Abstract: A machine comprising a rotor having: an inner member; an outer member encircling the inner member; and a groove in one of the inner member and the outer member. The groove has a first side wall, a second side wall and a base. A split ring seal is accommodated in the groove and contacts a surface of the other of the inner member and the outer member The first side wall has a plurality of open radial first channels and the second side wall has a plurality of open radial second channels.

Abstract: A turbine engine rotor has a central shaft and a disk stack having a plurality of disks encircling the shaft. A seal has a first member having, in central axial cross-section: a rearwardly-open channel receiving a portion of one of the disks; a sleeve extending rearward from the channel and between the disk and the shaft; and a portion extending radially inward from the sleeve and having a forward surface. The seal has a second member having, in central axial cross-section: a forward-facing surface contacting an aft-facing surface of the shaft; and a rear-facing surface contacting the forward surface of said portion extending radially inward from the sleeve.

Abstract: A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

Abstract: A turbine engine rotor has a central shaft and a disk stack having disks encircling the shaft. A seal has in central axial cross-section: a rearwardly-open channel receiving a portion of one of the disks; a sleeve extending rearward from the channel and between the disk and the shaft; and a portion extending radially inward from the sleeve and having a forward surface restrained against forward movement relative to the shaft.

Abstract: A method for processing a seal for a gas turbine engine includes providing a carbon fiber preform, densifying the carbon fiber preform with a carbon matrix to form a carbon/carbon composite ring, and forming a seal by cutting the carbon/carbon composite ring to form at least one seam at which opposed ends of the carbon/carbon composite ring meet.

Abstract: A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

Abstract: An actuation structure changes the orientation of a vane airfoil. A spindle is fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extends through a bore in the housing. A mount is between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that it is part of the housing. A bushing is secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve. A seal is radially outward of the bushing with the seal providing an air seal between the spindle and the bore. A gas turbine engine is also disclosed.

Abstract: An actuation structure changes the orientation of a vane airfoil. A spindle is fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extends through a bore in the housing. A mount is between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that it is part of the housing. A bushing is secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve. A seal is radially outward of the bushing with the seal providing an air seal between the spindle and the bore. A gas turbine engine is also disclosed.

Abstract: A machine comprising a rotor having: an inner member; an outer member encircling the inner member; and a groove in one of the inner member and the outer member. The groove has a first side wall, a second side wall and a base. A split ring seal is accommodated in the groove and contacts a surface of the other of the inner member and the outer member The first side wall has a plurality of open radial first channels and the second side wall has a plurality of open radial second channels.

Abstract: A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

Abstract: A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

Abstract: An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

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: An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

Abstract: An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

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: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

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.