| 主权项 |
1. A gas turbine engine comprising:
a compressor in a flow path, the compressor including moveable inlet guide vanes; and an actuating system drivingly connected to the moveable inlet guide vanes, the system including:
a face gear located out of the flow path and rotationally engaged to a central support having a fixed position with respect to the compressor, the face gear rotatable about a central axis of the compressor, a radial or substantially radial surface of the face gear defining circumferentially spaced teeth each defining land surfaces,a pinion engaged to and extending transversely from an end of each of the vanes, each pinion having an array of involute gear teeth spaced apart from the vane end, each pinion in meshed engagement with the face gear, the teeth of each pinion defining land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith, a smallest axial distance between the adjacent land surfaces of the meshed pinion and face gear teeth defining a backlash of the actuating system, andat least one shim abutting the pinion or the face gear and having a thickness adjusting an axial distance between the pinion and the face gear to set the backlash to a predetermined value. |
