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Modeling of Acoustic Damping of Perforations on the Combustion Instability of Annular Aeroengine Combustors

[+] Author Affiliations
Wenjie Tao, Man Zhang

AECC Commerical Aircraft Engine Co., Ltd, Shanghai, China

Lei Li

Shanghai Jao Tong University, Shanghai, China

Paper No. GT2017-64282, pp. V04BT04A007; 9 pages
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 4B: Combustion, Fuels and Emissions
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5085-5
  • Copyright © 2017 by ASME


Combustors running at lean conditions are prone to combustion instability. It occurs when the unsteady heat release interacts constructively with the acoustic waves in the combustor. Acoustic dampers such as perforated liners are commonly used to suppress the instabilities. For analyzing the damping effects of perforations on the combustion instability in an annular combustion chamber, a linear acoustic model has been developed in this work. This model comprises 1D straight injection ducts, a 2D thin annular chamber and an annular cavity that feeds flow to the chamber through perforations. The analytical model is constructed as an acoustic network and the solution of the system’s dispersion equation gives the frequencies and growth rates of the instability modes.

The proposed method is used firstly to calculate the acoustic modes in an annular combustion chamber with four injectors deprived of perforations, and the results correspond well with the Large Eddy Simulation of the same combustor. With perforations, the model yields reduced growth rates for three acoustic modes including the first azimuthal mode, the first axial mode and the first mixed mode. Key parameters critical to the damping effect of perforations are then studied and the lowest growth rates are found for perforations at a common Strouhal number near 0.3.

Copyright © 2017 by ASME



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