Abstract: A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

Abstract: Compliant bellow seal may be axially disposed between first and second cooling plates bounding first and second cooling passages between cooling plates and first and second stage disks in turbine. Bellow seal includes two or more convolutions with oppositely facing forward and aft sealing surfaces, which may be flat, on forward and aft annular sealing walls and cylindrical annular outer and inner contact and sealing surfaces on and facing radially outwardly or inwardly from one of the convolutions. A snake bellow seal embodiment may have at least two of the convolutions being full convolutions of unequal width and a forwardmost partial convolution including the sealing wall. Bellow seal may allow turbine cooling flow from an inter-stage radial face spline to flow through inner openings of second cooling passage and block first stage disk cooling air from flowing through inner openings of first cooling passage.

Abstract: Compliant bellow seal may be axially disposed between first and second cooling plates bounding first and second cooling passages between cooling plates and first and second stage disks in turbine. Bellow seal includes two or more convolutions with oppositely facing forward and aft sealing surfaces, which may be flat, on forward and aft annular sealing walls and cylindrical annular outer and inner contact and sealing surfaces on and facing radially outwardly or inwardly from one of the convolutions. A snake bellow seal embodiment may have at least two of the convolutions being full convolutions of unequal width and a forwardmost partial convolution including the sealing wall. Bellow seal may allow turbine cooling flow from an inter-stage radial face spline to flow through inner openings of second cooling passage and block first stage disk cooling air from flowing through inner openings of first cooling passage.

Abstract: A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises providing a rotor assembly including a rotor shaft and a rotor disk that includes a radially outer rim, a radially inner hub, and an integral web extending therebetween, wherein the rotor assembly is rotatable about an axis of rotation extending through the rotor shaft, and coupling a disk retainer including at least one discharge tube to the rotor disk wherein the discharge tube extends outwardly from the disk retainer for pumping the air to a higher pressure before discharging cooling fluid therefrom in a direction that is substantially perpendicular with respect to the axis of rotation.