Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.

Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.

Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.

Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include 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.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.

Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.

Abstract: A compressor section or a turbine section of a gas turbine engine having an axis includes a drum. The compressor section or the turbine section also includes a plurality of bores extending radially inward from the drum including a first bore and a second bore. The compressor section or the turbine section also includes a first bore basket at least partially defining a first cavity such that the first bore has at least one surface located in the first cavity. The compressor section or the turbine section also includes a second bore basket at least partially defining a second cavity that is isolated from the first cavity such that the second bore has at least one surface located in the second cavity.

Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include 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.

Abstract: A compressor section or a turbine section of a gas turbine engine having an axis includes a drum. The compressor section or the turbine section also includes a plurality of bores extending radially inward from the drum including a first bore and a second bore. The compressor section or the turbine section also includes a first bore basket at least partially defining a first cavity such that the first bore has at least one surface located in the first cavity. The compressor section or the turbine section also includes a second bore basket at least partially defining a second cavity that is isolated from the first cavity such that the second bore has at least one surface located in the second cavity.