System and method of locating feathering propeller blade angular position

Abstract

The present disclosure is directed to a turbine engine () defining an axial direction, a radial direction, a circumferential direction, a first end () and a second end () opposite of the first end () along the axial direction. The turbine engine includes a propeller assembly () proximate to the first end including a plurality of blades () arranged in the circumferential direction disposed around an axial centerline (), and a feathering mechanism () including a hollow piston rod (). The feathering mechanism rotates the plurality of blades about a pitch axis () extended in the radial direction from the axial centerline. The turbine engine further includes a housing () proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly () extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe () extended along the axial direction. The beta tube assembly further defines a plurality of grooves () extended along the axial direction proximate to the housing. A first groove () extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix () corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove () extends in the axial direction.