An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.

The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed positions. The system includes a hydraulic actuator to move the thrust reverser element between the stowed and deployed positions, and a directional control valve with a regeneration feature including a restrictor and a velocity fuse arranged in parallel with the restrictor. The velocity fuse is configured to close when the assisting load on the thrust reverser element increases the flow rate of hydraulic fluid through the velocity fuse above threshold value. In operation, the system defines a first movement speed when the velocity fuse is open, and a second movement speed when the velocity fuse is closed, thereby decreasing an effective exit orifice size of the hydraulic actuator when the assisting load increases the deploy rate.

The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed positions. The system includes a hydraulic actuator to move the thrust reverser element between the stowed and deployed positions, and a directional control valve with a regeneration feature including a restrictor and a velocity fuse arranged in parallel with the restrictor. The velocity fuse is configured to close when the assisting load on the thrust reverser element increases the flow rate of hydraulic fluid through the velocity fuse above threshold value. In operation, the system defines a first movement speed when the velocity fuse is open, and a second movement speed when the velocity fuse is closed, thereby decreasing an effective exit orifice size of the hydraulic actuator when the assisting load increases the deploy rate.

An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed positions. The system includes a hydraulic actuator to move the thrust reverser element between the stowed and deployed positions, and a directional control valve with a regeneration feature including a restrictor and a velocity fuse arranged in parallel with the restrictor. The velocity fuse is configured to close when the assisting load on the thrust reverser element increases the flow rate of hydraulic fluid through the velocity fuse above threshold value. In operation, the system defines a first movement speed when the velocity fuse is open, and a second movement speed when the velocity fuse is closed, thereby decreasing an effective exit orifice size of the hydraulic actuator when the assisting load increases the deploy rate.