A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.

An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

A thrust reverser system is provided that includes a sleeve, a fixed cascade structure and a blocker door. The fixed cascade structure is within a cavity of the sleeve when the sleeve is in a sleeve stowed position. The blocker door is within the cavity of the sleeve when the sleeve is in the sleeve stowed position and the blocker door is in a blocker door stowed position. The blocker door projects in a radial inward direction away from the sleeve towards the centerline when the sleeve is in a sleeve deployed position and when the blocker door is in a blocker door deployed position. The blocker door includes a pivot attachment fixed at an end of the blocker door. The pivot attachment is configured to move in a forward direction from a first location to a second location.

An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.