TY - GEN
T1 - Modeling and quantification of acoustic damping induced by vortex shedding in non-compact thermoacoustic systems
AU - Hofmeister, Thomas
AU - Hummel, Tobias
AU - Schuermans, Bruno
AU - Sattelmayer, Thomas
N1 - Publisher Copyright:
Copyright © 2019 ASME.
PY - 2019
Y1 - 2019
N2 - This paper presents a methodology to compute acoustic damping rates of transversal, high-frequency modes induced by vortex-shedding. The acoustic damping rate presents one key quantity for the assessment of the linear thermoacoustic stability of gas turbine combustors. State of the art network models – as employed to calculate damping rates in low-frequency, longitudinal systems – cannot fulfill this task due to the acoustic non-compactness encountered in the high-frequency regime. Furthermore, it is yet unclear, whether direct eigensolutions of the Linearized Euler Equations (LEE), which capture the mechanism of vortex shedding, yield correct damping rate results constituted by the implicit presence of acoustic as well as hydrodynamic contributions in these solutions. The methodology’s applicability to technically relevant systems is demonstrated by a validation test case using a lab-scale, swirl-stabilized combustion system.
AB - This paper presents a methodology to compute acoustic damping rates of transversal, high-frequency modes induced by vortex-shedding. The acoustic damping rate presents one key quantity for the assessment of the linear thermoacoustic stability of gas turbine combustors. State of the art network models – as employed to calculate damping rates in low-frequency, longitudinal systems – cannot fulfill this task due to the acoustic non-compactness encountered in the high-frequency regime. Furthermore, it is yet unclear, whether direct eigensolutions of the Linearized Euler Equations (LEE), which capture the mechanism of vortex shedding, yield correct damping rate results constituted by the implicit presence of acoustic as well as hydrodynamic contributions in these solutions. The methodology’s applicability to technically relevant systems is demonstrated by a validation test case using a lab-scale, swirl-stabilized combustion system.
UR - http://www.scopus.com/inward/record.url?scp=85075792384&partnerID=8YFLogxK
U2 - 10.1115/1.4044936
DO - 10.1115/1.4044936
M3 - Conference contribution
AN - SCOPUS:85075792384
T3 - Proceedings of the ASME Turbo Expo
BT - Combustion, Fuels, and Emissions
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, GT 2019
Y2 - 17 June 2019 through 21 June 2019
ER -