Vane with chevron face
A gas turbine engine component includes a vane arc segment that defines an axis. The vane arc segment includes an airfoil section and first and second platforms. The airfoil section has a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge. The airfoil section has associated characteristics, including a center of pressure and an aerodynamic load vector through the center of pressure. The first platform defines a first side chevron face that has a leading leg and a trailing leg that meet at an angle. The leading leg is elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meets the leading face at a leading first side corner. The leading first side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
1. A gas turbine engine component comprising:
a vane arc segment defining an axis, the vane arc segment including
an airfoil section having a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge, the airfoil section having associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure,
a first platform and a second platform arranged, respectively, at the first radial end and the second radial end of the airfoil section, the first platform defining a leading face, a trailing face, a first side chevron face, and a second side face, the first side chevron face having a leading leg and a trailing leg that meet at an angle, the leading leg being elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meeting the leading face at a leading first side corner, and the leading first side corner being located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
2. The gas turbine engine component as recited in claim 1 , wherein the leading leg defines a plane that is non-intersecting with the aerodynamic load vector forward of the center of pressure.
3. The gas turbine engine component as recited in claim 1 , wherein the centerline is substantially parallel with the aerodynamic load vector.
4. The gas turbine engine component as recited in claim 3 , wherein the leading leg defines a plane that is non-intersecting with the aerodynamic load vector forward of the center of pressure.
5. The gas turbine engine component as recited in claim 1 , wherein the airfoil section, the first platform, and the second platform form a continuous piece, and the continuous piece is formed of a ceramic matrix composite.
6. The gas turbine engine component as recited in claim 5 , wherein the ceramic matrix composite includes silicon carbide fibers disposed in a silicon carbide matrix.
7. The gas turbine engine component as recited in claim 1 , wherein the first platform is a radially inner platform, the first side chevron face is a pressure side chevron face, and the second side face is a suction side face.
8. A gas turbine engine component comprising:
a vane arc segment defining an axis, the vane arc segment including
an airfoil section having a first radial end, a second radial end, a pressure side, a suction side, a leading edge, and a trailing edge, the airfoil section having associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure,
a first platform and a second platform arranged, respectively, at the first radial end and the second radial end of the airfoil section, the first platform defining a leading face, a trailing face, a pressure side chevron face, and a suction side face, the pressure side chevron face having a leading leg and a trailing leg that meet at an angle, the leading leg defining a plane that is non-intersecting with the aerodynamic load vector forward of the center of pressure, the leading leg meeting the leading face at a leading pressure side corner, and the leading pressure side corner being located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
9. The gas turbine engine component as recited in claim 8 , wherein the leading leg is elongated along a centerline, and the centerline is substantially parallel with the aerodynamic load vector.
10. The gas turbine engine component as recited in claim 8 , wherein the airfoil section, the first platform, and the second platform form a continuous piece, and the continuous piece is formed of a ceramic matrix composite.
11. The gas turbine engine component as recited in claim 10 , wherein the ceramic matrix composite includes silicon carbide fibers disposed in a silicon carbide matrix.
12. The gas turbine engine component as recited in claim 8 , wherein the first platform is a radially inner platform.
13. A gas turbine engine component comprising:
a vane arc segment defining an axis, the vane arc segment including
an airfoil section having a first radial end, a second radial end, a pressure side, a suction side, a leading edge, and a trailing edge, the airfoil section having associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure,
a first platform and a second platform arranged, respectively, at the first radial end and the second radial end of the airfoil section, the first platform defining a leading face, a trailing face, a pressure side chevron face, and a suction side face, the pressure side chevron face having a leading leg and a trailing leg that meet at an angle, the leading leg being elongated along a centerline, and the centerline being substantially parallel with the aerodynamic load vector.
14. The gas turbine engine component as recited in claim 13 , wherein the centerline is non-axially oriented with respect to the axis.
15. The gas turbine engine component as recited in claim 14 , wherein the leading leg defines a plane that is non-intersecting with the aerodynamic load vector forward of the center of pressure.
16. The gas turbine engine component as recited in claim 13 , wherein the leading leg meets the leading face at a leading pressure side corner, and the leading pressure side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
17. The gas turbine engine component as recited in claim 13 , wherein the leading leg defines a plane that is non-intersecting with the aerodynamic load vector forward of the center of pressure.
18. The gas turbine engine component as recited in claim 13 , wherein the airfoil section, the first platform, and the second platform form a continuous piece, and the continuous piece is formed of a ceramic matrix composite.
19. The gas turbine engine component as recited in claim 18 , wherein the ceramic matrix composite includes silicon carbide fibers disposed in a silicon carbide matrix.
20. The gas turbine engine component as recited in claim 13 , wherein the first platform is a radially inner platform.