An aircraft includes a jet engine and a telescopic tube assembly positioned on the jet engine. The telescopic tube assembly includes one end portion of the telescopic tube assembly which is associated with a thrust reverser translating sleeve of the jet engine and an opposing end portion of the telescopic tube assembly which is associated with a fixed portion of the of the jet engine. A jet engine includes a telescopic tube assembly positioned on the jet engine. The telescopic tube assembly includes one end portion of the telescopic tube assembly which is associated with a thrust reverser translating sleeve of a jet engine and an opposing end portion of the telescopic tube assembly which is associated with a fixed portion of the of the jet engine.

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.

Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.

A variable area nozzle assembly includes a fixed nozzle structure, a translating sleeve, a plurality of nozzle segments, and a plurality of segment hoop locking assemblies. The translating sleeve is movably mounted to the fixed nozzle structure. The translating sleeve is translatable along the nozzle axis within the fixed nozzle structure between and to a first axial position and a second axial position. The plurality of nozzle segments form a variable area nozzle extending circumferentially about the nozzle axis. Each nozzle segment of the plurality of nozzle segments is pivotably mounted to the translating sleeve. The plurality of nozzle segments includes a first nozzle segment and a second nozzle segment. The plurality of segment hoop locking assemblies include a first segment hoop locking assembly. The first segment hoop locking assembly includes a hoop crank. With the translating sleeve in the first axial position or the second axial position, the hoop crank restricts circumferential movement of the first nozzle segment relative to the second nozzle segment.

Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.

There is provided a propulsion machine 10 comprising a fluid duct defined by a wall 42, 44 and a moveable member 34, 36 with a sealing module 90, 90 therebetween. The moveable member 34, 36 is moveable relative to the wall 42, 44. The sealing module 90, 90 comprises a mounting structure 92 coupled to the moveable member 34, 36 and an extendable structure 94 having a sealing surface 96. A chamber 98 is defined between the mounting structure 92 and the extendable structure 94 throughout a travel of the extendable structure 94 relative to the mounting structure 92. The sealing module 90, 90 is configured to receive a pressurized actuation fluid into the chamber 98 to load the sealing surface 96 against an opposing surface 43 of the wall 42, 44 to provide a seal with the opposing surface 43.

An exhaust assembly for a turboprop engine, the assembly having: a primary exhaust nozzle disposed at an aft end of an engine core of the turboprop engine; a secondary exhaust nozzle extending aft from the primary exhaust nozzle to an aft end of the secondary exhaust nozzle, a movable panel disposed in the aft end of the secondary exhaust nozzle and movable to decrease an area of the secondary exhaust nozzle.

There is provided a propulsion machine 10 comprising a fluid duct defined by a wall 42, 44 and a moveable member 34, 36 with a sealing module 90, 90 therebetween. The moveable member 34, 36 is moveable relative to the wall 42, 44. The sealing module 90, 90 comprises a mounting structure 92 coupled to the moveable member 34, 36 and an extendable structure 94 having a sealing surface 96. A chamber 98 is defined between the mounting structure 92 and the extendable structure 94 throughout a travel of the extendable structure 94 relative to the mounting structure 92. The sealing module 90, 90 is configured to receive a pressurized actuation fluid into the chamber 98 to load the sealing surface 96 against an opposing surface 43 of the wall 42, 44 to provide a seal with the opposing surface 43.

An exhaust nozzle for a gas turbine engine includes: an exhaust duct configured to receive an exhaust flow of gas from a combustor of the engine; a first flap rotatably coupled to the exhaust duct for rotation about a first axis; a first actuator configured to actuate the first flap about the first axis between a first inner and a first outer position; a second flap rotatably coupled to the exhaust duct for rotation about a second axis; and a second actuator configured to actuate the second flap about the second axis between a second inner and a second outer position. The first and second flaps at least in part define a passageway configured to convey the exhaust flow of gas to an exterior of the gas turbine engine. The first and second axes of rotation are coaxial. Also provides is a method of operating an exhaust nozzle.

A variable area nozzle assembly includes a fixed nozzle structure, a translating sleeve, a plurality of nozzle segments, and a plurality of segment hoop locking assemblies. The translating sleeve is movably mounted to the fixed nozzle structure. The translating sleeve is translatable along the nozzle axis within the fixed nozzle structure between and to a first axial position and a second axial position. The plurality of nozzle segments form a variable area nozzle extending circumferentially about the nozzle axis. Each nozzle segment of the plurality of nozzle segments is pivotably mounted to the translating sleeve. The plurality of nozzle segments includes a first nozzle segment and a second nozzle segment. The plurality of segment hoop locking assemblies include a first segment hoop locking assembly. The first segment hoop locking assembly includes a hoop crank. With the translating sleeve in the first axial position or the second axial position, the hoop crank restricts circumferential movement of the first nozzle segment relative to the second nozzle segment.