Abstract: Example variable geometry systems with split actuation are disclosed herein. In one example, a compressor is provided that includes a compressor stage and an actuation system. The compressor stage includes a plurality of variable stator vanes arranged along a circumference of the compressor stage. The actuation system is to actuate a first variable stator vane of the compressor stage according to a first schedule and to actuate a second variable stator vane of the compressor stage according to a second schedule.

Abstract: A stator assembly for a gas turbine engine includes: (a) an outer shroud having a circumferential array of outer slots; (b) an inner shroud having a circumferential array of inner slots; (c) a plurality of airfoil-shaped vanes extending between the inner and outer shrouds, each vane having inner and outer ends which are received in the inner and outer slots; and (d) an annular, resilient retention ring spring which engages the inner ends of the vanes and urges them in a radially inward direction.

Abstract: A stator assembly for a gas turbine engine includes: (a) an outer shroud having a circumferential array of outer slots; (b) an inner shroud having a circumferential array of inner slots; (c) a plurality of airfoil-shaped vanes extending between the inner and outer shrouds, each vane having inner and outer ends which are received in the inner and outer slots; and (d) an annular, resilient retention ring spring which engages the inner ends of the vanes and urges them in a radially inward direction.

Abstract: A method facilitates balancing a gas turbine rotor. The method includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that couples to the tip shroud leading edge, a shorter second portion that extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and couples to at least one of the tip shroud leading and trailing edges.

Abstract: A method for balancing a gas turbine rotor includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that is configured to couple to the tip shroud leading edge, a second portion having a second length that is shorter than the first length, such that the second portion extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and is configured to couple to at least one of the tip shroud leading and trailing edges.