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Journal articles on the topic 'Stall Flutter'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

Li, Nailu, Mark J. Balas, Pourya Nikoueeyan, Hua Yang, and Jonathan W. Naughton. "Stall Flutter Control of a Smart Blade Section Undergoing Asymmetric Limit Oscillations." Shock and Vibration 2016 (2016): 1–14. http://dx.doi.org/10.1155/2016/5096128.

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Stall flutter is an aeroelastic phenomenon resulting in unwanted oscillatory loads on the blade, such as wind turbine blade, helicopter rotor blade, and other flexible wing blades. Although the stall flutter and related aeroelastic control have been studied theoretically and experimentally, microtab control of asymmetric limit cycle oscillations (LCOs) in stall flutter cases has not been generally investigated. This paper presents an aeroservoelastic model to study the microtab control of the blade section undergoing moderate stall flutter and deep stall flutter separately. The effects of different dynamic stall conditions and the consequent asymmetric LCOs for both stall cases are simulated and analyzed. Then, for the design of the stall flutter controller, the potential sensor signal for the stall flutter, the microtab control capability of the stall flutter, and the control algorithm for the stall flutter are studied. The improvement and the superiority of the proposed adaptive stall flutter controller are shown by comparison with a simple stall flutter controller.

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2

OKAWA, Hirohisa. "Stall flutter of helicopter blade." Journal of the Japan Society for Aeronautical and Space Sciences 33, no. 377 (1985): 332–39. http://dx.doi.org/10.2322/jjsass1969.33.332.

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3

Ekaterinaris, J. A., and M. F. Platzer. "Numerical Investigation of Stall Flutter." Journal of Turbomachinery 118, no. 2 (1996): 197–203. http://dx.doi.org/10.1115/1.2836626.

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Unsteady, separated, high Reynolds number flow over an airfoil undergoing oscillatory motion is investigated numerically. The compressible form of the Reynolds-averaged governing equations is solved using a high-order, upwind biased numerical scheme. The turbulent flow region is computed using a one-equation turbulence model. The computed results show that the key to the accurate prediction of the unsteady loads at stall flutter conditions is the modeling of the transitional flow region at the leading edge. A simplified criterion for the transition onset is used. The transitional flow region is computed with a modified form of the turbulence model. The computed solution, where the transitional flow region is included, shows that the small laminar/transitional separation bubble forming during the pitch-up motion has a decisive effect on the near-wall flow and the development of the unsteady loads. Detailed comparisons of computed fully turbulent and transitional flow solutions with experimental data are presented.

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4

TOKISUE, Hiromitsu, Yasuo MACHIDA, and Hiroyuki TAKATA. "Stall flutter of airfoils of leading edge stall type." Transactions of the Japan Society of Mechanical Engineers Series B 55, no. 510 (1989): 337–43. http://dx.doi.org/10.1299/kikaib.55.337.

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5

Bethi, Rajagopal V., Sai Vishal Reddy Gali, and J. Venkatramani. "Identifying route to stall flutter through stochastic bifurcation analysis." MATEC Web of Conferences 211 (2018): 02011. http://dx.doi.org/10.1051/matecconf/201821102011.

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The interaction of an elastic structure such as an airfoil and fluid flow can give rise to nonlinear phenomenon such as limit cycle oscillations, period doubling or chaos. These phenomena are indicated by a change in the stability behaviour of the dynamical known as bifurcations. Presence of viscous effects in the fluid flow can give rise to flow separation which causes a stability change in the system that is identified to happen via a Hopf bifurcation. In such cases, the airfoil exhibits limit cycle oscillations which are torsionally dominant, known as stall flutter. Despite identifying the route to stall flutter under uniform flow conditions, investigating a stall problem under stochastic wind has received minimal attention. The ability of fluctuating flows to change the stability boundaries and disrupt the route to flutter, compels the need to carry out a stochastic analysis of stalling airfoils. Study of stall flutter in such systems under the influence of a time varying sinusoidal gust is undertaken and the route to flutter is identified by carrying out a stochastic bifurcation analysis.

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6

Chi, R. M., and A. V. Srinivasan. "Some Recent Advances in the Understanding and Prediction of Turbomachine Subsonic Stall Flutter." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 408–17. http://dx.doi.org/10.1115/1.3239741.

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In this paper, some recent advances in the understanding and prediction of subsonic flutter of jet engine fan rotor blades are reviewed. Among the topics discussed are (i) the experimental evidence of mistuning in flutter responses, (ii) new and promising unsteady aerodynamic models for subsonic stall flutter prediction, (iii) an overview of flutter prediction methodologies, and (iv) a new research effort directed toward understanding the mistuning effect on subsonic stall flutter of shrouded fans. A particular shrouded fan of advanced design is examined in the detailed technical discussion.

