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Computational Analysis of Tonal Noise Generated High-Bypass Ratio Fan Stage

[+] Author Affiliations
Aleksey M. Sipatov, Michail V. Usanin, Valery G. Avgustinovich, Natalia O. Chuhlantseva

OJSC “Aviadvigatel”, Perm, Russia

Paper No. GT2005-68857, pp. 1265-1274; 10 pages
doi:10.1115/GT2005-68857
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

The paper shows the procedure of estimating different fan stage geometries from the point of the fan stage aerodynamic and acoustic efficiency by using CFX v.5.6 gas dynamics software. Two different fan stages were examined. The acoustic analysis was made based on unsteady pressure distribution along exit guide vanes. The unsteady pressure distribution was determined from 3-D calculations of rotor-stator interactions. An improved approach is suggested to estimate acoustic sources with the leading edge geometry considered. Three various grid models were analyzed to estimate the grid discretization influence on computational results. The hybrid approach was used to evaluate the acoustic contribution of fan stage rotor–stator interaction to a turbo-jet engine total noise level on first harmonic in a far field. This approach consists of three steps. The first step includes the solving of Navier-Stokes equations in fan stage, the second step includes the solving of linearized Euler’s equations (LEE) in a near field and, then, the third covers the calculation of Ffowcs Williams–Hawkings (FWH) integral in a far field. The first step marked the effect of strong attenuation of acoustics modes in the fan passage. The results of calculations in the far field were compared with experiment data.

Copyright © 2005 by ASME
Topics: Noise (Sound)

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