The invention relates to a method for controlling the operation of a gas turbine with a compressor (2) compressing intake air (1) and with at least one combustor (8, 9) for the combustion of liquid and/or gaseous fuel (5, 6) in the compressed gas stream (1...

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...

A control system (40) for a turbofan (10) comprises a variable area nozzle (26) for regulating core flow ( Fc ) through the turbofan, an actuator (27), a temperature sensor (42), a flight controller (44) and a nozzle control (47). The actuator (27) is coup...

The method involves determination of average temperature within the range of the conduit of gas flow in partial load operation. The correction temperature level for the compensation of the distortions in the temperature distribution of the gas flow is dete...

An arrangement for controlling flow of fluid to a component of a gas turbine engine 10, the arrangement comprising: a conduit

A gas turbine plant includes a combustion section (3), a turbine section (2), an exhaust section (12), a temperature detecting unit (13), and a monitoring unit (15). The combustion section combusts fuel using air to generate combustion gas. The turbine sec...

The gas turbine has a combustion chamber (6), a row of guide blades (3), and temperature sensors (8). These consist of spectrometers operating in optical, IR or UV range and measure combustion gas temperature, and gas temperature at a distance of 0,1 to 5 ...

A gas turbine engine (10) including a temperature sensor assembly (110) that continuously monitors an operating temperature within a multi-stage rotor assembly (18) of the turbine engine is described. A plurality of cavities (100) are defined within the mu...