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EP-3851638-B1 - ROTOR ASSEMBLY FOR A GAS TURBINE ENGINE

EP3851638B1EP 3851638 B1EP3851638 B1EP 3851638B1EP-3851638-B1

Inventors

  • ROBERGE, GARY D.

Dates

Publication Date
20260506
Application Date
20210118

Claims (15)

  1. A rotor assembly for a gas turbine engine, comprising: a first rotor disk (180A) configured to rotate about a rotational axis (102); a second rotor disk (180B) configured to rotate about the rotational axis (102); a plurality of rotor blades (104) arranged circumferentially around the rotational axis (102), each of the plurality of rotor blades (104) axially between and mounted to the first rotor disk (180A) and the second rotor disk (180B); and a plurality of vanes (234) arranged circumferentially around the rotational axis (102), the plurality of vanes (234) comprising a first vane (234) that is integral with the first rotor disk (180A) and projects axially to the second rotor disk; wherein the plurality of vanes (234) further includes a second vane (234) circumferentially neighboring the first vane (234); and characterised in that the second vane (234) is integral with the second rotor disk (180B) and projects axially to the first rotor disk (180A).
  2. The rotor assembly of claim 1, wherein: the first vane (234) extends longitudinally along a centerline (240) from a radial inner end (242) of the first vane (234) to a radial outer end (244) of the first vane (234); and at least a portion of the centerline (240) is straight.
  3. The rotor assembly of claim 1 or 2, wherein: the first vane (234) extends longitudinally along a or the centerline (240) from a or the radial inner end (242) of the first vane (234) to a or the radial outer end (244) of the first vane (234); and at least a portion of the centerline (240) is curved.
  4. The rotor assembly of claim 1, 2 or 3, wherein: the first vane (234) extends longitudinally along a or the centerline (240) from a or the radial inner end (242) of the first vane (234) to a or the radial outer end (244) of the first vane (234); and at least a portion of the centerline (240) is perpendicular to the rotational axis (102) and/or at least a portion of the centerline (240) is angularly offset from the rotational axis (102).
  5. The rotor assembly of any preceding claim, wherein: the plurality of vanes (234) are configured to pump fluid in a radial outward direction in a passage (238) axially between the first rotor disk (180A) and the second rotor disk (180B) towards the plurality of rotor blades (104); and/or a or the passage (238) is defined circumferentially between a circumferentially neighboring pair of the plurality of vanes (234), and is fluidly coupled with a passage (236) within a first of the plurality of rotor blades (104).
  6. The rotor assembly of any preceding claim, wherein: the first rotor disk (180A) includes a hub (182A), a web (184A) and a rim (186A), the web (184A) extending radially out from the hub (182A) to the rim (186A); and the first vane (234) projects axially out from and is integral with the web (184A) of the first rotor disk (180A).
  7. The rotor assembly of claim 6, wherein: the second rotor disk (180B) includes a hub (182B), a web (184B) and a rim (186B), the web (184B) extending radially out from the hub (182B) to the rim (186B); the second vane (234) projects axially out from and is integral with the web (184B) of the second rotor disk (180B); and the first vane (234) axially engages the web (184B) of the second rotor disk (180B), and the second vane (234) axially engages the web (184A) of the first rotor disk (180A).
  8. The rotor assembly of any preceding claim, further comprising a plurality of disk mounts (188) connecting the first rotor disk (180A) and the second rotor disk (180B) together.
  9. The rotor assembly of claim 8, wherein a first of the plurality of disk mounts (188) is disposed circumferentially between a circumferentially neighboring pair of the plurality of vanes (234).
  10. The rotor assembly of any preceding claim, wherein the plurality of rotor blades (104) comprise a first rotor blade (104) with a dovetail attachment (116).
  11. The rotor assembly of claim 10, wherein: the dovetail attachment (116) projects axially along the rotational axis (102) into a first pocket (196A) in the first rotor disk (180A); and/or the dovetail attachment (116) projects axially along the rotational axis (102) into a second pocket (196B) in the second rotor disk (180B).
  12. The rotor assembly of claim 10 or 11, wherein a portion (186A) of the first rotor disk (180A) extends circumferentially across and thereby circumferentially covers the dovetail attachment (116).
  13. The rotor assembly of any preceding claim, wherein the plurality of rotor blades (104) comprise a or the first rotor blade (104), and the first rotor blade (104) comprises ceramic.
  14. The rotor assembly of any preceding claim, wherein the first vane (234) axially engages the second rotor disk (180B).
  15. The rotor assembly of any preceding claim, wherein at least the first vane (234) and the first rotor disk (180A) are formed together in a monolithic body.

