Apparatus and method for consistently retaining a gas turbine engine blade in a predetermined position and orientation

An apparatus for retaining a gas turbine engine blade in a fixed predetermined position, comprising:

• (a) a base portion having a forward end, an aft end, a top surface and a bottom surface, said base portion further including:
• (1) a forward portion located adjacent said forward end, said forward portion including a top surface configured to substantially conform to a suction surface of an airfoil portion for said gas turbine engine blade;
• and
• (2) an elongated groove portion formed in said top surface adjacent said aft end;
• (b) a top portion having a forward end, an aft end, a top surface and a bottom surface, said top portion further including:
• (1) a forward portion located adjacent said forward end, said forward portion including a bottom surface configured to substantially conform to a pressure surface of said airfoil portion for said gas turbine engine blade;
• (2) a pin member extending from said bottom surface at said aft end which is matable with said groove portion of said base portion;
• and,
• (3) a slot portion formed in said top portion bottom surface between said pin member and said forward end;
• (c) a mechanism for connecting said base and top portions at a first designated point between said forward and aft ends;
• and,
• (d) a block member positioned within said slot portion between said base and top portions, said block being adapted to slide along said groove portion between a first position adjacent said designated connection point and a second position adjacent said pin member;
• wherein a predetermined clamping force is provided on said airfoil portion of said gas turbine engine blade between said forward portion top surface of said base portion and said forward portion bottom surface of said top surface when said block member is at said second position.