Abstract: 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.

Abstract: A method for controlling the operation of a gas turbine includes monitoring an operating parameter of the gas turbine engine. The method also includes determining a first position demand for controlling an operation of a first actuator based on the monitored operating parameter. In addition, the method includes controlling the operation of the first actuator based on the first position demand to adjust the angular position of at least one airfoil included within a first array of airfoils. The method further includes determining a second position demand for controlling the operation of a second actuator based on the first position demand. In addition, the method also includes controlling the operation of the second actuator based on the second position demand to adjust the angular position of at least one airfoil included within a second array of airfoils.

Abstract: 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.

Abstract: A method for controlling the operation of a gas turbine includes monitoring an operating parameter of the gas turbine engine. The method also includes determining a first position demand for controlling an operation of a first actuator based on the monitored operating parameter. In addition, the method includes controlling the operation of the first actuator based on the first position demand to adjust the angular position of at least one airfoil included within a first array of airfoils. The method further includes determining a second position demand for controlling the operation of a second actuator based on the first position demand. In addition, the method also includes controlling the operation of the second actuator based on the second position demand to adjust the angular position of at least one airfoil included within a second array of airfoils.

Abstract: A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regulator within the engine, and receives input from a plurality of sensors coupled to the engine. More specifically, the system receives input from environmental sensors, as well as inputs representing compressor inlet temperature, compressor discharge pressure, and corrected core engine speed. Furthermore, the fuel control system also receives input from the other engine fuel regulators.

Abstract: A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regulator within the engine, and receives input from a plurality of sensors coupled to the engine. More specifically, the system receives input from environmental sensors, as well as inputs representing compressor inlet temperature, compressor discharge pressure, and corrected core engine speed. Furthermore, the fuel control system also receives input from the other engine fuel regulators.

Abstract: A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regulator within the engine, and receives input from a plurality of sensors coupled to the engine. More specifically, the system receives input from environmental sensors, as well as inputs representing compressor inlet temperature, compressor discharge pressure, and corrected core engine speed. Furthermore, the fuel control system also receives input from the other engine fuel regulators.

Abstract: A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regulator within the engine, and receives input from a plurality of sensors coupled to the engine. More specifically, the system receives input from environmental sensors, as well as inputs representing compressor inlet temperature, compressor discharge pressure, and corrected core engine speed. Furthermore, the fuel control system also receives input from the other engine fuel regulators.