Shaped cooling holes for reduced stress
View Patent ↗A gas turbine engine component having shaped cooling holes that further enhances the cooling of a desired region while reducing stress levels in and around the cooling holes is disclosed. The cooling holes are generally elliptically-shaped and diffuse from a cooling fluid supply side to a discharge side and are oriented on the turbine component to reduce stress concentrations while directing the cooling fluid to a desired surface or location. The elliptical cooling holes have openings in the surface that have high points that are concentric and planar.
1. A cooled gas turbine engine component comprising:
a first surface;
a second surface separated from the first surface by a thickness of material; and,
a plurality of cooling holes extending between the first and second surfaces, the plurality of cooling holes having a generally elliptical shape that tapers in cross section through the full thickness of the material between the first surface to the second surface so as to diffuse a cooling flow.
2. The component of claim 1 , wherein the cross section of the elliptical shape at the first surface has a first major axis, a first minor axis, and a first high point.
3. The component of claim 2 , wherein the cross section of the elliptical shape at the second surface has a second major axis, a second minor axis, and a second high point.
4. The component of claim 3 , wherein the first major axis is less than the second major axis and the first minor axis is less than the second minor axis.
5. The component of claim 4 , wherein the first point and second point are concentric.
6. The component of claim 5 , wherein the plurality of cooling holes are oriented at an acute surface angle relative to the second surface.
7. The component of claim 3 , wherein a first radius of curvature is formed generally by a surface associated with the first major axis.
8. The component of claim 4 , wherein the first radius of curvature is oriented in a direction to spread stresses around the cooling holes.
9. A tapered elliptical cooling hole comprising:
a first elliptically-shaped opening in a first surface and having a first major axis, a first minor axis, and a first point at a high point of the first major axis; and,
a second elliptically-shaped opening in a second surface having a second major axis, a second minor axis, and a second point at a high point of the second major axis, the second surface spaced a distance from the first surface;
wherein the first point and the second point are concentric and located within a plane, and
wherein the cooling hole tapers over the entire distance between the first elliptically-shaped opening in the first surface and the second elliptically-shaped opening in the second surface.
10. The tapered elliptical cooling hole of claim 9 , wherein the elliptical cooling hole is located in a turbine blade or vane.
11. The tapered elliptical cooling hole of claim 9 , wherein the second major axis is greater than the first major axis.
12. The tapered elliptical cooling hole of claim 11 , wherein the second minor axis is greater than the first minor axis.
13. The tapered elliptical cooling hole of claim 9 , wherein the cooling hole is oriented at an acute angle relative to a first surface.
14. The tapered elliptical cooling hole of claim 9 , wherein the cooling hole maintains an elliptical cross section from the first surface to the second surface.
15. A method of enhancing cooling air flow onto a turbine component while reducing operating stresses comprising:
providing the turbine component having a first surface spaced a distance apart from a second surface by a thickness, the turbine component having a supply of cooling fluid;
placing a plurality of generally elliptically-shaped cooling holes extending from the first surface to the second surface, the cooling holes tapering through the entire distance between the first and second surface so as to diffuse the cooling holes from the first surface to the second surface; and,
directing the cooling fluid through the plurality of generally elliptically-shaped cooling holes, the cooling fluid passing from the first surface, through the hole, and exiting the hole through the second surface.
16. The method of claim 15 further comprising directing the cooling fluid onto a turbine component adjacent to the turbine component having the plurality of cooling holes.
17. The method of claim 15 further comprising directing the cooling fluid along the second surface of the turbine component.
18. The method of claim 15 , wherein the plurality of cooling holes have a first opening at the first surface and a second opening at the second surface and wherein an edge of the cooling holes at the first surface and second surface are concentric.
19. The method of claim 18 , wherein the plurality of cooling holes are oriented at an acute surface angle relative to the second surface.