Abstract: A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.

Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

Abstract: A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.

Abstract: A propulsion system is provided. The propulsion system defines a radial direction and includes a rotating element; a stationary element; an inlet assembly defining an inlet positioned between the rotating element and the stationary element and positioned inward of the stationary element along the radial direction, the inlet assembly comprising an inlet duct located downstream of the inlet; and a ducted fan comprising a plurality of fan blades positioned at least partially in the inlet duct; wherein the inlet duct divides into a first duct and a second duct separate from the first duct, wherein the first duct is a core duct downstream of the ducted fan, wherein the second duct is a fan duct downstream of the ducted fan, and wherein the second duct includes an exhaust nozzle having a plurality of chevrons disposed at an aft end of the exhaust nozzle to define an exhaust outlet.

Abstract: A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.

Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

Abstract: An aircraft includes a fuselage, a wing connected to and extending outward from the fuselage, and an engine mounted to the wing. The engine includes turbomachine defining a centerline axis, a fan, and an exhaust section with an outlet nozzle. The turbomachine defines a centerline axis. The fan is connected to and is disposed upstream from the turbomachine. The fan is disposed to rotate about the centerline axis. During operation of the engine, an exhaust stream is expelled from the outlet nozzle of the exhaust section. The exhaust stream defines a mean direction of flow in the downstream direction from the exhaust section. The mean direction of flow defines a first angle with the centerline axis of the turbomachine that is greater than zero such that the centerline axis is oriented downwardly along the vertical direction relative to the mean direction of flow of the exhaust stream.

Abstract: A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.

Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

Abstract: A turbofan engine includes a core engine, a fan, a fan bypass duct partially surrounding the core engine and the fan, and a bleed system. The bleed system includes a first bleed circuit configured to bleed pressurized air from the core engine and channel the flow to a first circuit of a heat exchanger, and a second bleed circuit configured to bleed fan air from the fan bypass duct and channel the flow to a second circuit of the heat exchanger. The second bleed circuit includes a bleed duct including a duct inlet and a duct outlet coupled in flow communication with the heat exchanger through a valve. The bleed duct also includes an acoustic suppression conduit extending from the bleed duct upstream of the valve to the fan bypass duct and sized to suppress pressure oscillations inside the second bleed circuit when the valve is at least partially closed.

Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

Abstract: A turbofan engine includes a core engine, a fan, a fan bypass duct partially surrounding the core engine and the fan, and a bleed system. The bleed system includes a first bleed circuit configured to bleed pressurized air from the core engine and channel the flow to a first circuit of a heat exchanger, and a second bleed circuit configured to bleed fan air from the fan bypass duct and channel the flow to a second circuit of the heat exchanger. The second bleed circuit includes a bleed duct including a duct inlet and a duct outlet coupled in flow communication with the heat exchanger through a valve. The bleed duct also includes an acoustic suppression conduit extending from the bleed duct upstream of the valve to the fan bypass duct and sized to suppress pressure oscillations inside the second bleed circuit when the valve is at least partially closed.

Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.