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7

Zhang, Xiaolin, Haipeng Sun, Yingbo Wang, Shanyao Li, Changle Sun, and Tingrui Liu. "Nonlinear Stall Flutter Suppression of Wind Turbine Blade Based on LMI Method." Journal of Physics: Conference Series 2173, no. 1 (2022): 012045. http://dx.doi.org/10.1088/1742-6596/2173/1/012045.

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Abstract Aiming at the failure of stall flutter in aeroelastic system of wind turbine blade, the active control process of stall flutter based on linear matrix inequality (LMI) design is described. The structural model is a typical blade section model based on spring-mass-damper, and the aerodynamic force is the ONERA stall aerodynamic model suitable for pure pitch motion. Based on the state variables, the nonlinear aeroelastic equations are expanded by Taylor series and linearized by low order approximation. The state feedback gain is calculated through LMI, and the time domain response stability analysis and stall flutter suppression method based on linearization are studied. The simulation results show that the maximum amplitude is greatly reduced after flutter control, and the system can be stabilized in a short time.

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8

Clark, William S., and Kenneth C. Hall. "A Time-Linearized Navier–Stokes Analysis of Stall Flutter." Journal of Turbomachinery 122, no. 3 (1999): 467–76. http://dx.doi.org/10.1115/1.1303073.

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A computational method for predicting unsteady viscous flow through two-dimensional cascades accurately and efficiently is presented. The method is intended to predict the onset of the aeroelastic phenomenon of stall flutter. In stall flutter, viscous effects significantly impact the aeroelastic stability of a cascade. In the present effort, the unsteady flow is modeled using a time-linearized Navier–Stokes analysis. Thus, the unsteady flow field is decomposed into a nonlinear spatially varying mean flow plus a small-perturbation harmonically varying unsteady flow. The resulting equations that govern the perturbation flow are linear, variable coefficient partial differential equations. These equations are discretized on a deforming, multiblock, computational mesh and solved using a finite-volume Lax–Wendroff integration scheme. Numerical modeling issues relevant to the development of the unsteady aerodynamic analysis, including turbulence modeling, are discussed. Results from the present method are compared to experimental stall flutter data, and to a nonlinear time-domain Navier–Stokes analysis. The results presented demonstrate the ability of the present time-linearized analysis to model accurately the unsteady aerodynamics associated with turbomachinery stall flutter. [S0889-504X(00)00203-8]

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9

Abdel-Rahim, A., F. Sisto, and S. Thangam. "Computational Study of Stall Flutter in Linear Cascades." Journal of Turbomachinery 115, no. 1 (1993): 157–66. http://dx.doi.org/10.1115/1.2929200.

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Aeroelastic interaction in turbomachinery is of prime interest to opertors, designers, and aeroelasticans. Operation at off-design conditions may promote blade stall; eventually the stall pattern will propagate around the blade annulus. The unsteady periodic nature of propagating stall will force blade vibration and blade flutter may occur if the stall propagation frequency is entrained by the blade natural frequency. In this work a computational scheme based on the vortex method is used to simulate the flow over a linear cascade of airfoils. The viscous effect is confined to a thin layer, which determines the separation points on the airfoil surfaces. The preliminary structural model is a two-dimensional characteristic section with a single degree of freedom in either bending or torsion. A study of the relationship between the stall propagation frequency and the blade natural frequency has been conducted. The study shows that entrainment, or frequency synchronization, occurs, resulting in pure torsional flutter over a certain interval of reduced frequency. A severe blade torsional amplitude (of order 20 deg) has been computed in the entrainment region, reaching its largest value in the center of the interval. However, in practice, compressor blades will not sustain this vibration and blade failure may occur before reaching such a large amplitude. Outside the entrainment interval the stall propagation is shown to be independent of the blade natural frequency. In addition, computational results show that there is no entrainment in the pure bending mode. Rather, “de-entrainment” occurs with similar flow conditions and similar stall frequencies, resulting in blade buffeting in pure bending.

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10

NISHIZAWA, Toshio, Yasuhiko IIDA, and Hiroyuki TAKATA. "Cascade Wind Tunnel Experiment of Stall Flutter." Transactions of the Japan Society of Mechanical Engineers Series B 65, no. 635 (1999): 2309–16. http://dx.doi.org/10.1299/kikaib.65.2309.

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11

Culler, Ethan C. E., and John A. N. Farnsworth. "Higher frequencies in stall flutter moment development." Journal of Fluids and Structures 85 (February 2019): 181–98. http://dx.doi.org/10.1016/j.jfluidstructs.2019.01.007.

