Abstract: A controller for a gas turbine, wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply including the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate mss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate mtotal to the combustor. The controller is arranged to, responsive to a load change ?L to the load L, control the compressor to provide air to the combustor at a new air mass flow rate mTR, wherein the new air mass flow rate mTR is within a range between a first threshold mLBO and a second threshold mSUR.

Abstract: A controller for a gas turbine wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply includes the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate mss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate mtotal to the combustor. The controller is arranged to, responsive to the load change ?L to the load L, control the fuel supply to supply a proportion Z of the fuel mass flow rate mtotal as a fuel mass flow rate mfuel pilot via the first fuel supply based, at least in part, on a combustor mass flow rate mt.

Abstract: A system for controlling a gas turbine, includes a control system for providing control signals to a gas turbine; a tuning system for providing tuning signals, a modelling system for generating virtual measurement signals, the virtual measurement signals being based on the control signals and the tuning signals; a sensor diagnostics system for diagnosing at least one sensor measurement signal and outputting control system reconfiguration signals to the control system and tuner system reconfiguration signals to the tuning system, the tuning signals being based at least on the tuner system reconfiguration signals, the control signals being based on the at least one sensor measurement signal, the virtual measurement signals and the control system reconfiguration signals.

Abstract: A controller for a gas turbine, wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply including the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate mss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate mtotal to the combustor. The controller is arranged to, responsive to a load change ?L to the load L, control the compressor to provide air to the combustor at a new air mass flow rate mTR, wherein the new air mass flow rate mTR is within a range between a first threshold mLBO and a second threshold mSUR.

Abstract: A controller for a gas turbine wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply includes the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate mss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate mtotal to the combustor. The controller is arranged to, responsive to the load change ?L to the load L, control the fuel supply to supply a proportion Z of the fuel mass flow rate mtotal as a fuel mass flow rate mfuel pilot via the first fuel supply based, at least in part, on a combustor mass flow rate mt.

Abstract: A system for controlling a gas turbine, includes a control system for providing control signals to a gas turbine; a tuning system for providing tuning signals, a modelling system for generating virtual measurement signals, the virtual measurement signals being based on the control signals and the tuning signals; a sensor diagnostics system for diagnosing at least one sensor measurement signal and outputting control system reconfiguration signals to the control system and tuner system reconfiguration signals to the tuning system, the tuning signals being based at least on the tuner system reconfiguration signals, the control signals being based on the at least one sensor measurement signal, the virtual measurement signals and the control system reconfiguration signals.

Abstract: A method for determining a deviation value of a health parameter, in particular a capacity or efficiency parameter, of at least one component of a gas turbine. A pressure value and temperature value at a measuring point of the component is measured. A corrected pressure value is determined based on a predetermined pressure correction factor of the component. A corrected temperature value is determined based on a predetermined temperature correction factor of the component. An estimated actual value of the health parameter of the component is determined based on the corrected pressure value, the corrected temperature value and measured shaft speed. A nominal value of the health parameter of the component which is predicted based on at least one predetermined input parameter is determined. Finally, a deviation value of a health parameter is determined by comparing the estimated actual value and the nominal value.

Abstract: A method for determining a deviation value of a health parameter, in particular a capacity or efficiency parameter, of at least one component of a gas turbine. A pressure value and temperature value at a measuring point of the component is measured. A corrected pressure value is determined based on a predetermined pressure correction factor of the component. A corrected temperature value is determined based on a predetermined temperature correction factor of the component. An estimated actual value of the health parameter of the component is determined based on the corrected pressure value, the corrected temperature value and measured shaft speed. A nominal value of the health parameter of the component which is predicted based on at least one predetermined input parameter is determined. Finally, a deviation value of a health parameter is determined by comparing the estimated actual value and the nominal value.

Abstract: A method of determining an exit temperature of a gas exiting a combustor of a gas turbine includes determining a mass flow and a temperature of fuel being delivered to the combustor; determining a mass flow and a temperature of air being delivered to the combustor, determining a temperature dependence of the specific heat capacity of a burnt mixture of the fuel and the air being delivered to the combustor; and determining an exit temperature of the burnt mixture exiting the combustor. The exit temperature is determined based on the determined mass flow and temperature of the fuel, the determined mass flow and temperature of the air, and the determined temperature dependence of the specific heat capacity of the burnt mixture.

Abstract: A method of detecting a partial flame failure in a gas turbine is provided. The method includes a gas duct to guide a propulsion gas and several combustors, each combustor leads into the gas duct and includes a burner. The method includes measuring a first temperature over time at each of at least two probing points located downstream from the combustors in the gas duct, measuring a second temperature over time in each of at least two of the burners, and detecting a partial flame failure from the first temperature measurements and the second temperature measurements, wherein the detecting of a partial flame failure includes determining a first detection parameter, the first detection parameter is determined from a rate of change of a variation between the first temperature measurements at different probing points. A gas turbine including temperature sensors to detect a partial flame failure is also provided.

Abstract: A method of determining an exit temperature of a gas exiting a combustor of a gas turbine includes determining a mass flow and a temperature of fuel being delivered to the combustor; determining a mass flow and a temperature of air being delivered to the combustor, determining a temperature dependence of the specific heat capacity of a burnt mixture of the fuel and the air being delivered to the combustor; and determining an exit temperature of the burnt mixture exiting the combustor. The exit temperature is determined based on the determined mass flow and temperature of the fuel, the determined mass flow and temperature of the air, and the determined temperature dependence of the specific heat capacity of the burnt mixture.

Abstract: A method of detecting a partial flame failure in a gas turbine is provided. The method includes a gas duct to guide a propulsion gas and several combustors, each combustor leads into the gas duct and includes a burner. The method includes measuring a first temperature over time at each of at least two probing points located downstream from the combustors in the gas duct, measuring a second temperature over time in each of at least two of the burners, and detecting a partial flame failure from the first temperature measurements and the second temperature measurements, wherein the detecting of a partial flame failure includes determining a first detection parameter, the first detection parameter is determined from a rate of change of a variation between the first temperature measurements at different probing points. A gas turbine including temperature sensors to detect a partial flame failure is also provided.