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 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.

Exemplary embodiments are disclosed of variable frequency drive (VFD) controllers with engine fail-over and systems including the same. In exemplary embodiments, a system includes a controller configured to be operable for controlling a VFD that drives a motor (e.g., a three-phase AC motor, etc.), which, in turn, drives (e.g., mechanically spins, etc.) a first pump. The same controller is also configured to be operable for controlling an engine (e.g., a diesel engine, etc.), which, in turn, drives (e.g., mechanically spins, etc.) a second pump. The system is configured to failover from the motor to the engine in response to a VFD communications failure.

An output corrector is provided with an adjustment coefficient creating unit which creates an adjustment coefficient, an output adjusting unit which adjusts a control output using the adjustment coefficient, and an output accepting unit which accepts an output from an output meter for detecting the output of a gas turbine. The adjustment coefficient creating unit includes a first coefficient element calculating unit which calculates a first coefficient element, a second coefficient element calculating unit which calculates a second coefficient element, and an adjustment coefficient calculating unit which calculates the adjustment coefficient using the first and second coefficient elements. The first coefficient element is the ratio of an immediately preceding output in an immediately preceding time period, to a reference output at a reference time point in the past. The second coefficient element is the ratio of the current output in the current time period, to the immediately preceding output.

A state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.

In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (W.sub.fdem) of fuel flow (W.sub.f) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (W.sub.f) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (W.sub.f) when the gas generator speed rate of change (N.sub.gdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (W.sub.fdot) of the fuel flow rate of change (W.sub.fdot), or fuel flow (W.sub.f), allowing the gas generator speed rate of change (N.sub.gdot) to track a scheduled reference value (Ngdot.sub.ref).

A system for increasing the efficiency of low pressure axial fans, includes, a low pressure axial fan including multiple first blades, and, a vortex generator operably coupled to the low pressure axial fan via a shaft. In use, the vortex generator includes multiple second blades. In further use, the low pressure axial fan is configured to operate in an operational mode and the vortex generator is configured to operate in a stationary mode.

An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.

An Electronic Engine Controller (EEC) for a gas turbine engine. The EEC is configured to be connected to a solenoid valve, and configured to control the solenoid valve by providing a driving signal to either a first solenoid winding or a second solenoid winding of the solenoid valve, the first and second solenoid windings being magnetically coupled to one another by an armature of the solenoid valve. The armature is movable under the action of the driving signal to operate the solenoid valve. The solenoid winding of the first and second solenoid windings provided with the driving signal is a driving winding and the other solenoid winding of the first and second solenoid windings is a pick-up winding. When the EEC controls the solenoid valve via the driving winding by providing the driving signal thereto, it is further configured to sense a position of the solenoid valve via the pick-up winding by detecting a signal induced in the pick-up winding by the magnetic coupling.

A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a low speed spool and a high speed spool; a rotor assembly coupled to the low speed spool; an electric machine rotatable with the low speed spool for extracting power from the low speed spool, for adding power to the low speed spool, or both; and an inter-spool clutch positioned between the low speed spool and the high speed spool for selectively coupling the low speed spool to the high speed spool.