Inserts for slotted integrally bladed rotor

A gas turbine engine comprising:

• an integrally bladed rotor having a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor,
• wherein each of the rotor slot and the rotor slot insert has straight sidewalls, wherein the integrally bladed rotor further comprises an axial retaining element configured to secure the rotor slot insert to the integrally bladed rotor in an axial direction and a radially retaining element configured to secure the rotor slot insert to the integrally bladed rotor in a radial direction.