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Experimental and numerical investigation of Helmholtz resonators and perforated liners as attenuation devices in industrial gas turbine combustors

Houston, B.; Qin, Q.; Rubini, P.; Houston, Brian; Wang, J.; Qin, Qin; Rubini, Philip

Authors

B. Houston

Brian Houston

J. Wang

Abstract

This paper reports upon developments in the simulation of the passive control of combustion dynamics in industrial gas turbines using acoustic attenuation devices such as Helmholtz resonators and perforated liners. Combustion instability in gas turbine combustors may, if uncontrolled, lead to large-amplitude pressure fluctuations, with consequent serious mechanical problems in the gas turbine combustor system. Perforated combustor walls and Helmholtz resonators are two commonly used passive instability control devices. However, experimental design of the noise attenuation device is time-consuming and calls for expensive trial and error practice. Despite significant advances over recent decades, the ability of Computational Fluid Dynamics to predict the attenuation of pressure fluctuations by these instability control devices is still not well validated. In this paper, the attenuation of pressure fluctuations by a group of multi-perforated panel absorbers and Helmholtz resonators are investigated both by experiment and computational simulation. It is demonstrated that CFD can predict the noise attenuation from Helmholtz resonators with good accuracy. A porous material model is modified to represent a multi-perforated panel and this perforated wall representation approach is demonstrated to be able to accurately predict the pressure fluctuation attenuation effect of perforated panels. This work demonstrates the applicability of CFD in gas turbine combustion instability control device design.

Publication Date Jul 1, 2015
Journal Fuel
Print ISSN 0016-2361
Electronic ISSN 1873-7153
Publisher Elsevier
Peer Reviewed Peer Reviewed
Volume 151
Pages 31-39
Institution Citation Houston, B., Wang, J., Qin, Q., & Rubini, P. (2015). Experimental and numerical investigation of Helmholtz resonators and perforated liners as attenuation devices in industrial gas turbine combustors. Fuel, 151, 31-39. https://doi.org/10.1016/j.fuel.2014.12.001
DOI https://doi.org/10.1016/j.fuel.2014.12.001
Keywords Combustion instability; Gas turbine combustor; Helmholtz resonator; Perforated liner; CFD
Publisher URL http://www.sciencedirect.com/science/article/pii/S0016236114012101
Additional Information Author's accepted manuscript of article published in: Fuel, 2015, v.151.

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