Vane with collar

Patent metadata

Field	Value
Publication number	US-11242762-B2
Application number	US-201916690989-A
Country	US
Kind code	B2
Filing date	Nov 21, 2019
Priority date	Nov 21, 2019
Publication date	Feb 8, 2022
Grant date	Feb 8, 2022

Abstract

An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.

First claim

What is claimed is:

1. An airfoil piece, comprising:
a first vane platform;
a second vane platform; and
a hollow airfoil section joining the first vane platform and the second vane platform, the hollow airfoil section including a collar projection extending past the first vane platform, the collar projection including at least one radial tab projecting therefrom, wherein the hollow airfoil includes first and second cavities separated by a divider, and wherein a second radial tab of the at least one radial tab is at a circumferential location of collar projection that corresponds to a location of the divider.

2. The airfoil piece of claim 1 , wherein the collar projection has a first radial extent and the at least one radial tab has a second radial extent, and a ratio of the first radial extent to the second radial extent is between 1:1 and 1:5.

3. The airfoil piece of claim 1 , wherein the at least one radial tab comprises a plurality of radial tabs, and the plurality of radial tabs have a cumulative circumferential extent.

4. The airfoil piece of claim 3 , wherein the cumulative circumferential extent is between and 20 and 40% of a circumferential extent of the collar projection.

5. The airfoil piece of claim 1 , wherein the airfoil section and collar projection include at least one continuous ceramic matrix composite ply.

6. The airfoil piece of claim 1 , wherein the hollow airfoil section is configured to receive a metallic spar piece therein.

7. An airfoil assembly, comprising:
a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, the hollow airfoil section including a collar projection extending past the first vane platform, the collar projection including at least one radial tab projecting therefrom;
a spar piece defining a spar platform and a spar extending from the spar platform into the hollow airfoil section, the spar piece including a radial pocket defined by first and second opposed faces, the radial pocket configured to receive the collar projection.

8. The airfoil assembly of claim 7 , wherein the collar projection has a first radial extent and the at least one radial tab has a second radial extent, and a ratio of the first radial extent to the second radial extent is between 1:1 and 1:5.

9. The airfoil assembly of claim 7 , wherein the at least one radial tab comprises a plurality of radial tabs, and the plurality of radial tabs have a cumulative circumferential extent.

10. The airfoil assembly of claim 9 , wherein the cumulative circumferential extent is between 20 and 40% of a circumferential extent of the collar projection.

11. The airfoil assembly of claim 7 , wherein the airfoil section and collar projection include at least one continuous ceramic matrix composite ply.

12. The airfoil assembly of claim 7 , wherein the collar projection is a radially outer collar projection.

13. The airfoil assembly of claim 7 , wherein the spar piece is metallic and the airfoil piece is ceramic matrix composite.

14. The airfoil assembly of claim 7 , wherein the spar piece is configured to transfer structural loads from the airfoil piece to a support structure via the collar projection.

15. The airfoil assembly of claim 7 , wherein the radial pocket includes at least one mating feature configured to mate with the at least one radial tab.

16. A method of assembling a vane, comprising:
inserting a spar piece into a cavity of a hollow airfoil section of an airfoil piece, the airfoil piece having a first vane platform, a second vane platform, the hollow airfoil section joining the first vane platform and the second vane platform, the hollow airfoil section including a collar projection extending past the first vane platform, the collar projection including at least one radial tab projecting therefrom, wherein the spar piece is metallic and the airfoil piece is ceramic matrix composite.

17. The method of claim 16 , wherein the inserting includes aligning a pocket in a spar platform of the spar piece with the collar projection.

18. The method of claim 17 , wherein the pocket includes at least one mating feature configured to mate with the at least one radial tab.

19. An airfoil piece, comprising:
a first vane platform;
a second vane platform; and
a hollow airfoil section joining the first vane platform and the second vane platform, the hollow airfoil section including a collar projection extending past the first vane platform, the collar projection including at least one radial tab projecting therefrom, wherein the hollow airfoil section is configured to receive a metallic spar piece therein.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Burdette Alyson T
• Dube Bryan P
• Patel Rutva A
• Broulidakis Nicholas

Classifications

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title