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Artykuły w czasopismach na temat „Transonic Cascade Flutter Study”

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Data publikacji: 6 września 2023

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1

Lu, P. J., and S. K. Chen. "Evaluation of Acoustic Flutter Suppression for Cascade in Transonic Flow." Journal of Engineering for Gas Turbines and Power 124, no. 1 (2000): 209–19. http://dx.doi.org/10.1115/1.1365933.

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Flutter suppression via actively excited acoustic waves is a new idea proposed recently. The high flutter frequency (typically 50–500 Hz for a fan blade) and stringent space constraint make conventional mechanical type flutter suppression devices difficult to implement for turbomachines. Acoustic means arises as a new alternative which avoids the difficulties associated with the mechanical methods. The objective of this work is to evaluate numerically the transonic flutter suppression concept based on the application of sound waves to two-dimensional cascade configuration. This is performed us

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2

Kobayashi, H. "Annular Cascade Study of Low Back-Pressure Supersonic Fan Blade Flutter." Journal of Turbomachinery 112, no. 4 (1990): 768–77. http://dx.doi.org/10.1115/1.2927720.

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Low back-pressure supersonic fan blade flutter in the torsional mode was examined using a controlled-oscillating annular cascade test facility. Precise data of unsteady aerodynamic forces generated by shock wave movement, due to blade oscillation, and the previously measured data of chordwise distributions of unsteady aerodynamic forces acting on an oscillating blade, were joined and, then, the nature of cascade flutter was evaluated. These unsteady aerodynamic forces were measured by direct and indirect pressure measuring methods. Our experiments covered a range of reduced frequencies based o

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3

Ott, P., A. Bo¨lcs, and T. H. Fransson. "Experimental and Numerical Study of the Time-Dependent Pressure Response of a Shock Wave Oscillating in a Nozzle." Journal of Turbomachinery 117, no. 1 (1995): 106–14. http://dx.doi.org/10.1115/1.2835625.

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Investigations of flutter in transonic turbine cascades have shown that the movement of unsteady normal shocks has an important effect on the excitation of blades. In order to predict this phenomenon correctly, detailed studies concerning the response of unsteady blade pressures versus different parameters of an oscillating shock wave should be performed, if possible isolated from other flow effects in cascades. In the present investigation the correlation between an oscillating normal shock wave and the response of wall-mounted time-dependent pressure transducers was studied experimentally in

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4

Lepicovsky, J., R. V. Chima, E. R. McFarland, and J. R. Wood. "On Flowfield Periodicity in the NASA Transonic Flutter Cascade." Journal of Turbomachinery 123, no. 3 (2000): 501–9. http://dx.doi.org/10.1115/1.1378300.

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A combined experimental and numerical program was carried out to improve the flow uniformity and periodicity in the NASA transonic flutter cascade. The objectives of the program were to improve the periodicity of the cascade and to resolve discrepancies between measured and computed flow incidence angles and exit pressures. Previous experimental data and some of the discrepancies with computations are discussed. In the present work surface pressure taps, boundary layer probes, shadowgraphs, and pressure-sensitive paints were used to measure the effects of boundary layer bleed and tailboard set

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5

Kobayashi, H. "Unsteady Aerodynamic Damping Measurement of Annular Turbine Cascade With High Deflection in Transonic Flow." Journal of Turbomachinery 112, no. 4 (1990): 732–40. http://dx.doi.org/10.1115/1.2927716.

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Unsteady aerodynamic forces acting on oscillating blades of a transonic annular turbine cascade were investigated in both aerodynamic stable and unstable domains, using a Freon gas annular cascade test facility. In the facility, whole blades composing the cascade were oscillated in the torsional mode by a high-speed mechanical drive system. In the experiment, the reduced frequency K was changed from 0.056 to 0.915 with a range of outlet Mach number M2 from 0.68 to 1.39, and at a constant interblade phase angle. Unsteady aerodynamic moments obtained by two measuring methods agreed well. Through

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6

Lepicovsky, Jan, David Šimurda, Jindřich Hála, Petr Šidlof, and Martin Štěpán. "Blade pressure loading and torque measurement in a transonic linear cascade." Journal of Physics: Conference Series 2511, no. 1 (2023): 012030. http://dx.doi.org/10.1088/1742-6596/2511/1/012030.

