Engine component assembly
An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
1. An engine component assembly, comprising:
a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface;
a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface, different from the first surface, parallel to and spaced from the cooling surface and defining a space between the second surface and the cooling surface of the first engine component;
at least one cooling aperture extending through the second engine component from the first surface to the second surface and defining a cooling fluid flow path along a cooling fluid streamline; and
at least one cavity provided in the cooling surface and defining a cavity surface;
wherein the at least one cooling aperture is arranged such that the cooling fluid streamline extends at a non-orthogonal angle relative to the cooling surface and towards the at least one cavity.
2. The engine component assembly of claim 1 wherein the at least one cooling aperture and the at least one cavity are arranged such that the cooling fluid streamline contacts the cavity surface.
3. The engine component assembly of claim 2 wherein the cooling fluid streamline contacts the cavity surface at an acute impingement angle.
4. The engine component assembly of claim 1 wherein the non-orthogonal angle is an acute angle.
5. The engine component assembly of claim 4 wherein the acute angle is less than 60 degrees.
6. The engine component assembly of claim 1 wherein the cooling fluid streamline is non-orthogonal to a non-cavity portion of the cavity surface.
7. The engine component assembly of claim 1 wherein the at least one cavity comprises a plurality of cavities.
8. The engine component assembly of claim 7 wherein the plurality of cavities is arranged in a predetermined configuration.
9. The engine component assembly of claim 7 wherein the at least one cooling aperture comprises at least one cooling aperture for each of the plurality of cavities.
10. The engine component assembly of claim 1 wherein the at least one cavity comprises a dimple or a channel.
11. The engine component assembly of claim 1 wherein the at least one cavity has a leading edge and a trailing edge relative to the cooling fluid flow path.
12. The engine component assembly of claim 11 further comprising a cooling feature provided at or by the trailing edge.
13. The engine component assembly of claim 12 wherein the cooling feature is provided at the trailing edge.
14. The engine component assembly of claim 12 wherein the cooling feature comprises at least one of a vortex generator, a turbulator, a pin fin, or an aerodynamic fin.
15. The engine component assembly of claim 12 wherein the cooling feature has a leading edge and a trailing edge relative to the cooling fluid flow path, and the cooling feature leading edge forms a transition with the at least one cavity.
16. The engine component assembly of claim 15 wherein the transition is a smooth transition.
17. The engine component assembly of claim 16 wherein the smooth transition comprises a radiused structure.
18. The engine component assembly of claim 17 wherein the cooling feature leading edge has an upward extent that terminates in a radiused structure.
19. The engine component assembly of claim 18 wherein the cooling feature comprises a top edge extending between the cooling feature leading edge and the cooling feature trailing edge, and the top edge reduces in height from the cooling feature leading edge to the cooling feature trailing edge.
20. The engine component assembly of claim 19 wherein the top edge tapers from the cooling feature leading edge to the cooling feature trailing edge when viewed in a plane transverse to the direction of the cooling fluid flow path.
21. The engine component assembly of claim 20 wherein the top edge forms an angle with the cooling surface of the first engine component having a vertex at the cooling feature trailing edge and the angle is between 10 degrees and 20 degrees.
22. The engine component assembly of claim 1 , wherein the at least one cooling aperture is defined by a louver in the second engine component.
23. The engine component assembly of claim 1 wherein the first engine component comprises at least one of a nozzle, a vane, a blade, a shroud, a combustor liner, or a combustor deflector.
24. The engine component assembly of claim 1 wherein the second engine component comprises a wall located within an interior of the first engine component.
25. The engine component assembly of claim 24 wherein the space is formed from at least a portion of the interior of the first engine component.
26. The engine component assembly of claim 24 wherein the wall comprises an insert located within the interior of the first engine component and the at least one cooling aperture extends through the insert.