five spars and ten ribs. The Altair was assumed to use the NACA4415 aerofoil at all three locations with two internal spars and ten ribs. Both models used a parabolic variation of spar, rib and wing skin thickness as a function of span, and in the case of the wing skin thickness, also chord. The work was carried out by integrating the current University of Sydney designed Evolutionary Optimiser (HAPMOEA) with Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) tools. The variable values computed by HAPMOEA were subjected to structural and aerodynamic analysis. The aerodynamic analysis computed the pressure loads using a Boeing developed Morino class panel method code named PANAIR. These aerodynamic results were coupled to a FEA code, MSC.Nastran® and the strain and displacement of the wings computed. The fitness of each wing was computed from the outputs of each program. In total, 48 design variables were defined to describe both the structural and aerodynamic properties of the wings subject to several constraints. These variables allowed for the alteration of the three aerofoil sections describing the root, crank and tip sections. They also described the internal structure of the wings allowing for variable flexibility within the wing box structure. These design variables were manipulated by the optimiser such that two fitness functions were minimised. The fitness functions were the overall mass of the simulated wing box structure and the inverse of the lift to drag ratio. Furthermore, six penalty functions were added to further penalise genetically inferior wings and force the optimiser to not pass on their genetic material. The results indicate that given the initial assumptions made on all the aerodynamic and structural properties of the HALE and MALE wings, a reduction in mass and drag is possible through the use of the HAPMOEA code. The code was terminated after 300 evaluations of each hierarchical level due to plateau effects. These evolutionary optimisation results could be further refined through a gradient based optimiser if required. Even though a reduced number of evaluations were performed, weight and drag reductions of between 10 and 20 percent were easy to achieve and indicate that the wings of both vehicles can be optimised.
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Book chapters on the topic "Aero-Structural coupling"

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Ramachandran, G. K. V., L. Sahlberg-Nielsen, A. Acampora, H. Jia, and C. Brown. "Coupling of aero-elastic and structural codes to carry out integrated load analysis of floating wind turbines." In Trends in Renewable Energies Offshore, 485–90. London: CRC Press, 2022. http://dx.doi.org/10.1201/9781003360773-55.

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Conference papers on the topic "Aero-Structural coupling"

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Haupt, Matthias, Reinhold Niesner, Ralf Unger, and Peter Horst. "Computational Aero-Structural Coupling For Hypersonic Applications." In 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3252.

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Schwartz, Jennifer, Robert Canfield, and Maxwell Blair. "Aero-Structural Coupling and Sensitivity of a Joined-Wing SensorCraft." In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-1580.

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Joshi, Ojas, and Pe´ne´lope Leyland. "Thermal Fluid-Structure Coupling for Atmospheric Entries." In ASME/JSME 2011 8th Thermal Engineering Joint Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajtec2011-44233.

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This paper deals with the modeling of aero-thermal aspects of a space vehicle during its entry phase into an atmosphere. We treat the numerical coupling techniques between the external and internal aero-thermo-dynamics (ATD) produced by the interaction of ATD fields with the structural components. The thermal properties induced within the structure via heat transfer mechanisms of convection, conduction and radiation is taken into account presenting multi-disciplinary coupling between the aero-thermo-dynamics, the heat loads and the structural thermal response.
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Wang, Hua, and Qing Ge. "Deformation Prediction of Aero-Structural Assembly Involving Drilling-Induced Stresses." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36948.

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Drilling is a material removal process which introduces the plastic deformation and stresses around the hole. When large amounts of drilling stresses are added up, there will be deformation in the aero-structural assembly. This work presents a deformation predicting method based on finite element analysis considering drilling stresses. A riveting equivalent unit is employed to simulate the riveting process in order to obtain a balance between accuracy and the computational efficiency in finite element analyzing. Drilling stresses are added up into the riveting process with additional temperature fields in ABAQUS. The assembly of the two riveted plates and the trailing edge were considered to illustrate effects of drilling stresses coupling. The simulation results had shown that drilling stresses had little influence on one riveting deformation. When so many drilling stresses and riveting effects were added up, there will be striking deformation in the aircraft’s structure. The deformation predicting method outlined in this work will enhance the understanding of the compliant components deformation resulting from the drilling stresses, and help systematically improving the precision control efficiency in civil aircraft industry.
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Lindhorst, Klemens, Matthias Haupt, and Peter Horst. "Usage of Time Domain Surrogate Model Approaches for Transient, Nonlinear Aerodynamics Within Aero-Structural Coupling Schemes." In 42nd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2842.