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Abstract Experimental results of a transonic compressor blade pressure loadings and blade shaft torque measurements are presented in this paper. Data were acquired for the cascade middle blade being set to a number of incidence angle offsets to simulate phases of a blade flutter oscillatory motion. This paper should be viewed as a progress report on the ongoing larger research effort on blade flutter in transonic flow regimes.

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7

Bakhle, Milind A., T. S. R. Reddy, and Theo G. Keith. "Subsonic/Transonic Cascade Flutter Using a Full-Potential Solver." AIAA Journal 31, no. 7 (1993): 1347–49. http://dx.doi.org/10.2514/3.49072.

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8

Kobayashi, H. "Effects of Shock Waves on Aerodynamic Instability of Annular Cascade Oscillation in a Transonic Flow." Journal of Turbomachinery 111, no. 3 (1989): 222–30. http://dx.doi.org/10.1115/1.3262259.

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The effects of shock waves on the aerodynamic instability of annular cascade oscillation were examined for rows of both turbine and compressor blades, using a controlled-oscillating annular cascade test facility and a method for accurately measuring time-variant pressures on blade surfaces. The nature of the effects and blade surface extent affected by shock waves were clarified over a wide range of Mach number, reduced frequency, and interblade phase angle. Significant unsteady aerodynamic forces were found generated by shock wave movement, which markedly affected the occurrence of compressor

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9

McBean, Ivan, Kerry Hourigan, Mark Thompson, and Feng Liu. "Prediction of Flutter of Turbine Blades in a Transonic Annular Cascade." Journal of Fluids Engineering 127, no. 6 (2005): 1053–58. http://dx.doi.org/10.1115/1.2060731.

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A parallel multiblock Navier-Stokes solver with the k‐ω turbulence model is used to solve the unsteady flow through an annular turbine cascade, the transonic Standard Test Case 4, Test 628. Computations are performed on a two- and three-dimensional model of the blade row with either the Euler or the Navier-Stokes flow models. Results are compared to the experimental measurements. Comparisons of the unsteady surface pressure and the aerodynamic damping are made between the three-dimensional, two-dimensional, inviscid, viscous simulations, and experimental data. Differences are found between the

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10

Cinnella, P., P. De Palma, G. Pascazio, and M. Napolitano. "A Numerical Method for Turbomachinery Aeroelasticity." Journal of Turbomachinery 126, no. 2 (2004): 310–16. http://dx.doi.org/10.1115/1.1738122.

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This work provides an accurate and efficient numerical method for turbomachinery flutter. The unsteady Euler or Reynolds-averaged Navier-Stokes equations are solved in integral form, the blade passages being discretised using a background fixed C-grid and a body-fitted C-grid moving with the blade. In the overlapping region data are exchanged between the two grids at every time step, using bilinear interpolation. The method employs Roe’s second-order-accurate flux difference splitting scheme for the inviscid fluxes, a standard second-order discretisation of the viscous terms, and a three-level

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11

KAZAWA, Junichi, and Toshinori WATANABE. "Active Control of Cascade Flutter with Piezo Electric Device in Transonic Flow." Proceedings of the JSME annual meeting 2004.3 (2004): 347–48. http://dx.doi.org/10.1299/jsmemecjo.2004.3.0_347.

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12

Šidlof, Petr, Pavel Šidlof, Martin Štěpán, David Šimurda, and Jan Lepicovsky. "Laser triangulation measurement of blade oscillation in a transonic compressor cascade." Journal of Physics: Conference Series 2511, no. 1 (2023): 012010. http://dx.doi.org/10.1088/1742-6596/2511/1/012010.

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Abstract The paper describes a method for optical measurement of oscillation of blades in a linear cascade designed for flutter research. The method uses laser triangulation, which measures the distance between the sensor and the oscillation object. The distance can be recalculated to angular displacement of the blade. However, the relation is nonlinear due to the curvature of the blade. The nonlinear dependence between the distance and angular displacement is derived and quantified analytically. The paper further analyzes the influence of light refraction in the optical window, surface qualit

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13

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

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14

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 un

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15

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 computa

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16

Šidlof, Petr, David Šimurda, Jan Lepicovsky, and Martin Štěpán. "Aerodynamic and dynamic loading in a blade cascade designed for flutter research." EPJ Web of Conferences 264 (2022): 01041. http://dx.doi.org/10.1051/epjconf/202226401041.

