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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Establishment of a High Quality Database for the Acoustic Modeling of Perforated Liners

[+] Author and Article Information
Claus Lahiri, Lars Enghardt, Friedrich Bake

Institute of Propulsion Technology, German Aerospace Center (DLR), 10623 Berlin, Germany

Sermed Sadig, Miklós Gerendás

Combustor Aerothermal and Cooling, Rolls-Royce Deutschland Ltd. & Co. KG, 15827 Dahlewitz, Germany

J. Eng. Gas Turbines Power 133(9), 091503 (Apr 20, 2011) (9 pages) doi:10.1115/1.4002891 History: Received August 05, 2010; Revised September 24, 2010; Published April 20, 2011; Online April 20, 2011

Perforated liners, especially in combination with a bias flow, are very effective sound absorbers. When appplied to gas turbine combustors, they can suppress thermo-acoustic instabilities and thus allow the application of new combustion concepts concerning higher efficiency and lower emissions. While the successful application of such a damping concept has been shown, it is still not possible to accurately predict the damping performance of a given configuration. This paper provides a comprehensive database of high quality experimental data. Variations of geometric, fluid mechanic, and acoustic parameters have been studied, including realistic engine configurations. The results demonstrate each parameter influence on the damping performance. A low order thermo-acoustic model is used to simulate the test configurations numerically. The model shows a good agreement with the measurements for a wide range of geometries and Strouhal and bias flow Mach numbers.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic setup of the duct acoustic testrig with speakers A and B and microphones 1–12. The anechoic terminations at both ends are not shown.

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Figure 2

Illustration of the sound filed in the duct for measurements A and B by means of the sound pressure amplitudes p̂, the reflection coefficient r, the transmission coefficient t, and the end reflection re

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Figure 3

Error of the dissipation coefficient in the experimental results at three grazing flow Mach numbers

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Figure 4

Definition of the perforation parameters

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Figure 5

Special orifice geometries

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Figure 6

Influence of the bias flow on configuration 3, grazing flow M=0.05. Measurements: symbols, model: lines.

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Figure 7

Influence of the bias flow on configuration 5, grazing flow M=0.05. Measurements: symbols, model: lines.

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Figure 8

Influence of the porosity, bias flow dP=0.2%, and grazing flow M=0

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Figure 9

Influence of the bias flow on configuration 7, grazing flow M=0.05. Measurements: symbols, model: lines.

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Figure 10

Influence of the orifice geometry, bias flow dP=0%, and grazing flow M=0.1

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Figure 11

Influence of the circumferential porosity distribution, bias flow dP=0.01%, and grazing flow M=0.05

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Figure 12

Influence of the bias flow on configuration 11-3, grazing flow M=0. Measurements: symbols, model: lines.

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Figure 13

Influence of the bias flow on configuration 12-3, grazing flow M=0. Measurements: symbols, model: lines.

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Figure 14

Influence of the bias flow on configuration 12-3, grazing flow M=0.1. Measurements: symbols, model: lines.

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Figure 15

Influence of the double skin arrangement at realistic engine condition, bias flow dPT=3%, grazing flow M=0.1. Measurements: symbols, model: lines.

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