Abstract: The gas turbine with a plurality of combustors for igniting gas and method includes receiving first temperature measurements for a first plurality of probing points, each associated with one of the plurality of combustors. The method includes receiving second temperature measurements for a second plurality of probing points, each located downstream of the plurality of combustors. The method includes determining an association between the first plurality of probing points and the second plurality of probing points. The determining includes using the first and second temperature measurements and position information for the first and second plurality of probing points to determine swirl characteristics for the gas turbine. The swirl characteristics representing the angular shift between the ignited gas at the plurality of combustors and the ignited gas at the second plurality of probing points.