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12

Gill, John D., Vincent R. Capece, and Ronald B. Fost. "Experimental Methods Applied in a Study of Stall Flutter in an Axial Flow Fan." Shock and Vibration 11, no. 5-6 (2004): 597–613. http://dx.doi.org/10.1155/2004/596706.

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Flutter testing is an integral part of aircraft gas turbine engine development. In typical flutter testing blade mounted sensors in the form of strain gages and casing mounted sensors in the form of light probes (NSMS) are used. Casing mounted sensors have the advantage of being non-intrusive and can detect the vibratory response of each rotating blade. Other types of casing mounted sensors can also be used to detect flutter of rotating blades. In this investigation casing mounted high frequency response pressure transducers are used to characterize the part-speed stall flutter response of a single stage unshrouded axial-flow fan. These dynamic pressure transducers are evenly spaced around the circumference at a constant axial location upstream of the fan blade leading edge plane. The pre-recorded experimental data at 70% corrected speed is analyzed for the case where the fan is back-pressured into the stall flutter zone. The experimental data is analyzed using two probe and multi-probe techniques. The analysis techniques for each method are presented. Results from these two analysis methods indicate that flutter occurred at a frequency of 411 Hz with a dominant nodal diameter of 2. The multi-probe analysis technique is a valuable method that can be used to investigate the initiation of flutter in turbomachines.

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13

Razak, Norizham Abdul, Thomas Andrianne, and Grigorios Dimitriadis. "Flutter and Stall Flutter of a Rectangular Wing in a Wind Tunnel." AIAA Journal 49, no. 10 (2011): 2258–71. http://dx.doi.org/10.2514/1.j051041.

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14

Procházka, Pavel, Pavel Šnábl, Sony Chindada, Ondřej Bublík, and Václav Uruba. "On the stall flutter occurrence in a blade cascade set to turbine and compressor geometry." EPJ Web of Conferences 264 (2022): 01032. http://dx.doi.org/10.1051/epjconf/202226401032.

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A blade cascade allowing free pitch movement of five blades was developed in Institute of Thermomechanics. This model is introduced to study the phenomenon of stall flutter existing in rotary bladed wheels of steam turbines and other devices. This article describes how to induce the stall flutter for prescribed boundary conditions (as inlet velocity, various angles of attack, etc.) and gives survey about flow field differences around the cascade set to both the turbine and the compressor geometry. This experimental research utilized time-resolved Particle Image Velocimetry (PIV) to measure and to evaluate statistical quantities of the wake behind the NACA0010 profiles of the cascade. Also dynamical analysis was performed in the form of Fast-Fourier transform and also phase-locked measurement was applied. Gained knowledge will be utilized to design advanced model of the cascade allowing stall flutter examination without the use of ball bearings.

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15

Huang, Huang, Mingming Yang, and Dingxi Wang. "Uncovering the Root Causes of Stall Flutter in a Wide Chord Fan Blisk." International Journal of Turbomachinery, Propulsion and Power 7, no. 4 (2022): 30. http://dx.doi.org/10.3390/ijtpp7040030.

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Flutter was encountered at part speeds in a scaled wide chord fan blisk designed for a civil aeroengine during a rig test when the fan bypass flow was throttled toward its stall boundary. Analysis of the blade tip timing measurement data revealed that the fan blades vibrated at the first flap (1F) mode with nodal diameters of two and three. To facilitate a further rig test and ultimately eliminate the flutter problem, a numerical campaign was launched to help understand the root causes of the flutter. Both the influence coefficient method (ICM) and the traveling wave method (TWM) were employed in the numerical investigation to analyze unsteady flows due to blade vibration, with the intention to corroborate different numerical results and take advantage of each method. To eliminate nonphysical reflections, a sponge layer with an inflated mesh size was used for the extended inlet and outlet regions. Steady flow field and unsteady flow field were examined to relate them to the blade flutter. The influences of vibration frequency, mass flow rate, shock, boundary layer separation and acoustic mode propagation behaviors on the fan flutter stability were also investigated. Particular attention was paid to the acoustic mode propagation behaviors.

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16

Liu, Tingrui. "Aeroservoelastic Pitch Control of Stall-Induced Flap/Lag Flutter of Wind Turbine Blade Section." Shock and Vibration 2015 (2015): 1–20. http://dx.doi.org/10.1155/2015/692567.

