Cooling hole with thermo-mechanical fatigue resistance
A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes 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 includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.
1. A gas turbine engine component comprising:
a wall having first and second opposing surfaces and defining a cooling hole, the cooling hole extending through the wall from an inlet located at the first wall surface to an outlet located at the second wall surface and having:
a metering section extending downstream from the inlet; and
a diffusing section extending from the metering section to the outlet and comprising:
a first lobe diverging longitudinally and laterally from the metering section and having a trailing edge;
a second lobe diverging longitudinally and laterally from the metering section and having a trailing edge;
an upstream end located at the outlet;
a downstream end generally opposite the upstream end and located at the outlet, wherein the downstream end extends in a straight and lateral direction from an end of the first lobe to an end of the second lobe, and wherein the downstream end is at least axially coextensive with the trailing edges of the first and second lobes;
a first sidewall having a first edge extending along the outlet between the upstream end and the downstream end trailing edge, the first edge diverging laterally from the upstream end and converging laterally before reaching the downstream end; and
a second sidewall having a second edge extending along the outlet between the upstream end and the downstream end generally opposite the first sidewall, the second edge diverging laterally from the upstream end and converging laterally before reaching the downstream end.
2. The component of claim 1 , wherein an angle formed between a line tangent to the first edge at its greatest lateral divergence and the downstream end is greater than about 75°, and wherein an angle formed between a line tangent to the second edge at its greatest lateral divergence and the downstream end is greater than about 75°.
3. The component of claim 2 , wherein an angle formed between a line tangent to the first edge at its greatest lateral divergence and the downstream end is greater than about 85°, and wherein an angle formed between a line tangent to the second edge at its greatest lateral divergence and the downstream end is greater than about 85°.
4. The component of claim 1 , wherein the first edge and the downstream end form a first curved portion, and wherein the second edge and the downstream end form a second curved portion.
5. The component of claim 1 , wherein the first lobe comprises a first lobe trailing edge along which the first lobe meets the outlet at the second wall surface, and wherein the second lobe comprises a second lobe trailing edge along which the second lobe meets the outlet at the second wall surface.
6. The component of claim 5 , wherein the first edge and the first lobe trailing edge form a first curved portion, and wherein the second edge and the second lobe trailing edge form a second curved portion.
7. The component of claim 6 , wherein the first lobe trailing edge and the second lobe trailing edge are parallel and even with the downstream end of the diffusing section.
8. The component of claim 1 , wherein the diffusing section further comprises:
a third lobe positioned between the first and second lobes.
9. The component of claim 1 , wherein the diffusing section further comprises:
a transition region extending between the first and second lobes and extending downstream to the downstream end.
10. The component of claim 9 , wherein the transition region has a portion located between the outlet and the first and second lobes.
11. The component of claim 1 , wherein the diffusing section further comprises:
a first inclined portion adjacent the first lobe and extending towards the second lobe; and
a second inclined portion adjacent the second lobe and extending towards the first lobe.
12. A gas turbine engine component comprising:
a wall having first and second opposing surfaces and defining a cooling hole, the cooling hole extending from an inlet located at the first wall surface to an outlet located at the second wall surface and having:
a metering section extending downstream from the inlet; and
a diffusing section extending from the metering section to the outlet and comprising:
a first lobe diverging longitudinally and laterally from the metering section;
a first inclined portion adjacent the first lobe and extending towards the second lobe;
a second lobe diverging longitudinally and laterally from the metering section;
a second inclined portion adjacent the second lobe and extending towards the first lobe, wherein the first inclined portion and the second inclined portion meet to form a ridge between the first and second lobes;
an upstream end located at the outlet;
a trailing edge opposite the upstream end and located at the outlet;
a first sidewall having a first edge extending along the outlet between the upstream end and the trailing edge, the first edge diverging laterally from the upstream end and converging laterally before reaching the trailing edge; and
a second sidewall having a second edge extending along the outlet between the upstream end and the trailing edge generally opposite the first sidewall, the second edge diverging laterally from the upstream end and converging laterally before reaching the trailing edge.
13. The component of claim 1 , wherein the component is selected from the group consisting of blades, vanes, airfoil tips, airfoil platforms, combustors, blade outer air seals and augmentors.
14. 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, the outlet comprising:
an upstream end;
a downstream end generally opposite the upstream end;
a first lateral edge extending between the upstream end and the downstream end, the first lateral edge diverging laterally from the upstream end and converging laterally before reaching the downstream end; and
a second lateral edge opposite the first lateral edge extending between the upstream end and the downstream end, the second lateral edge diverging laterally from the upstream end and converging laterally before reaching the downstream end, wherein the downstream end extends in a straight and lateral direction from the first lateral edge to the second lateral edge;
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 and laterally from the metering section; and
a second lobe diverging longitudinally and laterally from the metering section.
15. The wall of claim 14 , wherein the first lobe comprises a first lobe trailing edge along which the first lobe meets the downstream end of the outlet, and wherein the second lobe comprises a second lobe trailing edge along which the second lobe meets the downstream end of the outlet.
16. The wall of claim 14 , wherein an angle formed between a line tangent to the first lateral edge at its greatest lateral divergence and the downstream end is greater than about 75°, and wherein an angle formed between a line tangent to the second lateral edge at its greatest lateral divergence and the downstream end is greater than about 75°.
17. The wall of claim 14 , wherein the first lateral edge and the downstream end of the outlet form a first curved portion, and wherein the second lateral edge and the downstream end of the outlet form a second curved portion.
18. The wall of claim 15 , wherein the first lobe trailing edge and the second lobe trailing edge are parallel and even with the downstream end of the outlet.
19. The wall of claim 14 , wherein the diffusing section further comprises:
a third lobe positioned between the first and second lobes.
20. The wall of claim 14 , wherein the diffusing section further comprises:
a transition region extending between the first and second lobes and extending downstream to the downstream end of the outlet.
21. The wall of claim 14 , wherein the component is selected from the group consisting of blades, vanes, airfoil tips, airfoil platforms, combustors, blade outer air seals and augmentors.