are enveloped by a jacket having a thickness which increases from the distal side surface of the loop to the neck portion and has an inner contour substantially aligned with the proximal side surface contour of the loop and the core the jacket and root are disposed inside a rotary disk cavity such that when tensile loading is applied the neck width is maintained and compressive transverse loads may be applied to the fibers to prevent lamination thereof application_number US 64625703 A description as used herein a u201c jacket u201d shall mean any outer layer type structure enveloping an inner structure such as a sheath cladding ring or coating also as used herein a u201c shim u201d shall mean any piece of material used to fill gaps make something level or adjust something to fit properly or any material placed between two parts to make the parts continuously connect or fit both a jacket or shim may be made of any material also as used herein a u201c blade u201d shall mean any structure used in turbine engines turbomachinery aircraft mobile or stationary powerplants or other machines or devices which include a structure having surfaces which interact with fluid flows blades shall include vanes airfoils rudders and any other aerodynamic hydrodynamic or control surface structures also as used herein the term u201c circumscribe u201d shall refer to one element enclosing surrounding or abutting against another element to as to be substantially in contact with the outer surface of the circumscribed element but not necessarily all of such outer surface 0026 fig3 is a simplified schematic of the attachment principles employed in the present invention since composite blades are generally made up of a number of longitudinal layers having a relatively high tensile strength the present invention takes advantage.