Abstract: A turbine engine including an engine core, a nacelle, and a cowl door. The engine core including in serial, axial flow arrangement a compressor section, a combustor section, and a turbine section and defining a first airflow axially through the engine core. The nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface and an internal passage located between the exterior surface and the engine core and defining a third airflow. The cowl door located along the nacelle.

Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.

Abstract: A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.

Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.

Abstract: A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.

Abstract: A method of starting a gas turbine engine having a rotor comprising at least a shaft-mounted compressor and turbine, with a casing surrounding the rotor includes an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine.

Abstract: A method of starting a gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor.