Rotor assembly with internal vanes
View Patent ↗A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. 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 axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis. The vanes include a first vane that is integral with the first rotor disk and projects axially to the second rotor disk.
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; and
a plurality of vanes arranged circumferentially around the rotational axis, the plurality of vanes comprising a first vane and a second vane circumferentially neighboring the first vane, the first vane integral with the first rotor disk and projecting axially to the second rotor disk, and the second vane integral with the second rotor disk and projecting axially to the first rotor disk.
2. The rotor assembly of claim 1 , wherein
the first vane extends longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane; and
at least a portion of the centerline is straight.
3. The rotor assembly of claim 1 , wherein
the first vane extends longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane; and
at least a portion of the centerline is curved.
4. The rotor assembly of claim 1 , wherein
the first vane extends longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane; and
at least a portion of the centerline is perpendicular to the rotational axis.
5. The rotor assembly of claim 1 , wherein
the first vane extends longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane; and
at least a portion of the centerline is angularly offset from the rotational axis.
6. 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 vanes arranged circumferentially around the rotational axis, the plurality of vanes comprising a first vane and a second vane circumferentially neighboring the first vane, the first vane integral with the first rotor disk and projecting axially to the second rotor disk, and the second vane integral with the first rotor disk and projecting axially to the second rotor disk.
7. The rotor assembly of claim 1 , wherein the plurality of vanes are configured to pump fluid in a radial outward direction in a passage, axially between the first rotor disk and the second rotor disk, towards the plurality of rotor blades.
8. The rotor assembly of claim 1 , wherein a passage defined circumferentially between a circumferentially neighboring pair of the plurality of vanes is fluidly coupled with a passage within a first of the plurality of rotor blades.
9. The rotor assembly of claim 1 , wherein
the first rotor disk includes a hub, a web and a rim;
the web extends radially out from the hub to the rim; and
the first vane projects axially out from and is integral with the web.
10. The rotor assembly of claim 1 , further comprising a plurality of disk mounts connecting the first rotor disk and the second rotor disk together.
11. The rotor assembly of claim 10 , wherein a first of the plurality of disk mounts is disposed circumferentially between a circumferentially neighboring pair of the plurality of vanes.
12. The rotor assembly of claim 1 , wherein the plurality of rotor blades comprise a first rotor blade with a dovetail attachment.
13. The rotor assembly of claim 12 , wherein the dovetail attachment projects axially along the rotational axis into a first pocket in the first rotor disk.
14. The rotor assembly of claim 13 , wherein the dovetail attachment projects axially along the rotational axis into a second pocket in the second rotor disk.
15. The rotor assembly of claim 12 , wherein a portion of the first rotor disk extends circumferentially across and thereby circumferentially covers the dovetail attachment.
16. The rotor assembly of claim 1 , wherein the plurality of rotor blades comprise a first rotor blade, and the first rotor blade comprises ceramic.
17. The rotor assembly of claim 6 , wherein
the first vane extends longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane; and
an entirety of the centerline is non-straight.