Gas Turbines: Combustion, Fuels, and Emissions

Using Boundary Conditions to Account for Mean Flow Effects in a Zero Mach Number Acoustic Solver

[+] Author and Article Information
Emmanuel Motheau1

 CERFACS - CFD Team 42 av. Gaspard Coriolis, 31057 Toulouse, Franceemmanuel.motheau@cerfacs.fr

Franck Nicoud

CNRS UMR 5149,  University Montpellier II, 34095 Montpellier, Francefranck.nicoud@univ-montp2.fr

Thierry Poinsot

 CNRS - Institut de Mécanique des Fluides, 1 Allée du Professeur Camille Soula, 31000 Toulouse, Francethierry.poinsot@cerfacs.fr


Corresponding author.

J. Eng. Gas Turbines Power 134(11), 111502 (Sep 24, 2012) (8 pages) doi:10.1115/1.4007198 History: Received June 25, 2012; Revised July 13, 2012; Published September 24, 2012; Online September 24, 2012

The present study is devoted to the modeling of mean flow effects while computing thermoacoustic modes under the zero Mach number assumption. It is first recalled that the acoustic impedance modeling of a compressor or a turbine must be prescribed under an energetical form instead of the classical acoustic variables. Then we demonstrate the feasibility to take into account the coupling between acoustic and entropy waves in a zero Mach number framework to capture a family of low frequency entropic modes. The proposed approach relies on a new delayed entropy coupled boundary condition (DECBC) and proves able to capture a family of low frequency entropic mode even though no mean flow term is included in the fluctuating pressure equation.

Copyright © 2012 by American Society of Mechanical Engineers
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Grahic Jump Location
Figure 1

Configuration A investigated in Sec. 3. (a) The complete geometry is computed. (b) Only a part of the tube 1 is computed while the rest of the domain is modeled through downstream impedance.

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Figure 2

Modulus of the reflection coefficient as a function of inlet Mach number M1. Solid line: Acoustical formulation. Dashed line: Energetical formulation.

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Figure 3

Configuration B investigated in Sec. 4



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