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TECHNICAL PAPERS

Unsteady Navier-Stokes Simulation of a Transonic Flutter Cascade Near-Stall Conditions Applying Algebraic Transition Models

[+] Author and Article Information
Hans Thermann, Reinhard Niehuis

 Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062 Aachen, Germany

J. Turbomach 128(3), 474-483 (Feb 01, 2005) (10 pages) doi:10.1115/1.2183313 History: Received October 01, 2004; Revised February 01, 2005

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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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 9

2D unsteady computations for 0deg incidence: real and imaginary parts of the first harmonic of the unsteady pressure coefficient on the oscillating blade

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Figure 10

3D unsteady computations for 0deg incidence: real and imaginary parts of the first harmonic of the unsteady pressure coefficient on the oscillating blade

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Figure 11

2D unsteady computations for 4deg incidence: real and imaginary parts of the first harmonic of the unsteady pressure coefficient on the oscillating blade

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Figure 12

3D unsteady computations for 4deg incidence: real and imaginary parts of the first harmonic of the unsteady pressure coefficient on the oscillating blade

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Figure 1

Blade-to-blade section of the computational grid

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Figure 2

Grid-dependency: steady computations for 0deg incindence; upper: CH; lower: CH TRA; (a) and (c) static profile pressure; (b) and (d) shear stress coefficient

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Figure 3

Steady computations for 0deg incindence; upper: 2D; lower: 3D; (a) and (c) static profile pressure; (b) and (d) shear stress coefficient

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Figure 4

Zero degree incidence; comparison of oil flow visualization (left) with streamlines and shear stress coefficients on the suction surface; middle: CH; right: CH TRA

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Figure 5

Zero degree incidence; comparison of oil flow visualization (left) with streamlines and shear stress coefficients on the suction surface; middle: AB; right: AB TRA

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Figure 6

Steady computations for 4deg incindence; upper: 2D; lower 3D; (a) and (c) static profile pressure; (b) and (d) shear stress coefficient

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Figure 7

Four degree incidence; comparison of oil flow visualization (left) with streamlines and shear stress coefficients on the suction surface; middle: CH; right: CH TRA

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Figure 8

Four degree incidence; comparison of oil flow visualization (left) with streamlines and shear stress coefficients on the suction surface; middle: AB; right: AB TRA

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