Abstract

It is described a method of determining an exit temperature of a gas exiting a combustor (24) of a gas turbine (10), the method comprising: 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 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. Further a method of controlling a gas turbine is described.