Attachment faces for clamped turbine stator of a gas turbine engine
An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.
1. An airfoil fairing shell for a gas turbine engine comprising:
an airfoil section between an outer vane endwall and an inner vane endwall, at least one of said outer vane endwall and said inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face, said suction side tangential attachment face perpendicular to a resultant aerodynamic load generated by said airfoil.
2. The airfoil fairing shell as recited in claim 1 , wherein said radial attachment face, said suction side tangential attachment face, said pressure side tangential attachment face, and said axial attachment face are formed by a thickened region of at least one of said outer vane endwall and said inner vane endwall.
3. The airfoil fairing shell as recited in claim 1 , wherein said radial attachment face, said suction side tangential attachment face, said pressure side tangential attachment face, and said axial attachment face are formed by a thickened region of said inner vane endwall.
4. The airfoil fairing shell as recited in claim 1 , wherein said suction side tangential attachment face is parallel to said pressure side tangential attachment face.
5. The airfoil fairing shell as recited in claim 1 , wherein said suction side tangential attachment face and said pressure side tangential attachment face are non-parallel to said inner vane endwall.
6. The airfoil fairing shell as recited in claim 1 , wherein said suction side tangential attachment face and said pressure side tangential attachment face are non-parallel to an edge of said outer vane endwall.
7. The airfoil fairing shell as recited in claim 1 , wherein said suction side tangential attachment face is downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil.
8. A vane ring for a gas turbine engine, comprising:
a multiple of airfoil fairing shells each with a first attachment face formed by a thickened region of a vane endwall that forms a mateface, each of said multiple of airfoil fairing shells adjacent to another one of said multiple of airfoil fairing shells at said mateface; and
a structural support with a multiple of lugs, each of said multiple of lugs interfaces with at least one of said first attachment faces of each of said multiple of airfoil fairing shells.
9. The vane ring as recited in claim 8 , wherein said structural support includes an interface for attachment to an engine case structure.
10. The vane ring as recited in claim 8 , wherein said structural support is an arcuate segment.
11. The vane ring as recited in claim 8 , wherein said structural support is a full ring.
12. The vane ring as recited in claim 8 , wherein said lug extends transverse to said mateface of said vane endwall.
13. The vane ring as recited in claim 8 , wherein said thickened region of said vane endwall forms a radial attachment face, an axial attachment face, and a pressure side tangential attachment face.
14. The vane ring as recited in claim 13 , wherein said first attachment face is a suction side tangential attachment face.
15. The vane ring as recited in claim 14 , wherein said axial attachment face, said pressure side tangential attachment face, and said suction side tangential attachment face are perpendicular to said radial attachment face.
16. The vane ring as recited in claim 15 , wherein said axial attachment face is perpendicular to said pressure side tangential attachment face and said suction side tangential attachment face.
17. The vane ring as recited in claim 16 , wherein said suction side tangential attachment face is downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil fairing shell such that the in plane loading to the reaction forces on these faces is compressive.
18. The vane ring as recited in claim 16 , wherein said suction side tangential attachment face and said axial attachment face are downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil fairing shell such that the in plane loading to the reaction forces on these faces is compressive.