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Flow-induced vibration of turbine and compressor blades, so called blade flutter, represents a serious problem for designers and operators of large turbomachines. The research of mechanisms leading to this dangerous aeroelastic instability, which can occur especially in modern long and slender blades, is hindered by lack of experimental data. A new experimental setup for controlled flutter testing has been designed in cooperation of the Institute of Thermomechanics of the Czech Academy of Sciences and Faculty of Mechatronics of the Technical University of Liberec. The test section consists of

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17

Hála, Jindřich, Jan Lepičovský, Petr Šidlof, and David Šimurda. "CFD Investigation of the test facility for forced blade flutter research." EPJ Web of Conferences 264 (2022): 01017. http://dx.doi.org/10.1051/epjconf/202226401017.

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With the increasing share of renewable power resources turbomachines need to be operated under a wider range of operating conditions including highly off-design regimes. Under such regimes an undesirable phenomenon of blade flutter might occur and possibly destroy the machine. To prevent this, intensive research is conducted by research teams worldwide. Blade flutter research program at the Institute of Thermomechanics of the Czech academy of sciences (IT CAS) mainly aims to advance experimental techniques for investigation of sonic and transonic blade flutter. For this purpose, the new sophis

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18

Fransson, T. H., M. Jo¨cker, A. Bo¨lcs, and P. Ott. "Viscous and Inviscid Linear/Nonlinear Calculations Versus Quasi-Three-Dimensional Experimental Cascade Data for a New Aeroelastic Turbine Standard Configuration." Journal of Turbomachinery 121, no. 4 (1999): 717–25. http://dx.doi.org/10.1115/1.2836725.

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This paper presents a new International Standard Configuration to be added to an already existing set of 10 configurations for unsteady flow through vibrating axial-flow turbomachine cascades. This 11th configuration represents a turbine blade geometry with transonic design flow conditions with a normal shock positioned at 75 percent real chord on the suction side. Out of a set of test cases covering all relevant flow regimes two cases were selected for publication: A subsonic, attached flow case, and an off-design transonic case showing a separation bubble at 30 percent real chord on the suct

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19

Pátý, Marek, and Jan Halama. "ON THE USE OF A FLUX-SPLITTING SCHEME IN THE NUMERICAL FLUTTER ANALYSIS OF A LOW-PRESSURE TURBINE STAGE." Acta Polytechnica 61, SI (2021): 135–47. http://dx.doi.org/10.14311/ap.2021.61.0135.

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The endeavour to increase the power output of steam turbines results in the design of low-pressure stages with large diameters. Such designs, featuring long and thin blades, are increasingly susceptible to unfavourable aeroelastic effects. The interaction of structure and flow may induce blade vibrations, known as flutter, which act detrimentally on the operational life of the machine. The present work employs a time-marching numerical simulation to investigate the flutter behaviour of a low-pressure transonic turbine cascade. Its blades are subject to a harmonic motion based on the results of

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20

He, L., and J. D. Denton. "Inviscid-Viscous Coupled Solution for Unsteady Flows Through Vibrating Blades: Part 2—Computational Results." Journal of Turbomachinery 115, no. 1 (1993): 101–9. http://dx.doi.org/10.1115/1.2929193.

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A quasi-three-dimensional inviscid-viscous coupled approached has been developed for unsteady flows around oscillating blades, as described in Part 1. To validate this method, calculations for several steady and unsteady flow cases with strong inviscid-viscous interactions are performed, and the results are compared with the corresponding experiments. Calculated results for unsteady flows around a biconvex cascade and a fan tip section highlight the necessity of including viscous effects in predictions of turbomachinery blade flutter at transonic flow conditions.

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21

Karnick, Pradeepa T., and Kartik Venkatraman. "Shock–boundary layer interaction and energetics in transonic flutter." Journal of Fluid Mechanics 832 (October 26, 2017): 212–40. http://dx.doi.org/10.1017/jfm.2017.629.

