Abstract: An assembly adapted for use with a gas turbine engine includes a static component and a metering band. The static component is fixed relative to an axis. The metering band is arranged to extend circumferentially at least partway about the axis and is coupled with the static component. The metering band defines at least a portion of a cooling passageway for air to flow through.

Abstract: An assembly adapted for use with a gas turbine engine includes a static component and a metering band. The static component is fixed relative to an axis. The metering band is arranged to extend circumferentially at least partway about the axis and is coupled with the static component. The metering band defines at least a portion of a cooling passageway for air to flow through.

Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor, a vane ring, and an optional power supply system. The fan rotor is configured to discharge thrust in an aft direction when rotated about a central axis. The vane ring is located aft of the fan rotor along the central axis and mounted for rotation about the central axis. The vane ring includes a plurality of airfoils arranged to interact with the thrust discharged by the fan rotor so that the thrust drives rotation of the vane ring.

Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor and an optional power supply system. The fan rotor is mounted for rotation about a central axis and configured to couple to a rotational power source. The fan rotor includes a plurality of variable-pitch fan blades each movable from a thrust-generation orientation to a power-generation orientation.

Abstract: A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

Abstract: A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor, a vane ring, and an optional power supply system. The fan rotor is configured to discharge thrust in an aft direction when rotated about a central axis. The vane ring is located aft of the fan rotor along the central axis and mounted for rotation about the central axis. The vane ring includes a plurality of airfoils arranged to interact with the thrust discharged by the fan rotor so that the thrust drives rotation of the vane ring.

Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor and an optional power supply system. The fan rotor is mounted for rotation about a central axis and configured to couple to a rotational power source. The fan rotor includes a plurality of variable-pitch fan blades each movable from a thrust-generation orientation to a power-generation orientation.