GAS TURBINE ENGINE WITH FLAME FAILURE PROTECTION BASE ON EXHAUST GAS TEMPERATURE AND METHOD OF OPERATING A GAS TURBINE ENGINE

A gas turbine engine includes a combustor assembly (5) with a plurality of burners (13, 14), an exhaust frame (8) provided with a plurality of radial struts (20) and an exhaust diffuser (10) extending along a longitudinal axis (A) downstream of the exhaust frame (8). A plurality of temperature sensors (23, 25) are arranged inside the exhaust diffuser (10) downstream of the exhaust frame (8) and of the struts (20) at respective angular and radial positions with respect to the longitudinal axis (A). A control system (3) is configured to detect flame failure at one or more of the burners (13, 14) based on responses of the temperature sensors (23, 25) and a temperature threshold (TTH) and on a redundant logic.