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We study the influence of shock and boundary layer interactions in transonic flutter of an aeroelastic system using a Reynolds-averaged Navier–Stokes (RANS) solver together with the Spalart–Allmaras turbulence model. We show that the transonic flutter boundary computed using a viscous flow solver can be divided into three distinct regimes: a low transonic Mach number range wherein viscosity mimics increasing airfoil thickness thereby mildly influencing the flutter boundary; an intermediate region of drastic change in the flutter boundary due to shock-induced separation; and a high transonic Ma

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22

Schuff, Matthias, and Virginie Anne Chenaux. "Coupled Mode Flutter of a Linear Compressor Cascade in Subsonic and Transonic Flow Conditions." Journal of Physics: Conference Series 1909, no. 1 (2021): 012033. http://dx.doi.org/10.1088/1742-6596/1909/1/012033.

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23

Ayer, T. C., and J. M. Verdon. "Validation of a Nonlinear Unsteady Aerodynamic Simulator for Vibrating Blade Rows." Journal of Turbomachinery 120, no. 1 (1998): 112–21. http://dx.doi.org/10.1115/1.2841372.

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A time-accurate Euler/Navier–Stokes analysis is applied to predict unsteady subsonic and transonic flows through a vibrating cascade. The intent is to validate this nonlinear analysis along with an existing linearized inviscid analysis via result comparisons for unsteady flows that are representative of those associated with blade flutter. The time-accurate analysis has also been applied to determine the relative importance of nonlinear and viscous effects on blade response. The subsonic results reveal a close agreement between inviscid and viscous unsteady blade loadings. Also, the unsteady s

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24

Hennings, H., and W. Send. "Experimental Investigation and Theoretical Predication of Flutter Behavior of a Plane Cascade in Low Speed Flow." Journal of Engineering for Gas Turbines and Power 120, no. 4 (1998): 766–74. http://dx.doi.org/10.1115/1.2818465.

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The Institute of Aeroelasticity operates a test facility which enables aeroelastic investigations of plane cascades in low-speed flow. The test stand serves as a pilot facility to develop tools for analogous investigations in transonic flow. Eleven blades are elastically suspended in a windtunnel with a 1 × 0.2 m2 cross section. This paper describes the experimental method of determining the flutter boundary by extrapolation of the results measured in subcritical flow. A two-dimensional theoretical model of the 11 blades, including the windtunnel walls, permits the computation of unsteady pres

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25

Ji, Lucheng, Jia Yu, Weiwei Li, and Weilin Yi. "Study on aerodynamic optimal super/transonic turbine cascade and its geometry characteristics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 3 (2016): 435–43. http://dx.doi.org/10.1177/0954410016638875.

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The shock waves are important phenomena in transonic turbines, which cause lots of negative effects on the aerodynamic performance. Much of attention had been paid on reducing the strength of the shock waves via modifying turbine cascade geometry, and it is highly preferred to build experiences on the relationship between the cascade aerodynamic performance and the geometric parameters. The paper presents a numerical study on the aerodynamic optimal transonic turbine cascade and its geometry characteristics. Three typical Russia transonic turbine cascades with different design conditions are s

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26

Lepicovsky, Jan, David Šimurda, and Petr Šidlof. "Verification tests of a new blade flutter research facility." MATEC Web of Conferences 345 (2021): 00020. http://dx.doi.org/10.1051/matecconf/202134500020.

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Long term strategic changes in power generation approaches will require more flexibility for large power generating turbines as an unavoidable consequence of the increasing share of power generated by alternative energy sources. Demanded flexibility for the power turbine output will augment undesired flow phenomena in the low-pressure turbine module, which will consequently enhance blade flutter problems of long slender blades in turbine last stages. In order to advance the understanding of blade flutter onset conditions, the Institute of Thermomechanics of the Czech Academy of Sciences instig

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27

Chiarelli, Mario Rosario, and Salvatore Bonomo. "Numerical Investigation into Flutter and Flutter-Buffet Phenomena for a Swept Wing and a Curved Planform Wing." International Journal of Aerospace Engineering 2019 (February 27, 2019): 1–19. http://dx.doi.org/10.1155/2019/8210235.