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The aim of this paper is to analyze aeroelastic stability, especially flutter suppression for aeroelastic instability. Effects of aeroservoelastic pitch control for flutter suppression on wind turbine blade section subjected to combined flap and lag motions are rarely studied. The work is dedicated to solving destructive flapwise and edgewise instability of stall-induced flutter of wind turbine blade by aeroservoelastic pitch control. The aeroelastic governing equations combine a flap/lag structural model and an unsteady nonlinear aerodynamic model. The nonlinear resulting equations are linearized by small perturbation about the equilibrium point. The instability characteristics of stall-induced flap/lag flutter are investigated. Pitch actuator is described by a second-order model. The aeroservoelastic control is analyzed by three types of optimal PID controllers, two types of fuzzy PID controllers, and neural network PID controllers. The fuzzy controllers are developed based on Sugeno model and intuition method with good results achieved. A single neuron PID control strategy with improved Hebb learning algorithm and a radial basic function neural network PID algorithm are applied and performed well in the range of extreme wind speeds.

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17

Yamasaki, Masahide, Koji Isogai, Takefumi Uchida, and Itsuma Yukimura. "Shock-Stall Flutter of a Two-Dimensional Airfoil." AIAA Journal 42, no. 2 (2004): 215–19. http://dx.doi.org/10.2514/1.9088.

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18

Sisto, F., S. Thangam, and A. Abdel-Rahim. "Computational prediction of stall flutter in cascaded airfoils." AIAA Journal 29, no. 7 (1991): 1161–67. http://dx.doi.org/10.2514/3.10718.

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19

Poirel, Dominique, Luba Goyaniuk, and Azémi Benaissa. "Frequency lock-in in pitch–heave stall flutter." Journal of Fluids and Structures 79 (May 2018): 14–25. http://dx.doi.org/10.1016/j.jfluidstructs.2018.01.006.

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20

Ericsson, Lars E. "Role of Stall Flutter in the Double-Stall Phenomenon of Wind-Turbine Blades." Journal of Aircraft 37, no. 1 (2000): 104–9. http://dx.doi.org/10.2514/2.2567.

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21

Sanders, A. J., K. K. Hassan, and D. C. Rabe. "Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk." Journal of Turbomachinery 126, no. 1 (2004): 166–74. http://dx.doi.org/10.1115/1.1645532.

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Experiments are performed on a modern design transonic shroudless low-aspect ratio fan blisk that experienced both subsonic/transonic and supersonic stall-side flutter. High-response flush mounted miniature pressure transducers are utilized to measure the unsteady aerodynamic loading distribution in the tip region of the fan for both flutter regimes, with strain gages utilized to measure the vibratory response at incipient and deep flutter operating conditions. Numerical simulations are performed and compared with the benchmark data using an unsteady three-dimensional nonlinear viscous computational fluid dynamic (CFD) analysis, with the effects of tip clearance, vibration amplitude, and the number of time steps-per-cycle investigated. The benchmark data are used to guide the validation of the code and establish best practices that ensure accurate flutter predictions.

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22

Liu, Ying, Xiaobo Zhang, and Fei Zhang. "Simulation of flutter suppression for a transonic fan blade based on plasma excitation." MATEC Web of Conferences 355 (2022): 01018. http://dx.doi.org/10.1051/matecconf/202235501018.

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Along with the development of advanced high-performance aero-engines to the higher thrust-weight ratio, further improvement of stage load, the adoption of new materials and new lightweight structures, the aeroelasticity of blade structure is becoming more and more prominent. The high cycle fatigue failure of blades significantly reduces the structural reliability during the process of development and using. At the same time, a large number of failure forms of aero-engine experimental and server can be attributed to aeroelastic problems. Therefore, it is urgent to improve the aeroelastic stability of the blade. One of the most important factors is to suppress the airflow separation, but its mechanism is still unclear. Based on this, this paper combines the aerodynamic damping analysis of energy method with the plasma excitation simulation and references low-speed wind tunnel plasma expansion test to consider the effects of different exciter distributions and intensities on flutter. The results show that stall flutter is related to the flow separation, but the flow separation is not a key factor that determinates whether the flutters occurs or not. Flutter suppression is strongly correlated with the shock wave intensity, amplitude of first harmonic aerodynamic force, low-speed separation and aerodynamic work density. In addition, the relative distribution of the excitation field and the positive work zone also has a direct effect on the suppression of flutter.

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23

Liu, Tingrui. "Stall Flutter Suppression for Absolutely Divergent Motions of Wind Turbine Blade Base on H-Infinity Mixed-Sensitivity Synthesis Method." Open Mechanical Engineering Journal 9, no. 1 (2015): 752–60. http://dx.doi.org/10.2174/1874155x01509010752.

