A system, comprising: at least one computing device in communication with: a gas turbine system, the gas turbine system including a compressor, a combustor and a turbine component, and a plurality of sensors, at least one of the plurality of sensors positioned within or adjacent the gas turbine system, each sensor of the plurality of sensors measuring one of a plurality of operational characteristics of the gas turbine system, and wherein the at least one computing device is configured to detect thermal stability within the gas turbine system by performing processes including: calculating a lag output for each of the plurality of measured operational characteristics, the calculated lag output based on: a difference between a calculated lag for the measured operational characteristics of the gas turbine system and the measured operational characteristic, and a time constant for each of the plurality of measured operational characteristics; determining when each of the calculated lag outputs are below a predetermined threshold, the predetermined threshold based on each of the plurality of measured operational characteristics and build parameters of the gas turbine system, wherein the build parameters include at least one of: a) at least one of a type, size or model of the compressor; b) at least one of a type, size or model of the combustor; and c) at least one of a type, size or model of the turbine component, wherein the lag for each of the plurality of measured operational characteristics of the gas turbine system is calculated based on: OC lag t = OC lag t − 1 + OC measured t − 1 − OC lag t − 1 1 − e Δ t τ OC wherein: t is a first time; t -1 is a second time occurring prior to the first time t; OC lag ( t) is the calculated lag for the measured operational characteristic at time t; OC lag ( t -1) is the calculated lag for the measured operational characteristic at time t-1; OC meagureg ( t -1) is the measured operational characteristic at time t -1; Δ t is the difference between the first time and the second time; and τ OC is the time constant of the measured operational characteristic, and verifying that the gas turbine system is thermally stable in response to each of the calculated lag outputs for each of the plurality of measured operational characteristics being below the corresponding predetermined threshold. a gas turbine system, the gas turbine system including a compressor, a combustor and a turbine component, and a plurality of sensors, at least one of the plurality of sensors positioned within or adjacent the gas turbine system, each sensor of the plurality of sensors measuring one of a plurality of operational characteristics of the gas turbine system, and wherein the at least one computing device is configured to detect thermal stability within the gas turbine system by performing processes including: calculating a lag output for each of the plurality of measured operational characteristics, the calculated lag output based on: a difference between a calculated lag for the measured operational characteristics of the gas turbine system and the measured operational characteristic, and a time constant for each of the plurality of measured operational characteristics; a difference between a calculated lag for the measured operational characteristics of the gas turbine system and the measured operational characteristic, and a time constant for each of the plurality of measured operational characteristics; determining when each of the calculated lag outputs are below a predetermined threshold, the predetermined threshold based on each of the plurality of measured operational characteristics and build parameters of the gas turbine system, wherein the build parameters include at least one of: a) at least one of a type, size or model of the compressor; b) at least one of a type, size or model of the combustor; and c) at least one of a type, size or model of the turbine component, a) at least one of a type, size or model of the compressor; b) at least one of a type, size or model of the combustor; and c) at least one of a type, size or model of the turbine component, wherein the lag for each of the plurality of measured operational characteristics of the gas turbine system is calculated based on: OC lag t = OC lag t − 1 + OC measured t − 1 − OC lag t − 1 1 − e Δ t τ OC wherein: t is a first time; t -1 is a second time occurring prior to the first time t; OC lag ( t) is the calculated lag for the measured operational characteristic at time t; OC lag ( t -1) is the calculated lag for the measured operational characteristic at time t-1; OC meagureg ( t -1) is the measured operational characteristic at time t -1; Δ t is the difference between the first time and the second time; and τ OC is the time constant of the measured operational characteristic, and t is a first time; t -1 is a second time occurring prior to the first time t; OC lag ( t) is the calculated lag for the measured operational characteristic at time t; OC lag ( t -1) is the calculated lag for the measured operational characteristic at time t-1; OC meagureg ( t -1) is the measured operational characteristic at time t -1; Δ t is the difference between the first time and the second time; and τ OC is the time constant of the measured operational characteristic, and verifying that the gas turbine system is thermally stable in response to each of the calculated lag outputs for each of the plurality of measured operational characteristics being below the corresponding predetermined threshold.