Abstract: A gas turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), a variable nozzle airfoil (463), and a position selector (470). The inner shroud (462) is located radially inward from the outer shroud (461). The variable nozzle airfoil (463) extends radially between the outer shroud (461) and the inner shroud (462). The variable nozzle airfoil (463) includes a vane shaft (464) extending radially outward from the variable nozzle airfoil (463) through the outer shroud (461). The position selector (470) is coupled with the variable nozzle airfoil (463) to fixedly lock the variable nozzle airfoil (463) into one of a plurality of preselected positions.

Abstract: A gas-turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), and a variable nozzle airfoil (463). The outer shroud (461) includes a first spherical surface (466), a radially inner surface of the outer shroud (461). The inner shroud (462) includes a second spherical surface (467), a radially outer surface of the inner shroud (462). The variable nozzle airfoil (463) includes an outer edge (468) adjacent to the first spherical surface (466) and an inner edge (469) adjacent to the second spherical surface (467). The outer edge (468) has a curve which matches the contour of the first spherical surface (466). The inner edge (469) has a curve which matches the contour of the second spherical surface (467).