Exhaust nozzle control for a gas turbine engine

A gas turbine engine, comprising:

• a nacelle assembly including an exhaust nozzle coupled to the nacelle assembly, the exhaust nozzle comprising:
• a duct having a first surface and a second opposing surface extending along a duct axis to define an exhaust flow path;
• at least one effector having a body positioned in a recess across the first surface, the body extending along an effector axis between a first effector-sidewall and an opposing second effector-sidewall and extending between an effector leading edge and an effector trailing edge, the effector axis extending longitudinally through the at least one effector, the effector leading edge and the effector trailing edge pivotable about the effector axis to vary a throat area of the exhaust flow path, at least one of the effector leading edge and the effector trailing edge of the at least one effector tapering along the effector axis;
• and
• wherein the at least one of the effector leading edge and the effector trailing edge is pivotable away from the recess and into the exhaust flow path.

A method of exhaust control for a gas turbine engine, comprising:

• positioning a first effector in a first recess extending across an exhaust duct to define a first thrust vector angle with respect to exhaust flow exiting the exhaust duct, the first effector comprising a first edge that is an effector leading edge and a second edge that is an effector trailing edge;
• wherein the first effector having a tapering cross-section at positions along the effector leading edge and the effector trailing edge of the first effector with respect to an effector axis;
• and
• rotating the first effector in a first direction about the effector axis to cause the effector leading edge to be located in the first recess, the first effector trailing edge to extend into the exhaust duct, and the first thrust vector angle to increase such that the exhaust flow is vectored in a third direction.