A method for a hybrid electric propulsion (HEP) system includes utilizing a soft actor-critic agent, which includes at least one neural network, and a control barrier function (CBF) filter to obtain a power splitting profile for an HEP system. The power splitting profile includes an electric motor power for an electric motor of the HEP system and a gas turbine power for a gas turbine of the HEP system. The electric motor power and gas turbine power collectively provide a combined HEP output power. The method also includes, during a flight of an aircraft that includes the HEP system, performing an output action for the HEP system based on the power splitting profile. The utilizing is performed based on a predefined fuel consumption objective and a state of charge of at least one battery that powers the electric motor. A system for a HEP system is also disclosed.

A combustion control device is installed in a gas turbine including a compressor, a combustor, a turbine, a turbine bypass pipe through which compressed air from a casing is discharged to a turbine downstream part so as to bypass the turbine, and a turbine bypass valve that regulates a turbine bypass flow rate of the compressed air. The combustion control device includes: a fuel distribution setting unit that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section that sets the valve openings of fuel regulating valves. The fuel distribution setting unit includes correction means for modifying the fuel distribution ratios.

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.

A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured combustor instability against a predicted combustor instability. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured combustor instability differ from their predicted values by more than respective predetermined thresholds.

A non-transitory computer readable storage medium storing one or more processor-executable instructions wherein the one or more instructions when executed by a processor of a controller, cause acts to be performed is provided. The acts to be performed include controlling a fuel split to a combustor of a gas turbine utilizing automatic tuning and switching control of the fuel split to the combustor of the gas turbine to utilizing an adjusted fixed fuel split schedule instead of automatic tuning. The adjusted fixed fuel split schedule includes a fixed fuel split schedule adjusted via a biasing value, and the biasing value is based on both the fixed fuel split schedule and an automatic tuning based fuel split.

A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.

A system includes an injector including a scheduling valve assembly and a nozzle in fluid communication with the scheduling valve assembly. The injector includes two fluid circuits, a primary circuit and a secondary circuit, between the inlet of the injector and two respective outlets for staged flow output. A cooling circuit is in fluid communication with the inlet of the injector. The cooling circuit is in thermal communication with the secondary circuit for selectively cooling the secondary circuit at low flow and no flow conditions of the secondary circuit. A separate valve is connected in fluid communication in the cooling circuit for controlling flow through the cooling circuit. The separate valve is configured for active control regardless of pressure at the inlet of the injector. The scheduling valve assembly is configured for passive control of the primary and secondary circuits based on pressure at the inlet of the injector.

A method of controlling a flow of a fuel mixture of different types of fuel in a gas turbine engine is described which includes determining a combustive energy value of an input of the fuel mixture in the engine, extracting fuel schedule data from a fuel schedule established for a reference fuel, determining a desired fuel mixture flow rate by adapting the fuel schedule data to the fuel mixture based on the combustive energy value, and controlling a fuel metering device of the engine such that the fuel mixture flow rate corresponds to the desired fuel mixture flow rate.

The present disclosure is directed to a method of control of a gas turbine engine comprising a fan section coupled to a low turbine together defining a low spool, an intermediate compressor coupled to an intermediate turbine together defining an intermediate spool, and a high compressor coupled to a high turbine together defining a high spool. The method includes providing an intermediate spool speed to low spool speed characteristic curve to a controller; providing a commanded power output to the controller; providing one or more of an environmental condition to the controller; determining, via the controller, a commanded fuel flow rate; determining, via the controller, a commanded intermediate compressor loading; and generating an actual power output of the engine, wherein the actual power output is one or more of an actual low spool speed, an actual intermediate spool speed, an actual high spool speed, and an actual engine pressure ratio.

The disclosure relates to optimization of gas turbine power plant response during power system transients. In certain embodiments, systems, methods, and apparatus can control a power generating system by using the reactive components of the current and the reactive components of the voltage and the magnitude of the voltage at the generator terminals of a gas turbine generator system. In one embodiment, a system can identify a power system fault based on at least three conditions occurring for a specified duration and at substantially the same time: (1) an increase in the reactive current, (2) a decrease in the magnitude of the voltage, and (3) an increase in the reactive power. In one embodiment, a power system can further detect a remote breaker open (RBO) condition, and distinguish a RBO condition from a power system fault condition.