Patent ID: 11867135
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An assembly for an aircraft, comprising:
a powerplant including a gas turbine engine, an exhaust nozzle and a flowpath extending from the gas turbine engine to the exhaust nozzle;
the exhaust nozzle movable between a first position and a second position;
the exhaust nozzle configured to exhaust combustion products received from the flowpath when the exhaust nozzle is in the first position;
the exhaust nozzle configured to block flow of the combustion products through the exhaust nozzle when the exhaust nozzle is in the second position; and
a passage extending through the exhaust nozzle along a nozzle centerline, wherein the nozzle centerline of the exhaust nozzle in the first position is angularly offset from the nozzle centerline of the exhaust nozzle in the second position by an included angle.