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Numerical Simulation of Unsteady Flow Around Oscillating Blade

[+] Author Affiliations
R. A. Zagitov, N. V. Shuvaev, A. N. Dushko, Yu. N. Shmotin

JSC “NPO “Saturn”, Perm, Russia

Paper No. GT2012-69458, pp. 1529-1536; 8 pages
doi:10.1115/GT2012-69458
From:
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 7: Structures and Dynamics, Parts A and B
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4473-1
  • Copyright © 2012 by ASME

abstract

The paper is pointed to the problem of numerical simulation of unsteady flow around an oscillating blade in jet engine compressor. Single compressor rotor blade row is considered. It is assumed that mode shape and frequency of blade oscillation is not influenced by airflow. The system of governing equations is transformed to a moving coordinate system to describe blade oscillations. Multi-block structured “H-O” grid is used for spatial discretization. Inner boundary of “O”-grid (representing blade airfoil surface) is moved to describe blade airfoil oscillation. To minimize discretization error, special morphing procedure was developed for “O”-grid to accommodate blade airfoil surface motion. Other grid blocks remain steady. Nonlinear harmonic method is applied to integrate Euler equations on time variable. For spatial derivation Dispersion-Relation-Preserving methodology is applied. To maintain solution accuracy nonreflecting boundary conditions are implemented on artificial boundaries (inlet and outlet). Resulting system of nonlinear algebraic equations is resolved numerically. As an alternative, time-marching method is realized in ANSYS CFX by means of user routines. Numerical and experimental cascade results are compared.

Copyright © 2012 by ASME

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