NOZZLE WITH YAW VECTORING VANE

摘要

An exhaust vane (26) disposed in a divergent section (13) of an aircraft ga s turbine engine exhaust nozzle (10) is sideways pivotable about a vane pivot axis (28). The nozzle vane pivot axis (28) may be centrally located at an unvectored nozzle throat (18). Transversely spaced apart upper and lower tips (24, 25) of the exhaust vane (26) may be incorporated to sealingly engage a nozzle outer wall (23) along upper and lower surfaces (35, 37) of the outer wall (23) of the nozzle. The exhaust vane (26) has flat or contoured vane sidewalls (20) and contoured vane sidewalls (20) may be concave. The exhaust vane (26) may have transversely biased apart upp er and lower vane sections (29, 30) extending transversely inwardly from the upper and lower tips (24, 25) of the exhaust vane (26) respectively. The exhaust vane may be articulated having upstream and downstream sections (32, 34) separately sideways pivotable about the vane pivot axis (28) and a second pivot axis (38) downstream of and parallel to the vane pivot axis (28) respectively.