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This paper is devoted to solve the problem of stall flutter suppression for an absolutely divergent blade of small scale wind turbine. The blade is specially designed with absolutely divergent motions for the purpose of determining the most effective methods of active control for stall flutter suppression. A 2-DOF blade section is considered, with a simplified stall nonlinear aerodynamic model being applied. H-infinity mixed-sensitivity synthesis method with a new three-weight regulation is designed to control the time-domain instability of aeroelastic equations, with a third weight being chosen to weight complementary sensitivity for tracking problems and noise attenuation to robust stabilization in H-infinity control. Effects on flutter suppression are investigated based on different structural and external parameters. Apparent effects of H-infinity mixed-sensitivity method are displayed in the paper, when the other common intelligent control methods fail. The research provides a control way for absolutely divergent turbine blade motions.

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24

Rangarajan, Shreenivas, Dheeraj Tripathi, and J. Venkatramani. "Non-normality and transient growth in stall flutter instability." Chaos: An Interdisciplinary Journal of Nonlinear Science 33, no. 3 (2023): 031103. http://dx.doi.org/10.1063/5.0143321.

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The non-normal nature and transient growth in amplitude and energy of a pitch-plunge aeroelastic system undergoing dynamic stall are explored in this paper through numerical and supporting experimental studies. Wind tunnel experiments, carried out for a canonical pitch-plunge aeroelastic system in a subsonic wind tunnel, show that the system undergoes stall flutter instability via a sub-critical Hopf bifurcation. The aeroelastic responses indicate a transient growth in amplitude and energy—possibly triggering the sub-criticality, which is critical from the purview of structural safety. The system also shows transient energy growth followed by decaying oscillation for certain initial conditions, whereas sustained limit cycle oscillations are encountered for other initial conditions at flow speeds lower than the critical speed. The triggering behavior observed in the wind tunnel experiments is understood better by resorting to study the numerical model of the nonlinear aeroelastic system. To that end, a modified semi-empirical Leishman–Beddoes dynamic stall model is adopted to represent the nonlinear aerodynamic loads of the pitch-plunge aeroelastic system. The underlying linear operator and its pseudospectral analysis indicate that the aeroelastic system is non-normal, causing amplification in amplitude and energy for a short period.

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25

Ericsson, L. E. "Effect of Karman vortex shedding on airfoil stall flutter." Journal of Aircraft 24, no. 12 (1987): 841–48. http://dx.doi.org/10.2514/3.45528.

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26

Capece, V. R., and Y. M. EL-Aini. "Stall flutter prediction techniques for fan and compressor blades." Journal of Propulsion and Power 12, no. 4 (1996): 800–806. http://dx.doi.org/10.2514/3.24104.

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27

Ganiev, R. F., O. B. Balakshin, and B. G. Kukharenko. "Stall flutter for incomplete synchronization of turbocompressor-blade vibrations." Doklady Physics 55, no. 3 (2010): 124–26. http://dx.doi.org/10.1134/s1028335810030043.

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28

Vahdati, M., A. I. Sayma, J. G. Marshall, and M. Imregun. "Mechanisms and Prediction Methods for Fan Blade Stall Flutter." Journal of Propulsion and Power 17, no. 5 (2001): 1100–1108. http://dx.doi.org/10.2514/2.5850.

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29

LIU, Xiang-ning, and Jin-wu XIANG. "Stall Flutter Analysis of High-Aspect-Ratio Composite Wing." Chinese Journal of Aeronautics 19, no. 1 (2006): 36–43. http://dx.doi.org/10.1016/s1000-9361(11)60265-3.

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30

Benaissa, A., S. Biskri, L. Goyaniuk, D. Poirel, and N. Nait Bouda. "Beating phenomenon in frequency lock-in 2DOF stall flutter." Journal of Fluids and Structures 100 (January 2021): 103176. http://dx.doi.org/10.1016/j.jfluidstructs.2020.103176.

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31

Liang, Jiahua, Junqiang Bai, and Guojun Li. "Investigation of Stall Flutter Based on Peters-ONERA Aerodynamic Model." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 5 (2018): 875–83. http://dx.doi.org/10.1051/jnwpu/20183650875.

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The Peters model is used to simulate the linear aerodynamic force and ONERA stall model is used to simulate the nonlinear aerodynamic force. The state-space equation of the aeroelastic system is established by coupling the structural equation. In order to solve problems, Euler predictor corrector method is used in the time domain and eigenvalue analysis method is used in the frequency domain. The case of dynamic stall is simulated based on Peters-ONERA model and the results imply that the validity of the aerodynamic model. The effect of under relaxation iteration on the stability of static aeroelastic solution is studied. It is found that under relaxation iteration can improve the static aeroelastic solution stability. Then based on frequency and time domain methods, flutter critical characteristic and bifurcation phenomenon are studied. It is found that:(1) Under large angle of attack, the coupling between nonlinear aerodynamic modal and structure modal could induce the instability of the structure modal and single degree of freedom flutter. (2) Under different angles of attack, bifurcation characteristic of aeroelastic system is far different. (3) The sensitivity to the disturbance of the system is different in different ranges. When the disturbance increases, the aeroelastic system will change from stable state to limit cycle oscillation.

