Component for a turbine engine with a cooling hole

1. A component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow, comprising:

a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow;

at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet defining a modified outlet shape having:

an expansion section having an increasing width,

a constant section downstream of the expansion section and having a constant width, and

a contraction section downstream of the constant section and having a decreasing width.

2. The component of claim 1 wherein the decreasing width being a continuously decreasing width.

3. The component of claim 1 further comprising at least one connecting passage extending between the at least one inlet and the at least one outlet to define a passage centerline and a downstream flow direction from the inlet to the outlet.

4. The component of claim 3 wherein the connecting passage comprises a metering section fluidly coupled to the inlet and a diffusing section, downstream of the metering section, and fluidly coupling the metering section to the outlet.

5. The component of claim 4 wherein the passage centerline at the diffusing section forms an exit angle with the heated surface that is less than an entrance angle with the heated surface formed by the passage centerline of the metering section.

6. The component of claim 4 wherein the metering section has a constant cross-sectional area.

7. The component of claim 1 wherein the increasing width being a continuously increasing width.

8. The component of claim 1 wherein the outlet further comprises a second expansion section located downstream of the constant section.

9. The component of claim 8 wherein the second expansion section comprises a continuously increasing width.

10. The component of claim 1 wherein the component is an airfoil.

11. The component of claim 10 wherein the wall forms a platform for the airfoil.

12. A method for forming a set of cooling holes for an engine component, the set of cooling holes including at least one cooling hole extending between an inlet and an outlet, the method comprising:

forming the set of cooling holes such that the inlet is located on a first surface and the outlet is located on a second surface;

forming a connecting passage to connect the inlet to the outlet; and

forming the outlet with a modified outlet shape, the modified outlet shape comprising:

an expansion section having an increasing width,

a constant section having a constant width and located downstream from the expansion section, and

a second expansion section located downstream from the constant section.

13. The method of claim 12 further comprising forming a contraction section located downstream from the constant section.

14. The method of claim 13 further comprising forming the second expansion section at a location downstream from the constant section and upstream from the contraction section.

15. The method of claim 12 further comprising determining a patterned layout for the set of cooling holes comprising a first line and a second line parallel to the first line.

16. The method of claim 15 further comprising forming the patterned layout wherein the set of cooling holes includes a first pair of cooling holes and a first pair of inlets are in line with the first line and a first pair of outlets are in line with the second line.

17. The method of claim 16 further comprising forming a second pair of cooling holes where a second pair of outlets are outlets formed above the first pair of inlets with respect to the first surface.

18. The method of claim 16 wherein the first line and the second line are angled with respect to a flow direction.