Euler Flow Predictions for an Oscillating Cascade Using a High Resolution Wave-Split Scheme

Huff, Dennis L.; Swafford, T. W.; Reddy, T. S. R.

doi:10.1115/91-gt-198

Cited by 41 publications

(13 citation statements)

References 2 publications

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“…Recently, significant attention has been given to the vibration problems. A number of Euler solutions of the oscillating cascade flows were presented (Gerolymos, 1988;He, 1990;Huff et al, 1991;Bendiksen, 1991;Huff, 1992;Hsiao and Bendiksen, 1992). By utilizing the explicit MacCormack scheme, Gerolymos (1988) investigated both started and unstarted supersonic flows in vibrating cascade of fan blades.…”

Section: Introductionmentioning

confidence: 99%

“…He (1990) developed sinusoidal shape and high-order shape corrections for phase-shifted periodic boundary condition, so that the large computer storage required by the conventional direct parameter storage approach can be reduced. Huff et al (1991) introduced a high resolution wave-split scheme to predict the unsteady aerodynamics associated with transonic flows over oscillating cascades. Implementing five-stage Runge-Kutta finite volume scheme on a deformable cascade mesh, Bendiksen (1991) calculated the unsteady transonic cascade flows.…”

Section: Introductionmentioning

confidence: 99%

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Euler Solutions for Transonic Oscillating Cascade Flows Using Dynamic Triangular Meshes

Hwang

Yang

1993

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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The modified total-variation-diminishing scheme and an improved dynamic triangular mesh algorithm are presented to investigate the transonic oscillating cascade flows. In a Cartesian coordinate system, the unsteady Euler equations are solved. To validate the accuracy of the present approach, transonic flow around single NACA 0012 airfoil pitching harmonically about the quarter chord is computed first. The calculated instantaneous pressure coefficient distributions during a cycle of motion compare well with the related numerical and experimental data. To further evaluate the present approach involving nonzero interblade phase angle, the calculations of transonic flow around oscillating cascade of two unstaggered NACA 0006 blades with interblade phase angle equal to 180 deg are performed. From the instantaneous pressure coefficient distributions and time history of lift coefficient, the present approach, where a simple spatial treatment is utilized on the periodic boundaries, gives satisfactory results. By using the above solution procedure, transonic flows around oscillating cascade of four biconvex blades with different oscillation amplitudes, reduced frequencies and interblade phase angles are investigated. From the distributions of magnitude and phase angle of the dynamic pressure difference coefficient, the present numerical results show better agreement with the experimental data than those from the linearized theory in most of the cases. For every quarter of one cycle, the pressure contours repeat and proceed one pitch distance in the upward or downward direction for interblade phase angle equal to −90 deg or 90 deg, respectively. The unsteady pressure wave and shock behaviors are observed. From the lift coefficient distributions, it is further confirmed that the oscillation amplitude, interblade phase angle and reduced frequency all have significant effects on the transonic oscillating cascade flows.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Euler Solutions for Transonic Oscillating Cascade Flows Using Dynamic Triangular Meshes

Hwang

Yang

1993

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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“…However, under transonic flow conditions, even seemingly small oscillations may lead to nonlinear flow behavior. Huff et al 10 solve the nonlinear unsteady Euler equations on oscillating cascades with a timemarching method. The authors investigate amplitude effects on the unsteady pressure over the harmonically pitching blade in a cascade.…”

Section: Introductionmentioning

confidence: 99%

Coupled Fluid-Structure Simulation for Turbomachinery Blade Rows

Sadeghi

Liu

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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A numerical method for the computation of aeroelasticity is presented. Although the emphasis here is on turbomachinery, the method is applicable to a wide variety of problems. A flow solver is coupled to a structural solver by use of a fluid-structure interface method. The integration of the three-dimensional unsteady Navier-Stokes equations is performed in the time domain, simultaneously to the integration of a modal three-dimensional structural model. The flow solution is accelerated by using a multigrid method and a parallel multiblock approach. Fluid-structure coupling is achieved by subiteration. The code is formulated to allow application to general, three-dimensional configurations with multiple independent structures. The capability of the code to handle rotating blade rows is demonstrated by an application to a transonic fan.

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“…Shown in Fig. 13.3 is the computed unsteady pressure distribution on the [17]. Note the very good agreement between the two solutions everywhere except at the shock impulse.…”

Section: Linearized Analysis Of Unsteady Flowsmentioning

confidence: 86%

Untitled

Dowell

2015

A Modern Course in Aeroelasticity

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The field of turbomachinery is undergoing major advances in aeroelasticity, and this chapter provides an overview of these new developments in the key enabling methodology of unsteady aerodynamic modeling. Also see the earlier discussions in Chaps. 8 and 9.In this chapter, we review the state of the field of computational unsteady aerodynamics, particularly frequency domain methods used for the calculation of the unsteady aerodynamic forces arising in turbomachinery aeroelasticity problems. While the emphasis here is on turbomachinery aerodynamics, the methods described in this chapter have analogues for the analysis of isolated airfoils, wings, and even whole aircraft, as well as rotorcraft.The two main aeromechanics problems in turbomachinery are flutter and gust response. In the flutter problem, the unsteady aerodynamic loads acting on a cascade of turbomachinery airfoils arise from the motion of the airfoils themselves. In the gust response problem, the original excitation arises away from the blade row in question. Typical sources of excitation are wakes or potential fields from neighboring blade rows or support structures (struts), inlet distortions, and hot streaks from the combustor.More recently, a third class of aeromechanical problems has been identified [1]. This class of problems is akin to galloping of power lines or buffeting of aircraft wings. Examples include so-called separated flow vibrations and non-synchronous vibrations. In separated flow vibrations, the flow over a row of airfoils is separated, or nearly so. The flow itself is unstable, producing unsteady air loads with broadband frequency distributions that excite the airfoil at all frequencies producing a large response at the natural structural frequencies of the airfoil. Non-synchronous flow vibrations, on the other hand, are similar to separated flow vibrations in that the source of the excitation is thought to be a fluid dynamics instability (rather than an aeroelastic instability), except that non-synchronous vibrations can also occur well away from a stalled condition and the response tends to be at a single frequency. If this fluid dynamic natural frequency happens to be close to a structural natural frequency, then the fluid dynamic instability frequency can "lock on" to the structural frequency of the airfoils resulting in a large-amplitude vibration.

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Euler Flow Predictions for an Oscillating Cascade Using a High Resolution Wave-Split Scheme

Cited by 41 publications

References 2 publications

Euler Solutions for Transonic Oscillating Cascade Flows Using Dynamic Triangular Meshes

Euler Solutions for Transonic Oscillating Cascade Flows Using Dynamic Triangular Meshes

Coupled Fluid-Structure Simulation for Turbomachinery Blade Rows

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