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Marten, David, Matthew Lennie, George Pechlivanoglou, Christian Oliver Paschereit, Alessandro Bianchini, Giovanni Ferrara, and Lorenzo Ferrari. "Benchmark of a Novel Aero-Elastic Simulation Code for Small Scale VAWT Analysis." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75922.

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After almost 20 years of absence from research agendas, interest in the vertical axis wind turbine (VAWT) technology is presently increasing again, after the research stalled in the mid 90’s in favour of horizontal axis turbines (HAWTs). However, due to the lack of research in past years, there are a significantly lower number of design and certification tools available, many of which are underdeveloped if compared to the corresponding tools for HAWTs. To partially fulfil this gap, a structural FEA model, based on the Open Source multi-physics library PROJECT::CHRONO, was recently integrated with the Lifting Line Free Vortex Wake method inside the Open Source wind turbine simulation code QBlade and validated against numerical and experimental data of the SANDIA 34m rotor. In this work some details about the newly implemented nonlinear structural model and its coupling to the aerodynamic solver are first given. Then, in a continuous effort to assess its accuracy, the code capabilities were here tested on a small scale, fast-spinning (up to 450 rpm) VAWT. The study turbine is a helix shaped, 1kW Darrieus turbine, for which other numerical analyses were available from a previous study, including the results coming from both a 1D beam element model and a more sophisticated shell element model. The resulting data represented an excellent basis for comparison and validation of the new aero-elastic coupling in QBlade. Based on the structural and aerodynamic data of the study turbine, an aero-elastic model was then constructed. A purely aerodynamic comparison to experimental data and a BEM simulation represented the benchmark for QBlade aerodynamic performance. Then, a purely structural analysis was carried out and compared to the numerical results from the former. After the code validation, an aero-elastically coupled simulation of a rotor self-start has been performed to demonstrate the capabilities of the newly developed model to predict the highly nonlinear transient aerodynamic and structural rotor response.
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Moon, Wonki, Zhirong Shen, Johyun Kyoung, Hyungtae Lee, Mugyeom Lee, Aldric Baquet, Kanghyun Song, Booki Kim, and Jang Kim. "Time-Domain Response-Based Structural Assessment of a FOWT – Buckling and Ultimate Strength Assessment." In ASME 2022 4th International Offshore Wind Technical Conference. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/iowtc2022-96497.

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Abstract For more economic power generation, the blade size of offshore floating wind turbine becomes bigger than floating substructure. Consequently, structural load from wind turbine to floating substructure under unsteady turbulent wind condition becomes more important for structural strength assessment. In conventional load-based structural strength assessment, the coupling effect between hull motion and turbine loading is ignored so that the strength assessment based on the conventional methods has high uncertainties. Therefore, class societies recommend fully coupled time-domain analysis of the floating offshore wind turbine and subsequent response-based structural analysis to assess the structural strength. Present paper introduces an efficient time-domain structural analysis for buckling and ultimate strength assessment. For various design load cases, full-blown time-domain structural analyses are performed by mapping the aero-elastic, hydrodynamic, hydrostatic, inertial and mooring loadings to finite-element structural model. An efficient pseudo-spectral stress synthesizer based on ‘lodal’ response analysis is introduced to enhance the computational efficiency of time-domain structural analysis. As an application, a floating offshore wind turbine platform designed for Korean offshore wind farm projects is used. Based on full-blown time domain structural analysis, buckling and ultimate strength assessments are performed following the Class Rule provided by Korean Register.
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Braaten, Mark E., and Arathi Gopinath. "Aero-Structural Analysis of Wind Turbine Blades With Sweep and Winglets: Coupling a Vortex Line Method to ADAMS/AeroDyn." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45904.