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The results of numerical studies carried out on high-aspect-ratio wings with different planforms are discussed: the transonic regime is analysed for a swept wing and a curved planform wing. The wings have similar aspect ratios and similar aerodynamic profiles. The analyses were carried out by CFD and FE techniques, and the reliability of the numerical aerodynamic results was proven by a sensitivity study. Analysing the performances of the two wings demonstrated that in transonic flight conditions, a noticeable drag reduction can be obtained by adopting a curved planform wing. In addition, for

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28

SATO, Iwataro, and Shojiro KAJI. "Study of transonic cascade airfoils by a panel method." Transactions of the Japan Society of Mechanical Engineers Series B 52, no. 484 (1986): 3880–87. http://dx.doi.org/10.1299/kikaib.52.3880.

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Kiss, Tibor, Joseph A. Schetz, and Hal L. Moses. "Experimental and numerical study of transonic turbine cascade flow." AIAA Journal 34, no. 1 (1996): 104–9. http://dx.doi.org/10.2514/3.13028.

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Kholodar, Denis B., Jeffrey P. Thomas, Earl H. Dowell, and Kenneth C. Hall. "Parametric Study of Flutter for an Airfoil in Inviscid Transonic Flow." Journal of Aircraft 40, no. 2 (2003): 303–13. http://dx.doi.org/10.2514/2.3094.

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Shelton, M. L., B. A. Gregory, R. L. Doughty, T. Kiss, and H. L. Moses. "A Statistical Approach to the Experimental Evaluation of Transonic Turbine Airfoils in a Linear Cascade." Journal of Turbomachinery 115, no. 3 (1993): 366–75. http://dx.doi.org/10.1115/1.2929263.

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In aircraft engine design (and in other applications), small improvements in turbine efficiency may be significant. Since analytical tools for predicting transonic turbine losses are still being developed, experimental efforts are required to evaluate various designs, calibrate design methods, and validate CFD analysis tools. However, these experimental efforts must be very accurate to measure the performance differences to the levels required by the highly competitive aircraft engine market. Due to the sensitivity of transonic and supersonic flow fields, it is often difficult to obtain the de

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Chuang, H. A., and J. M. Verdon. "A Nonlinear Numerical Simulator for Three-Dimensional Flows Through Vibrating Blade Rows." Journal of Turbomachinery 121, no. 2 (1999): 348–57. http://dx.doi.org/10.1115/1.2841321.

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The three-dimensional, multistage, unsteady, turbomachinery analysis, TURBO, has been extended to predict the aeroelastic response of a blade row operating within a cylindrical annular duct. In particular, a blade vibration capability has been incorporated, so that the TURBO analysis can be applied over a solution domain that deforms with a vibratory blade motion. Also, unsteady far-field conditions have been implemented to render the computational inlet and exit boundaries transparent to outgoing unsteady disturbances and to allow for the prescription of incoming aerodynamic excitations. The

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33

Silva, Roberto G. A., Olympio A. F. Mello, and Joao L. F. Azevedo. "Navier-Stokes-Based Study into Linearity in Transonic Flow for Flutter Analysis." Journal of Aircraft 40, no. 5 (2003): 997–1000. http://dx.doi.org/10.2514/2.6886.

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Geissler, W. "Numerical study of buffet and transonic flutter on the NLR 7301 airfoil." Aerospace Science and Technology 7, no. 7 (2003): 540–50. http://dx.doi.org/10.1016/s1270-9638(03)00065-8.

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Lepicovsky, J., E. R. McFarland, R. V. Chima, V. R. Capece, and J. Hayden. "Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade." International Journal of Rotating Machinery 10, no. 2 (2004): 135–44. http://dx.doi.org/10.1155/s1023621x04000144.

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A study was conducted in the NASA Glenn Research Center (NASA-GRC) linear cascade on the intermittent flow on the suction surface of an airfoil section from the tip region of a modern low aspect ratio fan blade. Experimental results revealed that, at a large incidence angle, a range of transonic inlet Mach numbers exist where the leading-edge shock-wave pattern was unstable. Flush-mounted, high-frequency response pressure transducers indicated large local jumps in the pressure in the leading edge area, which generates large intermittent loading on the blade leading edge. These measurements sug

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36

Piovesan, Tommaso, Andrea Magrini, and Ernesto Benini. "Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics." Aerospace 6, no. 5 (2019): 57. http://dx.doi.org/10.3390/aerospace6050057.