Description

BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to rotational equipment and, more particularly, to rotor blades and associated rotor assemblies. The present invention relates to a rotor assembly for a gas turbine engine. 2. Background Information Gas turbine engine designers are continually being challenged to provide gas turbine engines with improved performance at reduced weights. One design metric being pushed to provide improved performance is increasing turbine rotational speed. As the turbine rotational speed is increased, however, rotor disk bores also increase in size in order to accommodate increasing centrifugal loading. This can result in bore widths that are so large that heat treating the center of a bore may become challenging. Rotor disk sizing may also be impacted by rim pull which includes the mass of airfoils and interrupted (circumferentially discontinuous) features created by axially or angled airfoil attachment features. Current turbine design standard includes separate airfoils that are mechanically attached to a disk using single or multiple tooth attachments; e.g., fir tree attachments. Provision of these attachments result in a live rim (full hoop or circumferentially continuous rim) that transfers radial loads from the airfoils as well as segmented portions of the disk between airfoil attachments. In addition, cover plates are typically employed to reduce leakage through attachments from one side of the disk to the other. US2641440A, US2019/338657A1 and US2401826A disclose prior art rotor assemblies. There is a need in the art for improved rotor blades and rotor assemblies with reduced weights and/or with improved cooling schemes. This includes rotor blades made using high temperature composites such as ceramic matrix composite (CMC) materials. It should be recognized that designing for such composite airfoils may require new rotor architectures to accommodate and exploit the unique capabilities and limitations of composite materials. SUMMARY OF THE DISCLOSURE In an aspect of the invention, a rotor assembly is provided for a gas turbine engine according to claim 1. The following optional features may be applied to any of the above aspects. At least the first vane and the first rotor disk or the second rotor disk may be formed together in a monolithic body. The first vane may extend longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane. At least a portion or an entirety of the centerline may be straight. The first vane may extend longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane. At least a portion or an entirety of the centerline may be curved. The first vane may extend longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane. At least a portion or an entirety of the centerline may be perpendicular to the rotational axis. The first vane may extend longitudinally along a centerline from a radial inner end of the first vane to a radial outer end of the first vane. At least a portion or an entirety of the centerline may be angularly offset from the rotational axis. The vanes may be 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. A passage may be defined circumferentially between a circumferentially neighboring pair of the vanes, which passage may be fluidly coupled with a passage within a first of the plurality of rotor blades. The first rotor disk may include a hub, a web and a rim. The web may extend radially out from the hub to the rim. The first vane may project axially out from and may be integral with the web. The rotor assembly may include a plurality of disk mounts connecting the first rotor disk and the second rotor disk together. A first of the disk mounts may be disposed circumferentially between a circumferentially neighboring pair of the plurality of vanes. The rotor blades may include a first rotor blade with a dovetail attachment. The dovetail attachment may project axially along the rotational axis into a first pocket in the first rotor disk. The dovetail attachment may project axially along the rotational axis into a second pocket in the second rotor disk. A portion of the first rotor disk may extend circumferentially across and thereby circumferentially cover the dovetail attachment. The rotor blades may include a first rotor blade, and the first rotor blade may be configured from or otherwise include ceramic. The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof. The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings. BRIEF DESCRIPTION OF THE DR