Abstract: Embodiments of the invention relate to an axial locking system for a row of blades in a turbine engine. While achieving the desired axial restraint, the system is configured to allow remote manipulation of the locking system. For example, a locking system provided on the upstream side of a row of blades can be accessed from the downstream side of the blades. Such a system can provide significant cost savings during the installation and removal of the blades. In one embodiment, the axial locking system can include a plate with a rotatable cam. Cooperating with the disc, the cam can be rotated to bring the radially outer end of the plate into locking engagement with the turbine blades. The cam can be manipulated from the other side of the disc by a tool extending through a passage formed between the disc and the blade root.

Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.

Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only allows for larger compressor blade tip clearances as the engine passes through non-standard operating conditions, but also minimizes clearances during normal engine operation, thereby increasing efficiency of the compressor. The blade assembly can include an airfoil having a movable tip insert recessed within a pocket in the radially distal end of the airfoil. The tip insert can move radially outward from a predetermined recessed position to a predetermined extended position. An abutment surface can be provided within the pocket for engaging the tip insert and/or other associated components so as to limit the extension of the tip insert to the predetermined extended position such that the tip insert does not impinge on the stationary compressor structure and such that a spring operatively associated with the tip insert does not overextend its operational limits.