A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.

A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.

A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.

A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface.

A gas turbine engine is provided. The gas turbine engine defines a radial direction. The engine includes: an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount including an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.

A gas turbine engine is provided. The gas turbine engine defines a radial direction. The engine includes: an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount including an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

A computing system for an unducted rotor engine with a variable pitch vane assembly in aerodynamic relationship with an unducted rotor assembly, including a sensor-based controller configured to execute a first set of operations and a model-based controller configured to execute a second set of operations. The first set of operations includes obtaining a first signal corresponding to a commanded low spool speed; obtaining a second signal indicative of a pitch angle corresponding to thrust output from the unducted rotor assembly and variable pitch vane assembly; generating a pitch feedback signal corresponding to a commanded adjustment to the pitch angle based at least on one or both of a variable blade pitch angle or a variable vane pitch angle. The second set of operations include obtaining a desired thrust output via a throttle input; determining, at least via a power management block, a commanded thrust output signal; receiving the commanded thrust output signal; and generating an output signal.