Gas turbine engine comprising: a combustor assembly, having a plurality of combustor units; and a control system, configured to control air supply and fuel supply to the combustor assembly; the control system comprising: pulsation sensors coupled to respective combustor units and configured to provide pulsation signals (P N (t)) from the respective combustor units, each combustor unit being provided with a respective one of the pulsation sensors; and a processing unit coupled to the pulsation sensors to receive the pulsation signals (P N (t)), the gas turbine engine being characterized in that the processing unit is configured to: determine at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)), the azimuthal pulsation component being defined by P M t = 1 NC ∑ N = 1 NC P N t e iMθ N where NC is a number of can combustors in the combustor assembly, θ N = 2 π N − 1 NC is an azimuthal angle of a N-th of the can combustors of the combustor assembly, i is the imaginary unit, and M is an order of the at least one azimuthal component ( P M ( t)) in the range [-ceil(NC/2) + 1; floor(NC/2)]; determine working time series (TSW N) of spectral parameters (A 1; A 1, A 2; F 1) from the at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)); and to selectively activate protecting measures based on the working time series (TSW N) and activation criteria. a combustor assembly, having a plurality of combustor units; and a control system, configured to control air supply and fuel supply to the combustor assembly; the control system comprising: pulsation sensors coupled to respective combustor units and configured to provide pulsation signals (P N (t)) from the respective combustor units, each combustor unit being provided with a respective one of the pulsation sensors; and a processing unit coupled to the pulsation sensors to receive the pulsation signals (P N (t)), the gas turbine engine being characterized in that the processing unit is configured to: determine at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)), the azimuthal pulsation component being defined by P M t = 1 NC ∑ N = 1 NC P N t e iMθ N where NC is a number of can combustors in the combustor assembly, θ N = 2 π N − 1 NC is an azimuthal angle of a N-th of the can combustors of the combustor assembly, i is the imaginary unit, and M is an order of the at least one azimuthal component ( P M ( t)) in the range [-ceil(NC/2) + 1; floor(NC/2)]; determine working time series (TSW N) of spectral parameters (A 1; A 1, A 2; F 1) from the at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)); and to selectively activate protecting measures based on the working time series (TSW N) and activation criteria. pulsation sensors coupled to respective combustor units and configured to provide pulsation signals (P N (t)) from the respective combustor units, each combustor unit being provided with a respective one of the pulsation sensors; and a processing unit coupled to the pulsation sensors to receive the pulsation signals (P N (t)), the gas turbine engine being characterized in that the processing unit is configured to: determine at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)), the azimuthal pulsation component being defined by P M t = 1 NC ∑ N = 1 NC P N t e iMθ N where NC is a number of can combustors in the combustor assembly, θ N = 2 π N − 1 NC is an azimuthal angle of a N-th of the can combustors of the combustor assembly, i is the imaginary unit, and M is an order of the at least one azimuthal component ( P M ( t)) in the range [-ceil(NC/2) + 1; floor(NC/2)]; determine working time series (TSW N) of spectral parameters (A 1; A 1, A 2; F 1) from the at least one azimuthal component ( P M ( t)) of the pulsation signals (P N (t)); and to selectively activate protecting measures based on the working time series (TSW N) and activation criteria.