Early Detection of Thermoacoustic Combustion Oscillations in Staged Multisector Combustor

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We attempt to detect a precursor of thermoacoustic combustion oscillations in a staged multisector combustor for an aeroengine by the combined methodology of recurrence-based analysis and machine learning. Combustion experiments are conducted at the combustor inlet temperature and pressure of 740 K and 1340 kPa, respectively. The joint dimensional vicinity and the determinism of recurrence plots , effectively capture significant changes in dynamical state during a transition from stable combustion to well-developed combustion oscillations. The feature space of the plane, which is obtained using a support vector machine, is found to be a promising tool for detecting a precursor of combustion oscillations with increasing main fuel flow rate while maintaining the pilot fuel flow rate.