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The FAST/ADAMS/AeroDyn system of codes has been widely used to perform the aero-structural analysis of conventional wind turbine blades. Recent advances in blade design involve the development of aeroelastic tailored blades with large amounts of sweep, and blades with winglets. However, the existing Blade Element Momentum (BEM) approach in AeroDyn is limited to straight blades and does not account for sweep or dihedral effects. The goal of this work is to obtain higher fidelity aerodynamic loads predictions for such advanced blade designs. A Vortex Line Method (VLM) for computing aerodynamic loads has been coupled to ADAMS through modification of the existing AeroDyn interface. The VLM approach adopted here adds fidelity by modeling the effects of sweep, dihedral, 3D wakes, and wake dynamics. An existing steady/unsteady VLM code with these capabilities was restructured to allow its integration with AeroDyn. The FAST routines from NREL, which are used as a preprocessor to ADAMS, and the ADAMS/AeroDyn interface itself, were also modified to create an ADAMS model that properly accounts for the curvature of the blade that occurs when large amounts of sweep or winglets are present. The resulting ADAMS/VLM model was compared to the original ADAMS/BEM model for a straight blade and for a highly swept blade. The model was also applied to blades with pressure-side and suction-side winglet configurations. The BEM and VLM models give similar aero predictions for the straight blade, as expected. The induced twist and blade deformations are found to be more similar for the two methods than the aerodynamic loads. Computations were made for the blades with the winglets at different wind speeds and different pitch settings, and results were obtained for blade deflection, induced twist, and thrust and torque force distributions.
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Li, Jun, Jie Hong, Yanhong Ma, and Dayi Zhang. "Modelling of Misaligned Rotor Systems in Aero-Engines." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85706.

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Based on the analysis of structural and dynamic characteristics, a dynamic model of flexible rotor system under misalignment and unbalance excitation in aero-engine was developed through Lagrange equations. The model describes the mechanism and influencing factors of nonlinear properties of misaligned rotors. Then some numerical simulations were performed in order to get the vibration response in time and frequency domain. The results suggest that the rotor system and its coupling may behave in a complex and nonlinear way with the excitation of misalignment and unbalance. The response of the system contains 1× and 2× harmonics, and the spectrum signature closely relate to the misalignment magnitude and the distribution of unbalance mass. A series of experiments were also designed to verify the dynamic model. Their characteristics of response are in good agreement.
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Gueydon, Sébastien, Koert Lindenburg, and Feike Savenije. "Coupling of Two Tools for the Simulation of Floating Wind Turbines." In ASME 2013 32nd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/omae2013-11174.

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For the design of a floating wind turbine it is necessary to take the loading due to the wind, wave and current in equal consideration. The PHATAS computer program from ECN (Energy research Centre of the Netherlands) is a time-domain aero-elastic simulation program, that accounts for the complete mutual interaction of unsteady rotor aerodynamics, structural dynamics of the rotor blades and tower, and interaction with the turbine controller under influence of turbulent wind and wave loading for fixed wind turbines. The aNySIM computer program from MARIN is a multi rigid body time domain model that accounts for wave loadings, current loadings, wind loadings, floating body dynamics, mooring dynamics. The coupled computer program aNySIM / PHATAS accounts for all loadings acting on a floating wind turbine and its response whereas PHATAS can only be used for fixed wind turbines onshore and offshore. This paper reports on the dynamic coupling between PHATAS and aNySIM. As a typical case study, the controller for floating offshore wind turbines is evaluated. This new tool has been used to repeat phase IV of the Offshore Code Comparison Collaboration (OC3) within IEA Wind Task 23, regarding floating wind turbine modelling. The results of these simulations are presented in this paper.
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You might also be interested in the extended bibliographies on the topic 'Aero-Structural coupling' for particular source types:
Journal articles
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