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research-article

A weakly nonlinear approach based on a distributed flame describing function to study the combustion dynamics of a full-scale lean-premixed swirled burner

[+] Author and Article Information
Davide Laera

DMMM Sez. Macchine ed Energetica Politecnico di Bari Via Re David 200, Bari 70125, Italy
davide.laera@poliba.it

Sergio M. Camporeale

DMMM Sez. Macchine ed Energetica Politecnico di Bari Via Re David 200, Bari 70125, Italy
sergio.camporeale@poliba.it

1Corresponding author.

ASME doi:10.1115/1.4036010 History: Received July 20, 2016; Revised January 23, 2017

Abstract

Modern combustion chambers of gas turbines for power generation and aero-engines suffer of thermo-acoustic combustion instabilities generated by the coupling of heat release rate fluctuations with pressure oscillations. The present article reports a numerical analysis of limit cycles arising in a longitudinal combustor. This corresponds to experiments carried out on the LRIA (Longitudinal Rig for Instability Analysis) test facility equipped with a full-scale lean-premixed burner. Heat release rate fluctuations are modeled considering a distributed flame describing function (DFDF) since the flame under analysis is not compact with respect to the wavelengths of the unstable modes recorded experimentally. For each point of the flame, a saturation model is assumed for the gain and the phase of the DFDF with increasing amplitude of velocity fluctuations. A weakly nonlinear stability analysis is performed by combining the DFDF with a Helmholtz solver to determine the limit cycle condition. The numerical approach is used to study two configurations of the rig characterized by different lengths of the combustion chamber. In each configuration, a good match has been found between numerical predictions and experiments in terms of frequency and wave shape of the unstable mode. Time resolved pressure fluctuations in the system plenum and chamber are reconstructed and compared with measurements. A suitable estimate of the limit cycle oscillation is found.

Copyright (c) 2017 by ASME
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