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32

Beedy, J., G. Barakos, K. J. Badcock, and B. E. Richards. "Non-linear analysis of stall flutter based on the ONERA aerodynamic model." Aeronautical Journal 107, no. 1074 (2003): 495–510. http://dx.doi.org/10.1017/s0001924000134001.

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Abstract This paper presents a simple and efficient way of calculating stall flutter using the ONERA aerodynamic model. At first, the model is presented along with a solution technique based on the harmonic balance method. The parameters of the model are estimated using data either from experiments or CFD calculations and optimised using the Levenberg-Marquardt algorithm. The aerodynamic model is then coupled with a structural one using the Rayleigh-Ritz formulation and a solution technique is devised based on the Newton- Raphson method. Finally the model is used to ‘fit’ aerodynamic loads of oscillating aerofoils generated using CFD. The aeroelastic analysis of a helicopter blade is finally undertaken using material properties found in the literature. The model appears to be robust and efficient and able to fit the unsteady aerodynamics of various cases. The proposed aeroelastic analysis was also found to be efficient and capable of providing adequate results for preliminary analysis of stall flutter.

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33

Isomura, K., and M. B. Giles. "A Numerical Study of Flutter in a Transonic Fan." Journal of Turbomachinery 120, no. 3 (1998): 500–507. http://dx.doi.org/10.1115/1.2841746.

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The bending mode Flutter of a modern transonic fan has been studied using a quasi-three-dimensional viscous unsteady CFD code. The type of flutter in this research is that of a highly loaded blade with a tip relative Mach number just above unity, commonly referred to as transonic stall flutter. This type of Flutter is often encountered in modern wide chord fans without a part span shroud. The CFD simulation uses an upwinding scheme with Roe’s third-order flux differencing, and Johnson and King’s turbulence model with the later modification due to Johnson and Coakley. A dynamic transition point model is developed using the en method and Schubauer and Klebanoff’s experimental data. The calculations of the flow in this fan reveal that the source of the flutter of IHI transonic fan is an oscillation of the passage shock, rather than a stall. As the blade loading increases, the passage shock moves forward. Just before the passage shock unstarts, the stability of the passage shock decreases, and a small blade vibration causes the shock to oscillate with a large amplitude between unstarted and started positions. The dominant component of the blade excitation force is due to the foot of the oscillating passage shock on the blade pressure surface.

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34

Lorber, Peter F., and Franklin O. Carta. "Incipient torsional stall flutter aerodynamic experiments on three-dimensional wings." Journal of Propulsion and Power 10, no. 2 (1994): 217–24. http://dx.doi.org/10.2514/3.23732.

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35

Carta, F. O., and P. F. Lorber. "Experimental study of the aerodynamics of incipient torsional stall flutter." Journal of Propulsion and Power 3, no. 2 (1987): 164–70. http://dx.doi.org/10.2514/3.22969.

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36

Copeland, George Scott. "Reduced-order DAE models for turbomachinery stall, surge, and flutter." ZAMM - Journal of Applied Mathematics and Mechanics / Zeitschrift für Angewandte Mathematik und Mechanik 78, S3 (1998): 883–84. http://dx.doi.org/10.1002/zamm.19980781515.

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37

Bhat, Shantanu S., and Raghuraman N. Govardhan. "Stall flutter of NACA 0012 airfoil at low Reynolds numbers." Journal of Fluids and Structures 41 (August 2013): 166–74. http://dx.doi.org/10.1016/j.jfluidstructs.2013.04.001.

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38

Westin, Michelle F., Jose M. Balthazar, Roberto G. A. da Silva, Mauricio A. Ribeiro, and Angelo M. Tusset. "Characterization of Aeroelastic Behavior in a High Aspect Ratio Wing Using Computational and Wind Tunnel Experiments." Axioms 12, no. 9 (2023): 826. http://dx.doi.org/10.3390/axioms12090826.

