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 that extends from an outer vane endwall that comprises a forward edge and an aft edge with matefaces that extend between the forward edge and the aft edge, the endwall comprises a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face,
wherein the radial attachment face forms a thickened area spaced from an inner face of the outer vane endwall defined by the suction side tangential attachment face, the pressure side tangential attachment face, and the axial attachment face which is transverse thereto, the forward edge thicker than the aft edge and the forward edge defines the thickness of the suction side tangential attachment face, the pressure side tangential attachment face, and the axial attachment face;
wherein the suction side tangential attachment face, the pressure side tangential attachment face, and the axial attachment face extends from the inner face to the radial attachment face to form a stepped surface.
2. The airfoil fairing shell as recited in claim 1 , wherein the airfoil section comprises a single airfoil.
3. The airfoil fairing shell as recited in claim 1 , wherein the airfoil fairing shell is radially clamped by an outer structural support and an inner structural support.
4. The airfoil fairing shell as recited in claim 1 , wherein a corner at an interface between the suction side tangential attachment face and the axial attachment face is chamfered.
5. The airfoil fairing shell as recited in claim 4 , wherein the chamfered corner allows a load bearing face on a stator shell to clear an edge of a complementary face fillet at their junction on a structural platform to prevent contact stress concentration.
6. The airfoil fairing shell as recited in claim 1 , wherein the suction side tangential attachment face and the pressure side tangential attachment face are perpendicular to the forward edge and the aft edge.
7. The airfoil fairing shell as recited in claim 1 , wherein the axial attachment face and the tangential attachment faces are perpendicular to each other.
8. The airfoil fairing shell as recited in claim 7 , wherein the axial attachment face and the tangential attachment faces are angled with respect to the engine axis.
9. The airfoil fairing shell as recited in claim 7 , wherein the axial attachment face and the tangential attachment faces are not angled with respect to the engine axis.
10. The airfoil fairing shell as recited in claim 1 , wherein the endwall is an outer vane endwall.
11. The airfoil fairing shell as recited in claim 1 , wherein the endwall is an inner vane endwall.
12. The airfoil fairing shell as recited in claim 1 , further comprising a series of lugs of a structural support wherein each lug of the series of lugs are generally rectilinear.
13. The airfoil fairing shell as recited in claim 1 , wherein the axial attachment face is a stepped surface that is of the thickness defined by the forward edge.
14. The airfoil fairing shell as recited in claim 1 , wherein the suction side tangential attachment face located downstream and to a suction side of an aerodynamic center “C” of the airfoil to interface with one of a series of lugs of a structural support to react aerodynamic in-plane loads such that the aerodynamic loads tend to create a compressive rather than tensile loads in a plane with the endwall;
the pressure side tangential attachment face transverse to the forward edge and the aft edge; and
the axial attachment face interfaces with the structural support to provide a secondary reaction load.
15. An airfoil fairing shell for a gas turbine engine comprising:
an airfoil section that extends from an outer vane endwall that comprises a forward edge and an aft edge with matefaces that extend between the forward edge and the aft edge, the endwall comprises a suction side tangential attachment face transverse to the forward edge and the aft edge, the suction side tangential attachment face located downstream and to a suction side of an aerodynamic center “C” of the airfoil to interface with one of a series of lugs of a structural support to react aerodynamic in-plane loads such that the aerodynamic loads create a compressive rather than tensile loads in a plane with the endwall, wherein the radial attachment face forms a thickened area spaced from an inner face of the outer vane endwall, the thickened area defined by the suction side tangential attachment face, the pressure side tangential attachment face, and the axial attachment face which is transverse thereto, the suction side tangential attachment face, the pressure side tangential attachment face, and the axial attachment face extends from the inner face to the radial attachment face.
16. The airfoil fairing shell as recited in claim 15 , wherein a corner at an interface between the suction side tangential attachment face and an axial attachment face is chamfered.
17. The airfoil fairing shell as recited in claim 16 , wherein the chamfered corner allows the load bearing faces on the stator shell to clear an edge of a complementary face fillet at their junction on the structural platform to prevent contact stress concentration.
18. The airfoil fairing shell as recited in claim 15 , wherein the suction side tangential attachment face and a pressure side tangential attachment face are perpendicular to the forward edge and the aft edge.
19. The airfoil fairing shell as recited in claim 15 , wherein an axial attachment face and the tangential attachment faces are perpendicular to each other.
20. The airfoil fairing shell as recited in claim 19 , wherein the axial attachment face and the tangential attachment faces are angled with respect to the engine axis.
21. The airfoil fairing shell as recited in claim 19 , wherein the axial attachment face and the tangential attachment faces are not angled with respect to the engine axis.
22. The airfoil fairing shell as recited in claim 15 , further comprising a pressure side tangential attachment face parallel to the suction side tangential attachment face.
23. The airfoil fairing shell as recited in claim 22 , wherein the pressure side tangential attachment face is transverse to the forward edge and the aft edge.
24. The airfoil fairing shell as recited in claim 22 , wherein the axial attachment face extends from the inner face to the radial attachment face to form a stepped surface.