Abstract: A replaceable leading edge insert for an: integrally bladed rotor disk in which the insert includes an enlarged base portion that can be inserted into a dovetail shaped slot formed in the rotor disk to secure the insert to the rotor disk against centrifugal loads during the operation of the blade. The blade on the rotor disk is formed without a leading edge and the leading edge insert includes an aft edge of similar shape to the fore edge n the blade such that the insert can be bonded or fastened to the blade along the entire length of the insert from the blade root to the tip. The rotor disk and the insert include a an annular groove formed on the front side in which a retaining ring is inserted to lock the inserts to the rotor disk. The inserts can be made of a different material from the rotor disk and can be formed with a sweep to form a more :aerodynamic and efficient blade.

Abstract: The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.

Abstract: An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.

Abstract: An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.

Abstract: The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.

Abstract: A turbine engine composite blade attachment mechanism is provided, including a blade having an airfoil section, a neck section, and a root section. The root section includes a continuous loop integral with the blade and branching out from the neck section to completely surround a root insert. The blade includes a plurality of fibers which extend from the airfoil section through the neck and around the core. The root section and neck 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.

Abstract: A turbine engine composite blade attachment mechanism is provided, including a blade having an airfoil section, a neck section, and a root section. The root section includes a continuous loop integral with the blade and branching out from the neck section to completely surround a root insert. The blade includes a plurality of fibers which extend from the airfoil section through the neck and around the core. The root section and neck 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.

Abstract: A method of forming a battery terminal of the type having an electrically conductive screw encased within a conductive material casting such as lead. The preferred method uses a pair of die halves axially aligned with one another. A casting of a battery terminal having upper and lower terminal portions is provided, along with an electrically conductive post or screw. The casting and screw are placed between the die halves. The die halves are compressively forced against one another. A forging cone causes the casting to be forced into the thread spaces of the screw or against the surface of the post and changes the exterior angle of the casting.