Multi-disk bladed rotor assembly for rotational equipment

1. A rotor assembly for a gas turbine engine, comprising:

a first rotor disk configured to rotate about a rotational axis;

a second rotor disk configured to rotate about the rotational axis;

a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades axially between and mounted to the first rotor disk and the second rotor disk;

a plurality of disk mounts connecting the first rotor disk and the second rotor disk together, the plurality of disk mounts comprising a first disk mount, the first disk mount integral with the first rotor disk, and the first disk mount projecting axially through the second rotor disk; and

a retention ring extending circumferentially through a slot in the first disk mount.

2. The rotor assembly of claim 1 , wherein the first disk mount is cantilevered from the first rotor disk.

3. The rotor assembly of claim 1 , wherein the retention ring further extends circumferentially through a slot in the second rotor disk.

4. The rotor assembly of claim 3 , wherein

the plurality of disk mounts further include a second disk mount that circumferentially neighbors the first disk mount;

the second disk mount is integral with the first rotor disk;

the second disk mount projects axially through the second rotor disk; and

the retention ring extends circumferentially through a slot in the second disk mount.

5. The rotor assembly of claim 3 , further comprising a second retention ring, wherein

the plurality of disk mounts further include a second disk mount that circumferentially neighbors the first disk mount;

the second disk mount is integral with the second rotor disk;

the second disk mount projects axially through the first rotor disk;

the second retention ring extends circumferentially through a slot in the second disk mount; and

the second retention ring extends circumferentially through a slot in the first rotor disk.

6. The rotor assembly of claim 1 , wherein

the plurality of disk mounts further include a second disk mount that circumferentially neighbors the first disk mount;

the second disk mount is integral with the first rotor disk; and

the second disk mount projects axially through the second rotor disk.

7. The rotor assembly of claim 1 , wherein

the plurality of disk mounts further include a second disk mount that circumferentially neighbors the first disk mount;

the second disk mount is integral with the second rotor disk; and

the second disk mount projects axially through the first rotor disk.

8. The rotor assembly of claim 1 , wherein the plurality of rotor blades comprise a first rotor blade with a dovetail attachment.

9. The rotor assembly of claim 8 , wherein the dovetail attachment has a flared cross-sectional geometry when viewed in a plane perpendicular to the rotational axis.

10. The rotor assembly of claim 8 , wherein the dovetail attachment projects axially along the rotational axis into a first pocket in the first rotor disk.

11. The rotor assembly of claim 10 , wherein the dovetail attachment projects axially along the rotational axis into a second pocket in the second rotor disk.

12. The rotor assembly of claim 8 , wherein a portion of the first rotor disk extends circumferentially across and thereby circumferentially covers the dovetail attachment.

13. The rotor assembly of claim 1 , wherein

the plurality of rotor blades comprise a first rotor blade; and

the first rotor blade comprises ceramic.

14. The rotor assembly of claim 1 , wherein

the plurality of rotor blades comprise a first rotor blade; and

the first rotor blade comprises metal.

15. The rotor assembly of claim 1 , wherein

the plurality of rotor blades comprise a first rotor blade; and

the first rotor blade comprises intermetallic material.

16. A rotor assembly for a gas turbine engine, comprising:

a first rotor disk configured to rotate about a rotational axis;

a second rotor disk configured to rotate about the rotational axis;

a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades axially between and mounted to the first rotor disk and the second rotor disk; and

a plurality of disk mounts connecting the first rotor disk and the second rotor disk together, the plurality of disk mounts comprising a first disk mount, the first disk mount fixedly connected to the first rotor disk, and the first disk mount removably attached to the second rotor disk; and

a retention ring extending circumferentially through a slot in the first disk mount.

17. The rotor assembly of claim 16 , wherein

the first disk mount is cantilevered from the first rotor disk; and

the first disk mount projects axially through an aperture in the second rotor disk.

18. A rotor assembly for a gas turbine engine, comprising:

a first rotor disk configured to rotate about a rotational axis, the first rotor disk comprising a first disk mount;

a second rotor disk configured to rotate about the rotational axis, the second rotor disk comprising a second disk mount;

a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades axially between and mounted to the first rotor disk and the second rotor disk, the first disk mount removably mounted to the second rotor disk, and the second disk mount removably mounted to the first rotor disk; and

a first retention ring and a second retention ring;

the first disk mount projecting through the second rotor disk and secured to the second rotor disk with the first retention ring; and

the second disk mount projecting through the first rotor disk and secured to the first rotor disk with the second retention ring.