Having a turbine blade tip clearance adjustment system for increasing the efficiency of the engine (10) (12) by reducing the gap (14) between the turbine blade tip (16) and the radially outer ring segments (18) discloses a gas turbine engine (10). Turbine blade tip clearance adjustment system (12) may have one or more clearance adjusting band (20), clearance adjusting band (20) is radially inner surface (22) of the ring segment (18) It is located outside, and is supported by at least one outer surface of the ring segment (18) (24) to limit radial movement of the ring segments (18). During operation, the clearance adjustment band (20) limits the radial movement of the ring segments (18), a turbine blade tip (16), during the transient start-up state has no constriction point. Furthermore, the minimum gap in a turbine engine operation (14) is seen in the steady state operation of the gas turbine engine (10). Therefore, the clearance adjustment system (12), a gap (14) between the turbine blade tip (16) and ring segment (18), in the steady state operation so that it can be adjusted to zero there.