GAS TURBINE ENGINE WITH SELECTED COMBUSTOR OUTLET TEMPERATURE MEASUREMENTS AND A METHOD OF OPERATING A GAS TURBINE ENGINE

A gas turbine engine includes a combustor assembly (5) having a plurality of can combustor units (8) and a control unit (20). Each combustor unit (8) has a first-stage combustor (12), a second-stage combustor (13) and a mixer (15), arranged between the first-stage combustor (12) and the second-stage combustor (13). A first temperature sensor (17a) and a second temperature sensor (17b) provide respective first temperature measurements (STla, ..., STNa) and second temperature measurements (STlb, ..., STNb) of hot gas flowing through the mixer (15) of the respective combustor unit (8) at a respective first location. The control unit (20) calculates a first average temperature (METa) of a first set (Sa) of the first temperature measurements (STla, ..., STNa) and a second average temperature (METb) of a second set (Sb) of the second temperature measurements (STlb, ..., STNb) determines a mixer exit temperature command (METC) as a function of the first average temperature (METa) and of the second average temperature (METb). Highest and lowest first temperature measurements (STla, ..., STNa) and highest and lowest second temperature measurements (STlb, ..., STNb) are excluded from the first set (Sa) and from the second set (Sb).