Turbine blade tip gap reduction system for a turbine engine

A turbine blade gap control system (10) configured to move a vane carrier (22) and attached ring segments (16) of a turbine engine (18) axially relative to a turbine blade assembly (28) to reduce the gaps (12) between the tips (20) of the turbine blades (14) and the ring segments (16) to increase the efficiency of the turbine engine (18) once operating in a steady state condition. The turbine blade assembly (28) may be formed from a plurality rows (30) of turbine blades (14) extending radially from a rotor (32), wherein each row (30) may be formed from a plurality of turbine blades (14) and wherein the turbine blades (14) may have tips (20) positioned at an acute angle (24) relative to a rotational axis (26) of the turbine blade assembly (28). A vane carrier (22) may be positioned concentric with the rotor (32) and positioned radially outward from the turbine blades (14), and a plurality of ring segments (16) may be attached to the vane carrier (22).