CMC vane mate face flange
A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.
1. A vane arc segment comprising:
a continuous airfoil piece for arrangement in a gas turbine engine about a central engine axis, the continuous airfoil piece defining first and second platforms and an airfoil section extending between the first and second platforms,
the airfoil section having a pressure side and a suction side,
the first platform defining axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side, the axially-sloped suction and pressure side circumferential mate faces lying in planes, the planes forming an angle of at least 45° relative to the central engine axis,
the flange extending along at least a portion of the axially-sloped suction side circumferential mate face, and the flange being flush with the axially-sloped suction side circumferential mate face.
2. The vane arc segment as recited in claim 1 , wherein the airfoil piece is formed of a ceramic matrix composite.
3. The vane arc segment as recited in claim 2 , wherein the ceramic matrix composite has a plurality of fiber plies that are continuous through the flange and first platform, the airfoil section, and the second platform.
4. The vane arc segment as recited in claim 3 , wherein the flange bears radial, tangential, and axial aerodynamic load transmissions of the airfoil piece.
5. The vane arc segment as recited in claim 1 , wherein the flange is coextensive with the axially-sloped suction side circumferential mate face.
6. The vane arc segment as recited in claim 1 , wherein the flange includes a radial face that has a curved profile.
7. The vane arc segment as recited in claim 6 , wherein the curved profile is a cylindrical surface segment.
8. The vane arc segment as recited in claim 1 , wherein the flange is a sole flange on the non-gaspath side.
9. The vane arc segment as recited in claim 1 , wherein the flange is a sole flange on the non-gaspath side that bears radial, tangential, and axial aerodynamic load transmissions of the airfoil piece.
10. The vane arc segment as recited in claim 9 , wherein the flange is elongated in a length direction along the axially-sloped suction side circumferential mate face, and the length direction is substantially perpendicular to a total aerodynamic load vector of the airfoil piece.
11. The vane arc segment as recited in claim 10 , wherein the airfoil piece is formed of a ceramic matrix composite.
12. A vane arc segment comprising:
a continuous airfoil piece for arrangement in a gas turbine engine about a central engine axis, the continuous airfoil piece defining first and second platforms and an airfoil section extending between the first and second platforms,
the airfoil section having a pressure side and a suction side,
the first platform defining axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side,
the flange having faces that bear radial, tangential, and axial aerodynamic load transmissions of the airfoil piece, wherein one of the faces of the flange is a radial face, and the radial face has a curved profile that is a cylindrical surface segment of a reference cylinder having a main axis that is co-linear with the central engine axis.
13. The vane arc segment as recited in claim 12 , wherein the flange is elongated along a flange axis, and the flange axis is substantially perpendicular to a total aerodynamic load vector of the airfoil piece.
14. The vane arc segment as recited in claim 12 , wherein the airfoil piece is formed of a ceramic matrix composite that has a plurality of fiber plies that are continuous through the flange and first platform, the airfoil section, and the second platform.
15. The vane arc segment as recited in claim 12 , wherein the axially-sloped suction and pressure side circumferential mate faces form an angle of at least 45° relative to an axial direction of the vane arc segment.
16. The vane arc segment as recited in claim 12 , wherein the flange is coextensive with the axially-sloped suction side circumferential mate face, and the flange is flush with the axially-sloped suction side circumferential mate face.
17. A vane arc segment comprising:
an airfoil piece defining first and second platforms and an airfoil section extending between the first and second platforms,
the airfoil section having a pressure side and a suction side,
the first platform defining suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side, the flange being a sole flange on the non-gaspath side, the flange having one or more faces that bear aerodynamic load transmissions of the airfoil piece, the flange being elongated along a flange axis, and the flange axis being substantially perpendicular to a total aerodynamic load vector of the airfoil piece, and
the airfoil piece being formed of a ceramic matrix composite having a plurality of fiber plies that are continuous through the flange and first platform, the airfoil section, and the second platform.
18. The vane arc segment as recited in claim 17 , wherein the ceramic matrix composite contains a SiC matrix and SiC fibers.
19. The vane arc segment as recited in claim 18 , wherein one of the faces of the flange is a radial face, the radial face has a curved profile, and the curved profile is a cylindrical surface segment.
20. The vane arc segment as recited in claim 19 , wherein the suction and pressure side circumferential mate faces are axially-sloped and form an angle of at least 45° relative to an axial direction of the vane arc segment, the flange is coextensive with the suction side circumferential mate face, and the flange is flush with the axially-sloped suction side circumferential mate face.