Multi-disk bladed rotor assembly for rotational equipment
A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk and a plurality of rotor blades. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. The first rotor blade includes an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion of the first rotor disk extends circumferentially across and covers the attachment.
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; and
a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades mounted to the first rotor disk and to the second rotor disk, and the plurality of rotor blades comprising a first rotor blade;
the first rotor blade comprising an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk, and the attachment having a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis; and
a portion of the first rotor disk extending circumferentially across and thereby circumferentially covering the attachment;
wherein the first rotor blade further includes an airfoil, a platform and a neck;
wherein the airfoil is connected to and projects radially out from the platform;
wherein the neck extends radially between and connects the platform and the attachment;
wherein a first end portion of the attachment projects axially along the rotational axis away from the neck and into the first pocket;
wherein a second end portion of the attachment projects axially along the rotational axis away from the neck and into the second pocket; and
wherein a second portion of the first rotor disk projects axially into a gap that is axially adjacent the neck and extends radially between the first end portion of the attachment and the platform.
2. The rotor assembly of claim 1 , wherein an axial end of the first pocket is axially enclosed by the portion of the first rotor disk.
3. The rotor assembly of claim 1 , wherein the first pocket is radially enclosed within the first rotor disk.
4. The rotor assembly of claim 1 , wherein the first pocket is formed by a circumferentially uninterrupted annular rim of the first rotor disk.
5. The rotor assembly of claim 1 , wherein the first pocket is formed by a circumferentially interrupted annular rim of the first rotor disk.
6. The rotor assembly of claim 1 , wherein
the plurality of rotor blades further comprise a second rotor blade;
the second rotor blade comprises a second attachment projecting axially along the rotational axis into a third pocket in the first rotor disk and a fourth pocket in the second rotor disk; and
a second portion of the first rotor disk extends circumferentially across and thereby circumferentially covers the second attachment.
7. The rotor assembly of claim 6 , wherein the second rotor blade circumferentially neighbors the first rotor blade.
8. The rotor assembly of claim 1 , wherein
the plurality of rotor blades further comprise a second rotor blade;
the second rotor blade comprises a second attachment projecting axially along the rotational axis into a third pocket in the first rotor disk and a fourth pocket in the second rotor disk; and
the first rotor disk has a slot that radially and circumferentially overlaps the second attachment.
9. The rotor assembly of claim 8 , wherein the second rotor blade circumferentially neighbors the first rotor blade.
10. The rotor assembly of claim 1 , wherein a portion of the second rotor disk extends circumferentially across and thereby circumferentially covers the attachment.
11. The rotor assembly of claim 1 , wherein the first rotor blade comprises ceramic.
12. The rotor assembly of claim 1 , wherein the first rotor blade comprises metal.
13. The rotor assembly of claim 1 , wherein the first rotor blade comprises intermetallic material.
14. The rotor assembly of claim 1 , further comprising a plurality of disk mounts connecting the first rotor disk and the second rotor disk together.
15. The rotor assembly of claim 1 , further comprising a reinforcing ring located axially between and rotatable with the first rotor disk and the second rotor disk.
16. The rotor assembly of claim 1 , further comprising at least one of
a first reinforcing ring connected to an exterior of the first rotor disk; or
a second reinforcing ring connected to an exterior of the second rotor disk.
17. 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; and
a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades mounted to the first rotor disk and to the second rotor disk, and the plurality of rotor blades comprising a first rotor blade;
the first rotor blade comprising an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk, and the attachment having a flared cross-sectional geometry when viewed in a plane perpendicular to the rotational axis;
a portion of the first rotor disk extending circumferentially across and thereby circumferentially covering the attachment;
wherein the first rotor blade further includes an airfoil, a platform and a neck;
wherein the airfoil is connected to and projects radially out from the platform;
wherein the neck extends radially between and connects the platform and the attachment;
wherein a first end portion of the attachment projects axially along the rotational axis away from the neck and into the first pocket;
wherein a second end portion of the attachment projects axially along the rotational axis away from the neck and into the second pocket; and
wherein a second portion of the first rotor disk projects axially into a gap that is axially adjacent the neck and extends radially between the first end portion of the attachment and the platform.
18. 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; and
a plurality of rotor blades arranged circumferentially around the rotational axis, each of the plurality of rotor blades mounted to the first rotor disk and to the second rotor disk, and the plurality of rotor blades comprising a first rotor blade;
the first rotor blade comprising an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk, and the attachment having a flared cross-sectional geometry when viewed in a plane perpendicular to the rotational axis;
wherein a portion of the first rotor disk extends completely circumferentially across the attachment, and the portion of the first rotor disk radially encloses the first pocket within the first rotor disk.