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Modern aeronautic fans are characterised by a transonic flow regime near the blade tip. Transonic cascades enable higher pressure ratios by a complex system of shockwaves arising across the blade passage, which has to be correctly reproduced in order to predict the performance and the operative range. In this paper, we present an accurate two-dimensional numerical modelling of the ARL-SL19 transonic compressor cascade. A large series of data from experimental tests in supersonic wind tunnel facilities has been used to validate a computational fluid dynamic model, in which the choice of turbule

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37

KOBAYASHI, Hiroshi. "Unsteady aerodynamic characteristics of annular cascade oscillating in transonic flow. 3rd Report. Low back-pressure supersonic compressor blade flutter." Transactions of the Japan Society of Mechanical Engineers Series B 52, no. 480 (1986): 2920–29. http://dx.doi.org/10.1299/kikaib.52.2920.

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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

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Frey, Christian, Graham Ashcroft, Hans-Peter Kersken, and Daniel Schlüß. "Flutter Analysis of a Transonic Steam Turbine Blade with Frequency and Time-Domain Solvers." International Journal of Turbomachinery, Propulsion and Power 4, no. 2 (2019): 15. http://dx.doi.org/10.3390/ijtpp4020015.

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The aim of this study was to assess the capabilities of different simulation approaches to predict the flutter stability of a steam turbine rotor. The focus here was on linear and nonlinear frequency domain solvers in combination with the energy method, which is widely used for the prediction of flutter onset. Whereas a GMRES solver was used for the linear problem, the nonlinear methods employed a time-marching procedure. The solvers were applied to the flutter analysis of the first rotor bending mode of the open Durham Steam Turbine test case. This test case is representative of the last stag

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SAWAKI, Yuta, Yuichi KUYA, and Keisuke SAWADA. "Study of Fast Prediction Method for Transonic Flutter Boundary Using Radial Basis Function." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 18 (2019): 133–41. http://dx.doi.org/10.2322/astj.jsass-d-17-00087.

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Singh, Indrajeet, R. K. Mishra, and P. S. Aswatha Narayana. "Numerical Study of a Transonic Aircraft Wing for the Prediction of Flutter Failure." Journal of Failure Analysis and Prevention 17, no. 1 (2016): 107–19. http://dx.doi.org/10.1007/s11668-016-0209-8.

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Sláma, Václav, Bartoloměj Rudas, Petr Eret, et al. "EXPERIMENTAL AND NUMERICAL STUDY OF CONTROLLED FLUTTER TESTING IN A LINEAR TURBINE BLADE CASCADE." Acta Polytechnica CTU Proceedings 20 (December 31, 2018): 98–107. http://dx.doi.org/10.14311/app.2018.20.0098.

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In this paper, experimental testing of flutter and numerical simulations using a commercial code ANSYS CFX and an in-house code TRAF are performed on an oscillating linear cascade of turbine blades installed in a subsonic test rig. Bending and torsional motions of the blades are investigated in a travelling wave mode approach. In each numerical approach, a rig geometry model with a different level of complexity is used. Good agreement between the numerical simulations and experiments is achieved using both approaches and benefits and drawbacks of each technique are commented in this paper. It

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Szumowski, A., J. Amecke, and J. Agocs. "Photographic study of obstacle-induced disturbations of transonic turbine cascade flow." Journal of Thermal Science 7, no. 3 (1998): 139–48. http://dx.doi.org/10.1007/s11630-998-0010-4.

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Wang, Liyue, Cong Wang, Sheng Qin, et al. "Experimental Study on Performance of Transonic Compressor Cascade with Microgroove Polyurethane Coatings." Fluids 7, no. 6 (2022): 190. http://dx.doi.org/10.3390/fluids7060190.

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Due to the harsh operating environment of aero-engines, a surface structure that provides excellent aerodynamic performance is urgently required to save energy and reduce emissions. In this study, microgroove polyurethane coatings fabricated by chemical synthesis are investigated in terms of their effect on aerodynamic performance, which is a new attempt to investigate the impact on aerodynamic performance of compressor cascade at transonic speeds. This method reduces manufacturing and maintenance cost significantly compared with traditional laser machining. Wake measurements are conducted in

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Glodic, Nenad, Carlos Tavera Guerrero, and Mauricio Gutierrez Salas. "Blade oscillation mechanism for aerodynamic damping measurements at high reduced frequencies." E3S Web of Conferences 345 (2022): 03002. http://dx.doi.org/10.1051/e3sconf/202234503002.

