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 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 borescope plug system includes a housing, a driver, and a spring. The housing includes a first housing end and a second housing end. The housing further includes a longitudinally extending centerline extending between the first housing end and the second housing end. The driver is disposed at least partially within the housing along the longitudinally extending centerline and includes a first driver end and a second driver end. The spring is disposed within the housing and couples the housing to the driver. The driver is configured to move within the housing, along the longitudinally extending centerline, to engage the first driver end with a borescope plug of a borescope plug port, and to install or remove the borescope plug from the borescope plug port based on a rotation of the driver about the longitudinally extending centerline.

Abstract: A conformal heat shield for a gas turbine engine may comprise a first section including a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment. The first arcuate segment and the second arcuate segment may each comprise a distal metal layer including a plurality of loops extending radially outward from the distal metal layer. A proximal metal layer may be located radially inward of the distal metal layer. An insulating material may be located between the distal metal layer and the proximal metal layer. A first strap may be located through the loops.

Abstract: A borescope plug system includes a housing, a driver, and a spring. The housing includes a first housing end and a second housing end. The housing further includes a longitudinally extending centerline extending between the first housing end and the second housing end. The driver is disposed at least partially within the housing along the longitudinally extending centerline and includes a first driver end and a second driver end. The spring is disposed within the housing and couples the housing to the driver. The driver is configured to move within the housing, along the longitudinally extending centerline, to engage the first driver end with a borescope plug of a borescope plug port, and to install or remove the borescope plug from the borescope plug port based on a rotation of the driver about the longitudinally extending centerline.

Abstract: A conformal heat shield for a gas turbine engine may comprise a first section including a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment. The first arcuate segment and the second arcuate segment may each comprise a distal metal layer including a plurality of loops extending radially outward from the distal metal layer. A proximal metal layer may be located radially inward of the distal metal layer. An insulating material may be located between the distal metal layer and the proximal metal layer. A first strap may be located through the loops.