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 gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod therethrough. First and second bore annular flowpaths are radially located between first and second stage disk bores and tie rod. A means for increased cooling and/or heating in second stage disk bore is axially located within second stage disk bore. The means may include an airflow accelerator such as one or more annular ribs on the tie rod. A bore annular cross-sectional flow area between the second stage disk hub and the ribs may be substantially smaller than between the second stage disk hub and the tie rod. An axially unobstructed inlet into the second bore annular flowpath allows fully axially flowing and axially unobstructed flowing of second stage bore cooling air into inlet.