Abstract: An aircraft propulsion system includes a gas turbine engine, a nacelle, and a controller. The gas turbine engine includes a rotational assembly rotatable about an axis. The rotational assembly includes a bladed fan rotor. The bladed fan rotor includes a plurality of fan blades. The nacelle houses the gas turbine engine. The nacelle includes an air inlet. The air inlet forms an inlet flow region. The inlet flow region includes a reference section at and upstream of the plurality of fan blades. The reference section includes a cross-sectional flow area of the inlet flow region. The controller is configured to control the gas turbine engine to operate at or above a target engine speed corresponding to corrected air mass flow rate per unit area through the reference section which is greater than a vortex breakdown threshold for the reference section.

Abstract: A tail cone ventilation system including a tail cone case defining a tail cone interior and a tail cone exterior, the tail cone having a forward portion and an aft portion separated axially along a tail cone axis; an air inlet fluidly coupled with the tail cone interior through ducting, the air inlet located externally from the tail cone interior; a conduit attached to the tail cone case at the tail cone exterior and to a pylon at an opposite end, the conduit comprising a cable chase having cable, the cable being in operative communication with at least one electronic component within the tail cone interior; a cooling supply fluidly coupled between the air inlet and a pylon exhaust, the cooling supply configured to cool the cable within the cable chase; and a fan fluidly coupled with the cooling supply.

Abstract: A method for a gas turbine engine includes calculating an inlet airflow distortion value at a reference area within an airflow duct and in front of a fan of the gas turbine engine. The inlet airflow distortion value is indicative of an air pressure of an air vortex at the reference area caused by a set of crosswind conditions. The calculating is based on a ratio between an inlet airflow static air pressure in the reference area and a total ambient air pressure. The inlet airflow distortion value is compared to a threshold corresponding to a permissible amount of inlet airflow distortion at the reference area for the set of crosswind conditions, and, based on the comparison indicating that the inlet airflow distortion exceeds the threshold, an inlet airflow distortion notification is provided. A system for a gas turbine engine and a method for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine with split variable fan exit guide vanes including a fan duct supporting a circumferential pattern of split variable fan exit guide vanes, the split variable fan exit guide vanes comprising an upper section and a lower section, the upper section and the lower section each being adjustable about an axis extending along a span of each of the split variable fan exit guide vanes; an upper actuator in operative communication with the upper section, the upper actuator configured to independently adjust an incidence angle of the upper section responsive to predetermined gas turbine operating conditions; and a lower actuator in operative communication with the lower section, the lower actuator configured to independently adjust an incidence angle of the lower section responsive to the predetermined gas turbine operating conditions.

Abstract: A gas turbine engine with variable fan exit guide vanes including a fan duct supporting a circumferential pattern of variable fan exit guide vanes, the variable fan exit guide vanes being adjustable about an axis extending along a span of each of the variable fan exit guide vanes; and an actuator in operative communication with the variable fan exit guide vanes, the actuator configured to independently adjust an incidence angle of each of the variable fan exit guide vanes responsive to predetermined gas turbine operating conditions.

Abstract: A gas turbine engine with hybrid fan exit guide vanes including a fan duct supporting a circumferential pattern of split variable fan exit guide vanes, the split variable fan exit guide vanes comprising an upper section and a lower section, the upper section and the lower section each being adjustable about an axis extending along a span of each of the split variable fan exit guide vanes; an upper actuator in operative communication with the upper section, the upper actuator configured to independently adjust an incidence angle of the upper section responsive to predetermined gas turbine operating conditions; and a lower actuator in operative communication with the lower section, the lower actuator configured to independently adjust an incidence angle of the lower section responsive to the predetermined gas turbine operating conditions.

Abstract: A method for a gas turbine engine includes calculating an inlet airflow distortion value at a reference area within an airflow duct and in front of a fan of the gas turbine engine. The inlet airflow distortion value is indicative of an air pressure of an air vortex at the reference area caused by a set of crosswind conditions. The calculating is based on a ratio between an inlet airflow static air pressure in the reference area and a total ambient air pressure. The inlet airflow distortion value is compared to a threshold corresponding to a permissible amount of inlet airflow distortion at the reference area for the set of crosswind conditions, and, based on the comparison indicating that the inlet airflow distortion exceeds the threshold, an inlet airflow distortion notification is provided. A system for a gas turbine engine and a method for a gas turbine engine are also disclosed.