Multi-lobed cooling hole and method of manufacture
A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.
1. A gas turbine engine component comprising:
a wall having first and second wall surfaces and defining a cooling hole extending through the wall, the cooling hole including:
an inlet located at the first wall surface;
an outlet located at the second wall surface;
a metering section extending downstream from the inlet; and
a diffusing section extending from the metering section to the outlet, the diffusing section comprising:
a first lobe diverging longitudinally in a first direction and laterally from the metering section, the first lobe comprising a curved outer portion;
a second lobe adjacent the first lobe and diverging longitudinally in the first direction from the metering section; and
a third lobe adjacent the second lobe and diverging longitudinally in the first direction and laterally from the metering section, the third lobe comprising a curved outer portion; and
a transition region having an end adjacent the outlet and a portion that extends upstream of the outlet and between at least one of the first, second and third lobes and the outlet.
2. The component of claim 1 , wherein the second lobe comprises a curved bottom portion.
3. The component of claim 2 , wherein the diffusing section further comprises:
a first curved surface located between the first lobe and the second lobe; and
a second curved surface located between the third lobe and the second lobe, wherein a portion of the first curved surface is positioned between the outlet and the curved bottom portion of the second lobe, and wherein a portion of the second curved surface is positioned between the outlet and the curved bottom portion of the second lobe.
4. The component of claim 1 , wherein the first lobe and the second lobe meet at a first ridge, and wherein the second lobe and the third lobe meet at a second ridge.
5. The component of claim 4 , wherein the first ridge extends into a portion of the transition region, and wherein the second ridge extends into a portion of the transition region.
6. The component of claim 4 , wherein the transition region comprises:
a first rib aligned with the first ridge; and
a second rib aligned with the second ridge.
7. The component of claim 4 , wherein the first and second ridges terminate upstream of the transition region.
8. The component of claim 4 , wherein the first lobe further comprises a substantially planar portion located between the first ridge and the curved outer portion of the first lobe, and wherein the third lobe further comprises a substantially planar portion located between the second ridge and the curved outer portion of the third lobe.
9. The component of claim 4 , wherein the second lobe is curved between the first and second ridges.
10. The component of claim 1 , wherein the first, second and third lobes each comprise a trailing edge, and wherein the trailing edges of the first, second and third lobes terminate upstream of the outlet.
11. The component of claim 1 , wherein the end of the transition region adjacent the outlet is straight.
12. The component of claim 1 , wherein the end of the transition region adjacent the outlet is curved.
13. The component of claim 1 , wherein the portion of the transition region that extends between the lobes and the outlet is longitudinally convex.
14. The component of claim 1 , wherein the diffusing section further comprises:
a first substantially horizontal surface located between the first lobe and the second lobe; and
a second substantially horizontal surface located between the third lobe and the second lobe.
15. A wall of a component of a gas turbine engine, the wall comprising:
first and second wall surfaces;
an inlet located at the first wall surface;
an outlet located at the second wall surface;
a metering section commencing at the inlet and extending downstream from the inlet; and
a diffusing section extending from the metering section and terminating at the outlet, the diffusing section comprising:
a first lobe diverging longitudinally in a first direction and laterally from the metering section;
a second lobe adjacent the first lobe and diverging longitudinally in the first direction from the metering section;
a third lobe adjacent the second lobe and diverging longitudinally in the first direction and laterally from the metering section; and
a transition region having an end adjacent the outlet and a portion that extends upstream of the outlet and between at least one of the first, second and third lobes and the outlet.
16. The wall of claim 15 , wherein the first lobe and the second lobe meet at a first ridge, and wherein the second lobe and the third lobe meet at a second ridge.
17. The wall of claim 16 , wherein the first ridge extends into a portion of the transition region, and wherein the second ridge extends into a portion of the transition region.
18. The wall of claim 16 , wherein the transition region comprises:
a first rib aligned with the first ridge; and
a second rib aligned with the second ridge.
19. The wall of claim 16 , wherein the first and second ridges terminate upstream of the transition region.
20. The wall of claim 16 , wherein the first lobe comprises a curved outer portion and a substantially planar portion located between the first ridge and the curved outer portion of the first lobe, and wherein the third lobe comprises a curved outer portion and a substantially planar portion located between the second ridge and the curved outer portion of the third lobe.
21. The wall of claim 16 , wherein the second lobe is curved between the first and second ridges.
22. The wall of claim 15 , wherein the first, second and third lobes each comprise a trailing edge, and wherein the trailing edges of the first, second and third lobes terminate upstream of the outlet.
23. The wall of claim 15 , wherein the end of the transition region adjacent the outlet is straight.
24. The wall of claim 15 , wherein the end of the transition region adjacent the outlet is curved.
25. The wall of claim 15 , wherein the portion of the transition region that extends between the lobes and the outlet is longitudinally convex.
26. A method for producing a cooling hole in a gas turbine engine wall having first and second wall surfaces, the method comprising:
forming a metering section between the first wall surface and the second wall surface, wherein the metering section meters a flow of fluid through the cooling hole;
forming a center lobe between the metering section and the second wall surface, wherein the center lobe extends axially from the metering section and diverges longitudinally in a first direction from the metering section;
forming a first side lobe between the metering section and the second wall surface on a first side of the center lobe, wherein the first side lobe diverges longitudinally in the first direction and laterally from the metering section;
forming a second side lobe between the metering section and the second wall surface on a second side of the center lobe opposite the first side, wherein the second side lobe diverges longitudinally in the first direction and laterally from the metering section; and
forming a transition region downstream of at least one of the lobes, such that the transition region extends from the at least one lobe to the second wall surface.
27. The method of claim 26 , wherein the steps of forming the metering section, forming the center lobe, forming the first side lobe and forming the second side lobe are performed by electrical discharge machining, laser drilling, laser machining, electrical chemical machining, waterjet machining, casting, conventional machining and combinations thereof.
28. A gas turbine engine component comprising:
a wall having first and second wall surfaces and defining a cooling hole extending through the wall, the cooling hole including:
an inlet located at the first wall surface;
an outlet located at the second wall surface;
a metering section extending downstream from the inlet; and
a diffusing section extending from the metering section to the outlet, the diffusing section comprising:
a first lobe diverging longitudinally in a first direction from the metering section;
a second lobe adjacent the first lobe and diverging longitudinally in the first direction from the metering section; and
a third lobe adjacent the second lobe and diverging longitudinally in the first direction from the metering section; and
a transition region having an end adjacent the outlet and a portion that extends between at least one of the first, second and third lobes and the outlet.