Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Various embodiments include a system having: a computing device configured to monitor a gas turbine (GT) by: determining a moisture content and/or an oxygen content of inlet air entering the inlet of the GT compressor section; determining a corresponding one of the moisture content and/or the oxygen content of exhaust gas from the GT turbine section; calculating a flow rate of the exhaust gas from the turbine section and a flow rate of the inlet air entering the inlet of the compressor section based upon the moisture content and/or the oxygen content of the inlet air and the exhaust gas; and calculating a temperature of the exhaust gas and an energy of the exhaust gas from the turbine section based upon the flow rate of the exhaust gas from the turbine and the flow rate of the inlet air entering the inlet of the compressor section.

This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.

A method for optimizing a climb phase of an aircraft, implemented repeatedly during the climb phase, includes an acquiring step for acquiring current values of input parameters, a determining step for determining a current optimized DT.sub.flex value from the current values of the input parameters and from optimized DT.sub.flex values recorded in a database and a transmitting step for transmitting the determined current optimized DT.sub.flex value to a user system with a view to controlling the thrust of the aircraft, the method making it possible to continuously adapt, during the climb phase, the optimized DT.sub.flex value so it corresponds to current conditions of the aircraft to maximize its performance particular for fuel consumption.

The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight.

A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.