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Accurate prediction of aerodynamic damping is essential for flutter and forced response analysis of turbomachinery components. Reaching a high level of confidence in numerical simulations requires that the models have been validated against the experiments. Even though a number of test cases have been established over the past decades, there is still a lack of suitable detailed test data that can be used for validation purposes in particular when it comes to aero damping at high reduced frequencies which is more relevant in the context of forced response analysis. A new transonic cascade test

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Abhari, R. S., and A. H. Epstein. "An Experimental Study of Film Cooling in a Rotating Transonic Turbine." Journal of Turbomachinery 116, no. 1 (1994): 63–70. http://dx.doi.org/10.1115/1.2928279.

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Time-resolved measurements of heat transfer on a fully cooled transonic turbine stage have been taken in a short duration turbine test facility, which simulates full engine nondimensional conditions. The time average of this data is compared to uncooled rotor data and cooled linear cascade measurements made on the same profile. The film cooling reduces the time-averaged heat transfer compared to the uncooled rotor on the blade suction surface by as much as 60 percent, but has relatively little effect on the pressure surface. The suction surface rotor heat transfer is lower than that measured i

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Abhari, R. S., and M. Giles. "A Navier–Stokes Analysis of Airfoils in Oscillating Transonic Cascades for the Prediction of Aerodynamic Damping." Journal of Turbomachinery 119, no. 1 (1997): 77–84. http://dx.doi.org/10.1115/1.2841013.

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An unsteady, compressible, two-dimensional, thin shear layer Navier–Stokes solver is modified to predict the motion-dependent unsteady flow around oscillating airfoils in a cascade. A quasi-three-dimensional formulations is used to account for the stream-wise variation of streamtube height. The code uses Ni’s Lax–Wendroff algorithm in the outer region, an implicit ADI method in the inner region, conservative coupling at the interface, and the Baldwin–Lomax turbulence model. The computational mesh consists of an O-grid around each blade plus an unstructured outer grid of quadrilateral or triang

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Schäfer, Dominik. "Influence of Fluid Viscosity and Compressibility on Nonlinearities in Generalized Aerodynamic Forces for T-Tail Flutter." Aerospace 9, no. 5 (2022): 256. http://dx.doi.org/10.3390/aerospace9050256.

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The numerical assessment of T-tail flutter requires a nonlinear description of the structural deformations when the unsteady aerodynamic forces comprise terms from lifting surface roll motion. For linear flutter, a linear deformation description of the vertical tail plane (VTP) out-of-plane bending results in a spurious stiffening proportional to the steady lift forces, which is corrected by incorporating second-order deformation terms in the equations of motion. While the effect of these nonlinear deformation components on the stiffness of the VTP out-of-plane bending mode shape is known from

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Irina Carmen, ANDREI. "Numerical Study of Transonic Axial Flow Rotating Cascade Aerodynamics – Part 1: 2D Case." INCAS BULLETIN 6, no. 2 (2014): 3–13. http://dx.doi.org/10.13111/2066-8201.2014.6.2.1.

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Noorsalehi, Mohammad Hossein, Mahdi Nili-Ahmadabadi, Seyed Hossein Nasrazadani, and Kyung Chun Kim. "Aerodynamic Inverse Design of Transonic Compressor Cascades with Stabilizing Elastic Surface Algorithm." Applied Sciences 11, no. 11 (2021): 4845. http://dx.doi.org/10.3390/app11114845.

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The upgraded elastic surface algorithm (UESA) is a physical inverse design method that was recently developed for a compressor cascade with double-circular-arc blades. In this method, the blade walls are modeled as elastic Timoshenko beams that smoothly deform because of the difference between the target and current pressure distributions. Nevertheless, the UESA is completely unstable for a compressor cascade with an intense normal shock, which causes a divergence due to the high pressure difference near the shock and the displacement of shock during the geometry corrections. In this study, th

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