A convergent flap roller assembly is provided that includes a first hanger flange, a second hanger flange, a roller, and a pivot axle. Each hanger flange has a panel, a roller shaft, and at least one track tab. Each roller shaft extends outwardly from the respective panel, and includes a roller shaft bore. The roller has a center bore and an exterior contact surface. The roller shafts are received within the roller center bore and are in contact with each other, and the pivot axle extends through the roller shaft bores.

A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.

A nozzle for a gas turbine engine. An array of convergent petals hingedly coupled to a nozzle exit of fixed diameter. An array of divergent petals, each divergent petal hingedly coupled to one of the array of convergent petals. A cam surface associated with the array of convergent petals. A pivot point coupled to the array of divergent petals by a first linkage and to a fixed point by a second linkage. A cam follower coupled to the second linkage by a third linkage, the cam follower arranged to abut and travel in contact with the cam surface. An actuator coupled to the cam follower and arranged to translate the cam follower along the cam surface to move the convergent and divergent petals.

A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

An assembly is provided for an aircraft. This aircraft assembly include an airframe with a horizontal axis. The aircraft assembly also includes a powerplant arranged with the airframe. The powerplant includes a gas turbine engine, an exhaust nozzle and a flowpath fluidly coupling the gas turbine engine to the exhaust nozzle. The exhaust nozzle includes a support structure and a plurality of nozzle flaps disposed on opposing sides of the flowpath. Each of the nozzle flaps is pivotally connected to the support structure. The exhaust nozzle is configured to exhaust combustion products received from the gas turbine engine along a first trajectory when the nozzle flaps are pivoted into a first arrangement. The first trajectory is angularly offset from the horizontal axis in a vertical upward direction.

A convergent flap roller assembly is provided that includes a first hanger flange, a second hanger flange, a roller, and a pivot axle. Each hanger flange has a panel, a roller shaft, and at least one track tab. Each roller shaft extends outwardly from the respective panel, and includes a roller shaft bore. The roller has a center bore and an exterior contact surface. The roller shafts are received within the roller center bore and are in contact with each other, and the pivot axle extends through the roller shaft bores.

A rear portion of a convergent-divergent nozzle turbojet engine includes a device for controlling the position of a divergent flap relative to that of a convergent flap, including a first connecting rod having a first end portion hinged to the convergent flap and an opposite second end portion, a second connecting rod having a first end portion hinged to the divergent flap and an opposite second end portion, and a third connecting rod having a first end portion hinged to a synchronization ring and an opposite second end portion. The second end portion of the first connecting rod is hinged to the second end portion of the second connecting rod and/or to the second end portion of the third connecting rod, and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod.

A rear part for a turbojet engine includes a variable-geometry nozzle in which a convergent flap is provided with a lever supporting a bearing roller arranged axially between an upstream bearing wall and a downstream bearing wall, which are rigidly secured to a movable part capable of moving axially on command with respect to an upstream stator structure in such a way that the bearing roller is free to move with respect to the upstream and downstream bearing walls in a radial direction. During a downstream movement of the movable part, the upstream bearing wall pushes the lever to pivot a downstream end of the convergent flap towards the longitudinal axis. Operation of the drive mechanism for moving the movable part can thus be optimized while limiting the size and the mass of the mechanism for controlling the flaps.

A variable-geometry convergent-divergent exhaust nozzle includes: a duct to receive exhaust from a combustor; and first and second flap assemblies each including proximal and distal flaps. The first and second proximal flaps are rotatably coupled to the exhaust duct and include entry surfaces that in part define a nozzle passageway to convey the exhaust to an exterior of the engine. The first and second distal flaps are rotatably coupled to the first and second proximal flaps. The first distal flap includes converging and diverging surfaces angled with respect to each other. The second distal flap includes converging and diverging surfaces angled with respect to each other. The converging surfaces define at least in part a convergent portion of the nozzle passageway. The first and second diverging surfaces define at least in part a divergent portion of the nozzle passageway.

A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.