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The objective of this article is to characterize an aeroelastic system in terms of its dynamical behavior, which could be either chaotic or periodic before, during, and after achieving the flutter velocity. The aeroelastic system shown here is a wing with a high aspect ratio, which leads to a very flexible behavior subjected to unsteady flow. This paper compares the computational and experimental dynamical behavior of an aeroelastic system at the flutter velocity for the different dynamic stall models proposed. To understand the nonlinear behavior of this system, the traditional attractor reconstruction and Lyapunov exponent calculation are compared with the 0–1 test. In addition to this comparison, two dynamic stall semi-empirical models are applied directly to the time history. All these comparisons show that the computational and wind tunnel experiments are in good agreement, and the dynamic behavior usually gives close results for the 0–1 test and Lyapunov exponent. It is concluded that the system presents chaotic behavior when no dynamic stall correction is applied or when Gangwani’s correction is applied. However, Boeing–Vertol’s correction postpones the chaotic behavior, meaning that the chaotic behavior is only observed for velocities above the flutter.

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Liu, Tingrui, and Wei Xu. "Flap/Lag Stall Flutter Control of Large-Scale Wind Turbine Blade Based on Robust H2Controller." Shock and Vibration 2016 (2016): 1–15. http://dx.doi.org/10.1155/2016/8378161.

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Flap/lag stall nonlinear flutter and active control of anisotropic composite wind turbine blade modeled as antisymmetric beam analysis have been investigated based on robust H2controller. The blade is modeled as single-cell thin-walled beam structure, exhibiting flap bending moment-lag transverse shear deformation, and lag bending moment-flap transverse shear deformation, with constant pitch angle set. The stall flutter control of dynamic response characteristics of composite blade incorporating nonlinear aerodynamic model is investigated based on some structural and dynamic parameters. The aeroelastic partial differential equations are reduced by Galerkin method, with the aerodynamic forces decomposed by strip theory. Robust H2optimal controller is developed to enhance the vibrational behavior and dynamic response to aerodynamic excitation under extreme wind conditions and stabilize structures that might be damaged in the absence of control. The effectiveness of the control algorithm is demonstrated in both amplitudes and frequencies by description of time responses, extended phase planes, and frequency spectrum analysis, respectively.

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Thermann, Hans, and Reinhard Niehuis. "Unsteady Navier-Stokes Simulation of a Transonic Flutter Cascade Near-Stall Conditions Applying Algebraic Transition Models." Journal of Turbomachinery 128, no. 3 (2005): 474–83. http://dx.doi.org/10.1115/1.2183313.

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Due to the trend in the design of modern aeroengines to reduce weight and to realize high pressure ratios, fan and first-stage compressor blades are highly susceptible to flutter. At operating points with transonic flow velocities and high incidences, stall flutter might occur involving strong shock-boundary layer interactions, flow separation, and oscillating shocks. In this paper, results of unsteady Navier-Stokes flow calculations around an oscillating blade in a linear transonic compressor cascade at different operating points including near-stall conditions are presented. The nonlinear unsteady Reynolds-averaged Navier-Stokes equations are solved time accurately using implicit time integration. Different low-Reynolds-number turbulence models are used for closure. Furthermore, empirical algebraic transition models are applied to enhance the accuracy of prediction. Computations are performed two dimensionally as well as three dimensionally. It is shown that, for the steady calculations, the prediction of the boundary layer development and the blade loading can be substantially improved compared with fully turbulent computations when algebraic transition models are applied. Furthermore, it is shown that the prediction of the aerodynamic damping in the case of oscillating blades at near-stall conditions can be dependent on the applied transition models.

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Tang, D., and E. H. Dowell. "Flutter/LCO suppression for high-aspect ratio wings." Aeronautical Journal 113, no. 1144 (2009): 409–16. http://dx.doi.org/10.1017/s0001924000003079.

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Abstract An experimental high-aspect ratio wing aeroelastic model with a device to provide a controllable slender body tip mass distribution has been constructed and the model response due to flutter and limit cycle oscillations has been measured in a wind tunnel test. A theoretical model has also been developed and calculations made to correlate with the experimental data. Structural equations of motion based on nonlinear beam theory are combined with the ONERA aerodynamic stall model (an empirical extension of Theodorsen aerodynamic theory that accounts for flow separation). A dynamic perturbation analysis about a nonlinear static equilibrium is used to determine the small perturbation flutter boundary which is compared to the experimentally determined flutter velocity and flutter frequency. Time simulation is used to compute the limit cycle oscillations response when the flutter/LCO control system is ON or OFF. Theory and experiment are in good agreement for predicting the flutter/LCO suppression that can be achieved with the control device.

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dos Santos, Carlos R., Flávio D. Marques, and Muhammad R. Hajj. "The effects of structural and aerodynamic nonlinearities on the energy harvesting from airfoil stall-induced oscillations." Journal of Vibration and Control 25, no. 14 (2019): 1991–2007. http://dx.doi.org/10.1177/1077546319844383.

