Turbine engine with reduced cross flow airfoils
An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.
1. An airfoil assembly comprising:
a platform having an upstream edge, a downstream edge and a surface extending therebetween, with at least a portion of the surface extending circumferentially along a surface baseline defined by a constant radius;
an airfoil extending from the platform and having an outer wall extending between a leading edge and a trailing edge and between a root and a tip defining a span-wise direction, the outer wall defining a pressure side and a suction side;
a fence along the outer wall and defining a raised potion of the outer wall, the fence following a local contour of the surface; and
at least one of:
a projection located along the platform and extending along the outer wall, the projection extending radially outward from the surface baseline; or
a valley located along the platform and defining a depression formed along the surface, the valley extending radially inward from the surface baseline to a maximum depth;
wherein at least a portion of the fence follows the local contour defined by at least one of the projection or the valley.
2. The airfoil assembly of claim 1 , wherein the fence wraps around the leading edge of the airfoil.
3. The airfoil assembly of claim 1 , wherein the airfoil includes a mean camber line, and the fence is asymmetric about the mean camber line.
4. The airfoil assembly of claim 3 , wherein the fence extends along the pressure side with respect to the mean camber line a first distance, and along the suction side with respect to the mean camber line a second distance, less than the first distance.
5. The airfoil assembly of claim 1 , wherein the airfoil includes a mean camber line, and the fence includes a radial width, with respect to the mean camber line, the radial width being non-constant along a respective portion of the fence.
6. The airfoil of claim 5 , wherein the radial width decreases from an axially upstream portion to an axially downstream portion of the fence.
7. The airfoil assembly of claim 1 , wherein the airfoil assembly is located in a turbine engine having a longitudinal axis, and the airfoil has an axial chord defined as a normal axial distance with respect to the longitudinal axis, between the leading edge and the trailing edge.
8. The airfoil assembly of claim 7 , wherein the fence terminates at an axially downstream end that is greater than or equal to 60% and less than or equal to 90% of the axial chord from the leading edge to the trailing edge.
9. The airfoil assembly of claim 7 , wherein the fence terminates at an axially forward end that is greater than or equal to −20% and less than or equal to 30% of the axial chord, where 0% of the axial chord corresponds to the leading edge.
10. The airfoil assembly of claim 7 , wherein the fence includes a maximum thickness in the span-wise direction, the maximum thickness being greater than or equal to 2% and less than or equal to 10% of a length of the axial chord from the leading edge to the trailing edge.
11. The airfoil assembly of claim 1 , wherein the fence is a first fence, the airfoil assembly further including a second fence along the outer wall, the first and second fences spaced apart along the airfoil in the span-wise direction.
12. The airfoil assembly of claim 1 , wherein a portion of the fence on the pressure side follows the local contour defined by the projection, while a portion of the fence on the suction side follows the local contour defined by the valley.
13. The airfoil assembly of claim 1 , wherein the fence terminates axially prior to the valley on a side of the airfoil corresponding to the valley.
14. An airfoil assembly comprising:
a platform having an upstream edge, a downstream edge and a surface extending therebetween, with at least a portion of the surface extending circumferentially along a surface baseline defined by a constant radius;
an airfoil extending from the platform and having an outer wall extending between a leading edge and a trailing edge and between a root and a tip to define a span of the airfoil, the outer wall defining a pressure side and a suction side, the airfoil having an axial chord measured as a normal distance between the leading edge and the trailing edge;
a fence located along the outer wall and defining an undulation along a respective portion of the outer wall, the fence being located a predetermined height from the surface along the span of the airfoil, the predetermined height being between 0% and 20% of the span as measured from the root, the fence being spaced from the surface, and the fence having a thickness defined as a distance the fence extgends relative to the span, the thickness being between 2% and 10% of the axial chord; and
a splitter located along the surface being circumferentially offset from the airfoil, the splitter extending radially outward from the surface baseline.
15. The airfoil assembly of claim 14 , further comprising at least one of:
a projection along the platform and extending along the outer wall, the projection extending radially outward from the surface baseline; or
a valley along the platform and defining a depression formed along the surface, the valley extending radially inward from the surface baseline to a maximum depth.
16. The airfoil assembly of claim 14 , further comprising a trench provided circumferentially between the splitter and the airfoil.
17. The airfoil assembly of claim 14 , wherein the fence terminates radially away from the surface at an edge, with the edge having a non-constant radial height from the surface to define the edge as an angled edge.
18. An airfoil assembly comprising:
a platform having an upstream edge, a downstream edge and a surface extending therebetween, with at least a portion of the surface extending circumferentially along a surface baseline defined by a constant radius;
an airfoil extending from the platform and having an outer wall extending between a leading edge and a trailing edge and between a root and a tip, the outer wall defining a pressure side and a suction side;
a fence located along the outer wall and defining a raised potion of the outer wall;
a splitter located along the surface being circumferentially offset from the airfoil, the splitter extending radially outward from the surface baseline; and
a bridge extending circumferentially between the splitter and at least one of the outer wall or the fence.
19. The airfoil assembly of claim 18 , wherein the bridge extends circumferentially between the fence and a respective portion of the splitter.
20. An airfoil assembly comprising:
a platform having an upstream edge, a downstream edge and a surface extending therebetween, with at least a portion of the surface extending circumferentially along a surface baseline defined by a constant radius;
an airfoil extending from the platform and having an outer wall extending between a leading edge and a trailing edge and between a root and a tip, the outer wall defining a pressure side and a suction side;
a fence located along the outer wall and defining a raised potion of the outer wall;
a splitter located along the surface being circumferentially offset from the airfoil, the splitter extending radially outward from the surface baseline; and
a trench provided circumferentially between the splitter and the airfoil, the trench terminating at an outlet that is provided circumferentially between the splitter and the airfoil, with the outlet being axially aligned with a respective portion of the splitter.