Piston ring shuttle carrier

1. A rotating assembly of a gas turbine engine, comprising:

a first rotating component;

a second rotating component disposed radially outboard of the first rotating component, relative to an engine central longitudinal axis; and

a seal assembly configured to seal between the first rotating component and the second rotating component, the seal assembly including:

a shuttle disposed on a radial outer surface of the first component and freely axially movable along the radial outer surface; and

a piston ring seal retained in the shuttle and engaged with the first second rotating component;

a first axial stop and a second axial stop at the first rotating component between which the shuttle is axially retained

wherein the shuttle includes:

a shuttle pocket into which the piston ring is installed and is located axially between the first axial stop and the second axial stop;

at least one shuttle arm extending axially from the shuttle pocket and axially overlapping at least one of the first axial stop or the second axially stop;

wherein axial motion of the first second rotating component relative to the first rotating component during operation of the gas turbine engine urges movement of the shuttle along the radial outer surface of the first rotating component, while the position of the piston ring seal remains stationary relative to the second rotating component.

2. The rotating assembly of claim 1 , wherein an axial distance between the first axial stop and the second axial stop is greater than an axial length of the shuttle located therebetween.

3. The rotating assembly of claim 1 , wherein the first axial stop is a shoulder formed on the first rotating component, and the second axial stop is a retainer secured to the first rotating component.

4. The rotating assembly of claim 1 , wherein the shuttle extends circumferentially unbroken around the first rotating component.

5. The rotating assembly of claim 1 wherein the piston ring seal has a split ring configuration.

6. A rotor assembly of a gas turbine engine, comprising:

a plurality of rotors arranged along an engine central longitudinal axis between a forward rotor hub and an aft rotor hub;

a tie shaft located radially inboard of the plurality of rotors and rotatable therewith about the engine central longitudinal axis; and

a seal assembly configured to seal between a rotor of the plurality of rotors and the tie shaft, the seal assembly including:

a shuttle disposed on a radial outer surface of the tie shaft and freely axially movable along the radial outer surface; and

a piston ring seal retained in the shuttle and engaged with the rotor;

a first axial stop and a second axial stop at the tie shaft between which the shuttle is axially retained

wherein the shuttle includes:

a shuttle pocket into which the piston ring is installed and is located axially between the first axial stop and the second axial stop;

at least one shuttle arm extending axially from the shuttle pocket and axially overlapping at least one of the first axial stop or the second axially stop;

wherein axial motion of the rotor relative to the tie shaft during operation of the gas turbine engine urges movement of the shuttle along the radial outer surface of the tie shaft, while the position of the piston ring seal remains stationary relative to the rotor.

7. The rotor assembly of claim 6 , wherein an axial distance between the first axial stop and the second axial stop is greater than an axial length of the shuttle located therebetween.

8. The rotor assembly of claim 6 , wherein the first axial stop is a shoulder formed on the tie shaft, and the second axial stop is a retainer secured to the tie shaft.

9. The rotor assembly of claim 6 , wherein the shuttle extends circumferentially unbroken around the tie shaft.

10. The rotor assembly of claim 6 , wherein the piston ring seal has a split ring configuration.

11. A gas turbine engine, comprising:

a combustor; and

a rotor assembly operably connected to the combustor, including:

a plurality of rotors arranged along an engine central longitudinal axis between a forward rotor hub and an aft rotor hub;

a tie shaft located radially inboard of the plurality of rotors and rotatable therewith about the engine central longitudinal axis; and

a seal assembly configured to seal between a rotor of the plurality of rotors and the ties shaft, the seal assembly including:

a shuttle disposed on a radial outer surface of the tie shaft and freely axially movable along the radial outer surface; and

a piston ring seal retained in the shuttle and engaged with the rotor;

a first axial stop and a second axial stop at the tie shaft between which the shuttle is axially retained

wherein the shuttle includes:

a shuttle pocket into which the piston ring is installed and is located axially between the first axial stop and the second axial stop;

at least one shuttle arm extending axially from the shuttle pocket and axially overlapping at least one of the first axial stop or the second axially stop;

wherein axial motion of the rotor relative to the tie shaft urges movement of the shuttle along the radial outer surface of the tie shaft, while the position of the piston ring seal remains stationary relative to the rotor.

12. The gas turbine engine of claim 11 , wherein an axial distance between the first axial stop and the second axial stop is greater than an axial length of the shuttle located therebetween.

13. The gas turbine engine of claim 11 , wherein the first axial stop is a shoulder formed on the tie shaft, and the second axial stop is a retainer secured to the tie shaft.

14. The gas turbine engine of claim 11 , wherein the shuttle extends circumferentially unbroken around the tie shaft.

15. The gas turbine engine of claim 11 , wherein the piston ring seal has a split ring configuration.