Vane arc segment load path
A vane arc segment includes an airfoil piece that defines a first platform and an airfoil section that extends from the first platform. The first platform defines a radial flange that extends along at least a portion of a circumferential mate face of the first platform. The airfoil piece is formed of a fiber-reinforced composite that has fibers that are continuous between the airfoil section and the first platform. The airfoil section carries a second platform radially opposite the first platform. The second platform includes a through-hole, and the airfoil section extends through the through-hole.
1. A vane arc segment comprising:
an airfoil piece defining a first platform and an airfoil section extending from the first platform, the first platform defining a radial flange extending along at least a portion of a circumferential mate face of the first platform, and a circumferential face of the radial flange being flush with the circumferential mate face of the first platform, the airfoil piece being formed of a fiber-reinforced composite having fibers that are continuous between the airfoil section and the first platform; and
a second platform carried on the airfoil section radially opposite the first platform, the second platform including a through-hole, the airfoil section extending through the through-hole.
2. The vane arc segment as recited in claim 1 , wherein the fiber-reinforced composite has a braided fiber structure.
3. The vane arc segment as recited in claim 1 , wherein the second platform is also formed of a fiber-reinforced composite, and the fiber-reinforced composite of the second platform includes stacked fiber plies.
4. The vane arc segment as recited in claim 3 , wherein the airfoil section excludes any fiber plies of the fiber-reinforced composite of the second platform.
5. The vane arc segment as recited in claim 1 , wherein the through-hole has a shape that corresponds to the airfoil section.
6. The vane arc segment as recited in claim 1 , wherein the fibers of the fiber-reinforced composite of the first platform extend in the radial flange.
7. The vane arc segment as recited in claim 1 , wherein the airfoil section is hollow.
8. The vane arc segment as recited in claim 1 , wherein there is a non-fibrous interface between the airfoil section and the second platform.
9. The vane arc segment as recited in claim 8 , wherein the non-fibrous interface is ceramic.
10. The vane arc segment as recited in claim 1 , wherein the flange runs along a length of at least 50% of the circumferential mate face between forward and axial face of the first platform.
11. A gas turbine engine comprising:
first and second support structures;
vane arc segments supported between the first and second support structures, each said vane arc segment including
an airfoil piece defining a first platform and an airfoil section extending from the first platform, the first platform defining a radial flange extending along at least a portion of a circumferential mate face of the first platform, and a circumferential face of the flange is flush with the circumferential mate face of the first platform, and
a second platform carried on the airfoil section radially opposite the first platform, the second platform including a through-hole, the airfoil section extending through the through-hole, and
a load path from the first support structure extending through the airfoil section, the first platform, and the radial flange to the second support structure, the second platform being non-load bearing with regard to the load path.
12. The engine as recited in claim 11 , wherein the airfoil piece is formed of a fiber-reinforced composite having fibers that are continuous between the airfoil section and the first platform.
13. The engine as recited in claim 12 , wherein the fiber-reinforced composite has a braided fiber structure.
14. The engine as recited in claim 12 , wherein the second platform is also formed of a fiber-reinforced composite, and the fiber-reinforced composite of the second platform includes stacked fiber plies.
15. The engine as recited in claim 14 , wherein the airfoil section excludes any fiber plies of the fiber-reinforced composite of the second platform.
16. The engine as recited in claim 12 , wherein the fibers of the fiber-reinforced composite of the first platform extend in the radial flange.
17. The engine as recited in claim 11 , wherein there is a non-fibrous interface between the airfoil section and the second platform.
18. The engine as recited in claim 17 , wherein the non-fibrous interface is ceramic.
19. The vane arc segment as recited in claim 1 , wherein the fibers of the fiber-reinforced composite extend in the airfoil section, then turn from the airfoil section into the first platform, and then turn from the first platform into the radial flange.
20. The vane arc segment as recited in claim 1 , wherein the radial flange has a radial face that has a curved profile.
21. The vane arc segment as recited in claim 20 , wherein the curved profile is a cylindrical surface segment.