An operation control device for a single shaft gas turbine selects an operation mode based on a load state of a power generator, and controls the turbine based on the operation mode. In a first operation mode, a rotational speed of the turbine is maintained within a first rotational speed range, and in a second operation mode, the rotational speed is maintained within a second rotational speed range set on a lower rotational speed side than the first rotational speed range. The second rotational speed range is set on the lower rotational speed side than the first rotational speed range with a first non-selection rotational speed range set therebetween.

An operation control device for a single shaft gas turbine selects an operation mode based on a load state of a power generator, and controls the turbine based on the operation mode. In a first operation mode, a rotational speed of the turbine is maintained within a first rotational speed range, and in a second operation mode, the rotational speed is maintained within a second rotational speed range set on a lower rotational speed side than the first rotational speed range. The second rotational speed range is set on the lower rotational speed side than the first rotational speed range with a first non-selection rotational speed range set therebetween.

A method and system for acquiring fuel characteristics on board an aircraft. The method for acquiring fuel characteristic on board an aircraft includes a least one tank and comprises a determination step determining a fuel circuit in one tank among the tank or tanks. The circuit includes at least one pump pumping the fuel from the tank into the circuit. A fuel properties measurement unit and a first valve are configured to open or close the circuit. A filling step includes filling the circuit with fuel. An acquisition step includes acquiring a value respectively for each of the fuel characteristics of the tank, and a transmission step includes transmitting, to a user device, a signal representative of the acquired values of the fuel characteristics.

A method and system for acquiring fuel characteristics on board an aircraft. The method for acquiring fuel characteristic on board an aircraft includes a least one tank and comprises a determination step determining a fuel circuit in one tank among the tank or tanks. The circuit includes at least one pump pumping the fuel from the tank into the circuit. A fuel properties measurement unit and a first valve are configured to open or close the circuit. A filling step includes filling the circuit with fuel. An acquisition step includes acquiring a value respectively for each of the fuel characteristics of the tank, and a transmission step includes transmitting, to a user device, a signal representative of the acquired values of the fuel characteristics.

A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

A gas turbine includes a compressor configured to compress air; a combustor configured to mix and combust fuel and compressed air compressed by the compressor; a turbine configured to obtain rotational power using combustion gas generated by the combustor; an inlet guide vane disposed at an intake of the compressor to adjust a flow rate of air flowing into the compressor; a bleed line configured to return a part of the compressed air pressurized in the compressor to the intake of the compressor; and an on-off valve disposed in the bleed line. When the output of the gas turbine increases, a preset maximum value limit of the inlet guide vane is corrected based on a valve opening degree command value of the on-off valve and a compressor intake temperature such that the gas turbine achieves a predetermined performance.

A cooling system for use with a turbine engine. The system includes a coolant reservoir configured to store cooling fluid therein, and a cooling device coupled in flow communication with the coolant reservoir, wherein the cooling device is configured to cool heated components of the turbine engine with the cooling fluid. The system further includes a first valve configured to control flow of the cooling fluid from the coolant reservoir towards the cooling device, and a controller coupled in communication with the first valve. The controller is configured to monitor an operational status of the turbine engine, and actuate the first valve into an open position after the turbine engine has been shut down such that the cooling fluid cools the heated components.

A system and method for increasing power output of a gas turbine. A method of increasing a power output of a gas turbine comprises providing an auxiliary system configured to be coupled to the gas turbine. The auxiliary system includes a natural gas engine, a compressor, and a heat exchanger fluidly coupled to the compressor. The method includes fluidly coupling the auxiliary system to a combustor case of the gas turbine. The method comprises operating the natural gas engine to drive the compressor to compress air to form compressed air and directing exhaust of the natural gas engine to the heat exchanger. The method includes heating the compressed air in the heat exchanger using the exhaust of the natural gas engine to form heated compressed air and injecting the heated compressed air into the combustor case of the gas turbine.

A system and method for increasing power output of a gas turbine. A method of increasing a power output of a gas turbine comprises providing an auxiliary system configured to be coupled to the gas turbine. The auxiliary system includes a natural gas engine, a compressor, and a heat exchanger fluidly coupled to the compressor. The method includes fluidly coupling the auxiliary system to a combustor case of the gas turbine. The method comprises operating the natural gas engine to drive the compressor to compress air to form compressed air and directing exhaust of the natural gas engine to the heat exchanger. The method includes heating the compressed air in the heat exchanger using the exhaust of the natural gas engine to form heated compressed air and injecting the heated compressed air into the combustor case of the gas turbine.

A method for extending an operating window of an operating mode of a gas turbine engine includes monitoring operating conditions of the gas turbine engine. The gas turbine engine is prevented by the method from transitioning from the first operating mode up to a second operating mode. A bulk temperature demand of the gas turbine engine is adjusted by a predefined amount to generate a first biased bulk temperature demand. The adjustment includes applying a first incremental bias to a bulk flame temperature schedule. The operation of the gas turbine engine is then adjusted based on the first biased bulk temperature demand. The monitored operating conditions are analyzed to determine whether one of the operating conditions has reached a threshold value.