Patent ID: 9708914
Date: 2017-07-18
CPC Classifications: F01D,F04D,F05D,Y02T

Claim:
1. A gas turbine engine comprising a variable position airfoil member that includes a hub end having a leading edge and a trailing edge, the variable position airfoil member disposed within a flow path annulus adjacent a hub flow path surface having a divot that includes a downstream end in which a radial rate of growth of the downstream end is increasing, the variable position airfoil member pivotable around an adjustment axis and capable of being moved between a first position and a second position where the first position provides a flow area greater than a flow area in the second position, the hub end offset from the divot to permit pivoting movement of the variable position airfoil member without interference from the flow path surface between the first position and the second position, wherein the offset between the flow path surface of the divot and the hub end of the variable position airfoil member is constant as the variable position airfoil member moves between the first position and the second position, wherein the hub end is spherical, the variable position airflow member includes a tip end that is spherical, and the axial extent of spherical shape at the tip end forward of a pivot axis of the variable position airflow member is shifted backward relative to the axial extent of the spherical shape at the hub end forward of the pivot axis.