Experimental investigation of flutter in mid-stage compressor designs

Jutras, R.; Bankhead, H. R.

doi:10.2514/6.1980-786

Cited by 7 publications

(2 citation statements)

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“…Because a stall flutter in cascade occurs with a coupled bending-torsion mode, they also showed that a study of the two-degreesof-freedom case was mandatory. For the choke flutter, the experimental results (Tanida and Saito, 1977; Jutras et al, 1980) and analytically-based predictions (Micklow and Jeffers, 1981) -were presented. Tanida and Saito (1977) evaluated the possibility of the choke flutter in a transonic cascade operating under choking conditions.…”

Section: Introductionmentioning

confidence: 99%

“…Tanida and Saito (1977) evaluated the possibility of the choke flutter in a transonic cascade operating under choking conditions. Jutras et al (1980) conducted a systematic and controlled experiment to investigate negative incidence choke flutter in a non-rotating annular cascade vehicle. Based on a semiactuator disk theory, Micklow and Jeffers (1981) presented a mathematical analysis for the oscillating cascade of airfoils in choked flow.…”

Section: Introductionmentioning

confidence: 99%

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Transonic Stall/Choke Flutter Analysis of Cascades by a Navier-Stokes Solution-Adaptive Approach

Hwang

Fang

1996

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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In this paper, the stall and choke flutter analyses of NACA 0006 unstaggered cascades in transonic viscous flows are presented by using a time domain approach. For the present time domain approach, a solution-adaptive finite volume method with rigid-deformable dynamic mesh treatment is adopted to solve the two-dimensional unsteady Navier-Stokes equations. The structural model equations, where each blade is treated as a typical section having plunging and pitching degrees of freedom, are integrated to obtain the blade displacements by an explicit four-stage Runge-Kutta scheme. In the present calculations, the Baldwin-Lomax turbulence model and two transition formulations are used. The instantaneous meshes, vorticity contours, pressure contours and velocity vectors around the trailing edge clearly indicate the flow phenomena, such as the vortex shedding and A shocks with separation bubbles. From the histories of blade displacements and total energy, the flutter phenomena are studied. Furthermore, the Fast Fourier Transformation (FFT) and modal identification techniques are introduced to investigate the aeroelastic behaviors in present transonic stall and choke flutter problems.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%