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An airfoil may undergo stall-induced oscillations beyond the critical flutter speed with amplitudes determined by aerodynamic nonlinearities due to the dynamic stall. Stall-induced oscillations yield intense periodical motions that can be used to convert the airflow energy into electrical power. The inclusion of structural nonlinearities contributes to the complexity of the aeroelastic response. In this sense, the present work models and analyzes for the first time the effects of structural and aerodynamic nonlinearities in the potential of extracting energy from pitching and plunging motions of an airfoil during stall-induced oscillations. A computational model is employed, based on the electro-aeroelastic differential equations modeling a typical aeroelastic section with two degrees of freedom with an electrical generator connected to the pitching motion and a piezoelectric element connected to the plunging motion. The Beddoes–Leishman semi-empirical model is used to represent the unsteady aerodynamic loading. Concentrated structural nonlinearities, such as the hardening effect and free-play, are also considered. Bifurcation diagrams and harvested power calculations are used to analyze the performance of each energy harvesting scheme. The results show that nonlinear pitching stiffness reduces the average harvested power from this degree of freedom in a range of wind speeds. However, the presence of a free-play spring reduces the flutter velocity and initiates the harvesting at lower wind speeds. In conclusion, the present electro-aeroelastic model can be used to find optimal parameters of a harvester from airfoil stall-induced oscillations for a specific application.

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Tang, D. M., and E. H. Dowell. "Flutter and stall response of a helicopter blade with structural nonlinearity." Journal of Aircraft 29, no. 5 (1992): 953–60. http://dx.doi.org/10.2514/3.46268.

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Chen, Zhen, Zhiwei Shi, Sinuo Chen, and Zhangyi Yao. "Stall flutter suppression of NACA 0012 airfoil based on steady blowing." Journal of Fluids and Structures 109 (February 2022): 103472. http://dx.doi.org/10.1016/j.jfluidstructs.2021.103472.

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Dunn, Peter, and John Dugundji. "Nonlinear stall flutter and divergence analysis of cantilevered graphite/epoxy wings." AIAA Journal 30, no. 1 (1992): 153–62. http://dx.doi.org/10.2514/3.10895.

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Landa, P. S., and P. V. E. McClintock. "Æolian tones and stall flutter of lengthy objects in fluid flows." Journal of Physics A: Mathematical and Theoretical 43, no. 37 (2010): 375101. http://dx.doi.org/10.1088/1751-8113/43/37/375101.

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Sun, Zhiwei, Sohrab Haghighat, Hugh H. T. Liu, and Junqiang Bai. "Time-domain modeling and control of a wing-section stall flutter." Journal of Sound and Vibration 340 (March 2015): 221–38. http://dx.doi.org/10.1016/j.jsv.2014.10.028.

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Nichols, James, Andrea Attorni, Wouter Haans, and David Witcher. "Investigating Stall Flutter using a DS model-An application for HAWTs." Journal of Physics: Conference Series 555 (December 16, 2014): 012078. http://dx.doi.org/10.1088/1742-6596/555/1/012078.

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Ananth, S. M., A. Kushari, and C. Venkatesan. "Quasi-steady prediction of coupled bending–torsion flutter under rotating stall." Journal of Fluids and Structures 43 (November 2013): 402–27. http://dx.doi.org/10.1016/j.jfluidstructs.2013.09.004.

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Sun, Changle, Zhiyuan Wang, Yingbo Wang, Haipeng Sun, and Tingrui Liu. "Flutter Suppression of Wind Turbine Blade Based on RBF Neural Network Compensation Backstepping Control." Journal of Physics: Conference Series 2173, no. 1 (2022): 012030. http://dx.doi.org/10.1088/1742-6596/2173/1/012030.

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Abstract Aiming at the critical flutter problem of wind turbine blades, which is between classical flutter and stall flutter, a flutter suppression scheme based on radial basis function (RBF) neural network friction compensation backstepping is presented. The structure model is based on the typical 2D section of bending and twist model of spring-mass-damper, and the rotor variable exciter second-order model with friction disturbance is incorporated to control the rotor variable blade. A modified quasi - steady - state aerodynamic model was used for aerodynamics actuation. RBF compensation backstepping control scheme is a block-controlled backstepping controller designed based on the stability theorem of Lyapunov function, which approximates the frictional interference with nonlinear characteristics through RBF network, and cancels the friction existing in the actuator of variable rotor. Four wind speed environments were selected to analyze the response of blades under different wind speeds, and the flutter suppression effects under two wind speeds were selected to verify the ability of RBF network to approach the nonlinear function. The results show that the RBF backstepping control scheme can improve the robustness to suppress the critical flutter problem of wind turbine blades.

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