Vectoring exhaust nozzle for an aircraft powerplant

An assembly for an aircraft, comprising:

• an airframe with a horizontal axis;
• a powerplant arranged with the airframe, the powerplant including a gas turbine engine, an exhaust nozzle and a flowpath fluidly coupling the gas turbine engine to the exhaust nozzle;
• the exhaust nozzle including a support structure and a plurality of nozzle flaps disposed on opposing sides of the flowpath, and each of the plurality of nozzle flaps pivotally connected to the support structure;
• the exhaust nozzle configured to exhaust combustion products received from the gas turbine engine along a first trajectory when the plurality of nozzle flaps are pivoted into a first arrangement, wherein the first trajectory is angularly offset from the horizontal axis in a vertical upward direction;
• a first of the plurality of nozzle flaps configured as a multi-segment nozzle flap, and the first of the plurality of nozzle flaps pivotally connected to the support structure by a first pivot connection at an intersection between the first of the plurality of nozzle flaps and the support structure;
• and
• a second of the plurality of nozzle flaps configured as a unitary body nozzle flap;
• and
• a propulsor comprising an open propulsor rotor, the gas turbine engine configured to drive rotation of the open propulsor rotor about a rotational axis of the open propulsor rotor, and the assembly configured to reorient the propulsor relative to the airframe in order to change an orientation of the rotational axis of the open propulsor rotor relative to the airframe,
• wherein the flowpath has a first lateral width at an outlet of the gas turbine engine and a second lateral width at the exhaust nozzle, and the first lateral width is smaller than the second lateral width;
• and
• wherein the flowpath has a first vertical height at the outlet from the gas turbine engine and a second vertical height at the exhaust nozzle, and the first vertical height is greater than the second vertical height.

An assembly for an aircraft, comprising:

• an airframe comprising a horizontal axis and a fuselage;
• a powerplant including a gas turbine engine, an exhaust nozzle and a flowpath fluidly coupling the gas turbine engine to the exhaust nozzle;
• the gas turbine engine disposed within the fuselage;
• the exhaust nozzle including a support structure and a plurality of nozzle flaps disposed on opposing sides of the flowpath, and each of the plurality of nozzle flaps pivotally connected to the support structure;
• the exhaust nozzle configured to exhaust combustion products received from the gas turbine engine along a first trajectory when the plurality of nozzle flaps are pivoted into a first arrangement, wherein the first trajectory is angularly offset from the horizontal axis in a vertical upward direction;
• and
• a tiltrotor module arranged remote from the fuselage and comprising a propulsor rotor, the gas turbine engine configured to drive rotation of the propulsor rotor about a rotational axis of the propulsor rotor, and the tiltrotor module configured to change an orientation of the rotational axis of the propulsor rotor relative to the fuselage,
• wherein the flowpath has a first lateral width at an outlet of the gas turbine engine and a second lateral width at the exhaust nozzle, and the first lateral width is smaller than the second lateral width;
• and
• wherein the flowpath has a first vertical height at the outlet from the gas turbine engine and a second vertical height at the exhaust nozzle, and the first vertical height is greater than the second vertical height.