Heat release rate and pressure phase differences inside an aeronautical gas turbine combustor

Abstract eng:
Spatial maps of instantaneous phase difference between heat release rate and pressure oscillations is presented during nonstationary behavior in a high-pressure, liquid-fueled gas turbine combustor. Using the Hilbert transform technique, simultaneous high-speed OH∗ chemiluminescence images along with pressure oscillations data were analyzed to obtain the corresponding phase difference. The results show that, for time periods with increasing amplitude pressure fluctuations, in-phase heat release rate and pressure oscillations developed throughout the upstream portion of the combustor, which extended along the burner centerline and towards the downstream portion of the combustor. This behavior is reversed during time periods with decreasing amplitude pressure oscillations.

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