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The present work details the analysis of the aerodynamics of an experimentalswirl stabilized burner representative of gas turbine combustors. This analysisis carried out using High Frequency PIV (HFPIV) measurements in a reactivesituation. While this information is usually available at a rather low rate,temporally resolved PIV measurements are necessary to better understand highlyturbulent swirled flows, which are unsteady by nature. Thanks to recenttechnical improvements, a PIV system working at 12 kHz has been developed tostudy this experimental combustor flow field. Statistical quantities of theburner are first obtained and analyzed, and the measurement quality is checked,then a temporal analysis of the velocity field is carried out, indicating thatlarge coherent structures periodically appear in the combustion chamber. Thefrequency of these structures is very close to the quarter wave mode of thechamber, giving a possible explanation for combustion instability coupling.

Characterization of the reactive flow field dynamics in a gas turbine injector using high frequency PIV