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A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a d

A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a damaged insert from an integrally bladed disk. One or more of the fastener pins provides for an electrical conductive path that bypasses the disbondable composition during a lightening strike so that the insert does not release. Each replaceable insert includes a root portion that fits within a slot of the rotor disk, with each insert being secured against radial displacement by two shear pins secured within two shear pin slots formed in both the insert root portion and the rotor disk slot. The shear pin slots are curved and follow the curvature of the airfoil at the junction to the rotor disk. A retaining and balancing ring is secured within an annular groove and functions to retain the shear pins within the slots and to balance the rotor disk. The combination of the fastener pins, the electrochemically disbondable composition, and the shear pins in the slot provide for three methods of securing an insert to the blade so that a damaged insert can be easily replaced.

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We claim: 1. A replaceable leading edge insert for use on a rotor blade of an IBR, the insert comprising: a leading edge airfoil portion; a root portion with the airfoil portion extending therefrom; a scarf joint on an aft side of the airfoil portion; a row of holes extending along the scarf joint

We claim: 1. A replaceable leading edge insert for use on a rotor blade of an IBR, the insert comprising: a leading edge airfoil portion; a root portion with the airfoil portion extending therefrom; a scarf joint on an aft side of the airfoil portion; a row of holes extending along the scarf joint in a substantially radial direction of the blade to provide for electrically conductive fasteners to secure the insert to the blade; and, an electrically disbondable material on the scarf joint for securing the insert to a rotor blade. 2. The replaceable leading edge insert of claim 1, and further comprising: the root portion of the insert includes two shear pin retainer slots to provide for two shear pins to secure the root portion within a rotor disk slot against radial displacement of the insert. 3. The replaceable leading edge insert of claim 2, and further comprising: the root portion of the insert includes an annular groove to receive an annular retaining ring to prevent the shear pins from the shear pin slots. 4. The replaceable leading edge insert of claim 1, and further comprising: the root portion of the insert forms a flow path surface for the fluid passing around the blade. 5. The replaceable leading edge insert of claim 1, and further comprising: the row of holes is of such spacing to prevent unzipping of the insert form the blade. 6. The replaceable leading edge insert of claim 1, and further comprising: the leading edge insert extends to a blade tip of the blade. 7. An integrally bladed rotor having a plurality of blades extending from the rotor disk with each blade having a forward edge formed to receive a replaceable leading edge insert, the integrally bladed rotor comprising: the replaceable leading edge insert having a scarf joint on the aft edge of the insert with a row of holes to secure the insert to the blade; a plurality of electrically conductive fastener means inserted into the holes to secure the insert to the blade; and, an electrically disbondable material on the scarf joint for securing the insert to a rotor blade. 8. The integrally bladed rotor of claim 7, and further comprising: the row of holes is spaced such that unzipping of the insert from the blade is prevented. 9. The integrally bladed rotor of claim 7, and further comprising: at least one of the plurality of fastener means also provides for an electrical conduction path between the insert and the blade to prevent the electrically disbondable composition from releasing due to a lightening strike to the integrally bladed rotor. 10. The integrally bladed rotor of claim 7, and further comprising: the replaceable leading edge insert extends to the tip of the blade. 11. The integrally bladed rotor of claim 7, and further comprising: the rotor includes a slot for each blade to receive an insert root portion; the rotor slot having two shear pin slots; the replaceable insert having a root portion sized to fit within the slot in the rotor, each root portion having two shear pin slots positioned to form shear pin slots when the insert is placed within the rotor slot; and, two shear pins secured within the slots to radially secure the replaceable insert to the rotor. 12. The integrally bladed rotor of claim 11, and further comprising: the shear pin slots have a curvature that substantially follows the curvature of the airfoil at the junction to the blade platform. 13. The integrally bladed rotor of claim 11, and further comprising: the two shear pin slots each have an opening on the forward side of the rotor and a closed end on the aft side, and each shear pin slot slopes upward from the forward end to the aft end of the rotor. 14. The integrally bladed rotor of claim 11, and further comprising: an annular groove formed underneath the platform of the insert; and, an annular retaining ring secured within the annular groove to retain the shear pins within the shear pin slots. 15. The integrally bladed rotor of claim 14, and further comprising: the retaining ring is also a balancing ring to provide balance to the rotor disk. 16. The integrally bladed rotor of claim 7, and further comprising: at least one of the plurality of fastener means also provides for an electrical conduction path between the insert and the blade to prevent the electrically disbondable composition from releasing due to a lighting strike to the integrally bladed rotor.