Impingement cooling for a gas turbine engine component
An impingement cooled component includes a first wall having a plurality of impingement holes and a second wall spaced apart from the first wall. The second wall is downstream of the first wall, relative to a cooling flow, the second wall has a contoured surface facing the first wall. The contoured surface includes a plurality of contours defined by at least one of a plurality of peaks and a plurality of valleys, and at least one of the contours in the plurality of contours is aligned with an axis defined by one of the impingement holes in the plurality of impingement holes.
1. An impingement cooled component comprising:
a first wall including a plurality of impingement holes;
a second wall spaced apart from said first wall, wherein the second wall is downstream of said first wall, relative to a cooling flow, the second wall having a contoured surface facing said first wall;
wherein said contoured surface includes a plurality of contours defined by at least one of a plurality of peaks and a plurality of valleys; and
wherein a peak of each contour in said plurality of contours is aligned with an axis defined by one of said impingement holes in said plurality of impingement holes.
2. The impingement cooled component of claim 1 , wherein each of said impingement holes defines an impingement axis, and wherein said impingement axis is normal to said second wall.
3. The impingement cooled component of claim 1 , wherein each of said impingement holes defines an impingement axis, and wherein said impingement axis is angled relative to said second wall.
4. The impingement cooled component of claim 1 , wherein the second wall further comprises a plurality of film holes, each of said film holes providing a fluid passageway connecting said contoured surface of said second wall with a second surface of said second wall.
5. The impingement cooled component of claim 4 , wherein at least one of said film cooling holes connects a peak of at least one contour of said contoured surface with said second surface of said second wall.
6. The impingement cooled component of claim 4 , wherein at least one of said film cooling holes connects a valley of at least one contour of said contoured surface with said second surface of said second wall.
7. The impingement cooled component of claim 1 , said contoured surface comprises a plurality of identical contours.
8. The impingement cooled component of claim 1 , wherein said plurality of contours are evenly distributed across said contoured surface.
9. The impingement cooled component of claim 1 , wherein said plurality of impingement holes are a first density in a first region of said first wall and a second density, different from said first density, in a second region of said first wall.
10. The impingement cooled component of claim 1 , wherein said second wall further comprises a second surface opposite said contoured surface and wherein said second surface is straight.
11. The impingement cooled component of claim 1 , wherein the second wall is a wall of one of a turbine rotor, a turbine vane, a blade outer air seal, a rotor platform, a vane platform, and a blade outer air seal platform.
12. A method for cooling a component comprising: directing a plurality of impingement lets onto a plurality of peaks of a contoured surface of a cooled component, thereby increasing a surface area of the cooled component contacted by the impingement jet, relative to a non-contoured surface, and generating a cooling film on a second surface of the cooling component using film cooling holes connecting the contoured surface to the second surface, wherein the second surface is opposite the contoured surface.
13. A method for cooling a component comprising: directing a plurality of impingement lets onto a plurality of peaks of a contoured surface of a cooled component, thereby increasing a surface area of the cooled component contacted by the impingement jet, relative to a non-contoured surface, wherein directing at least one impingement jet onto a contoured surface comprises directing a plurality of impingement jets onto the contoured surface, and wherein the plurality of impingement jets are unevenly distributed across the contoured surface.
14. A gas turbine engine component comprising:
a component wall having at least a first surface and a second surface;
an impingement baffle spaced apart from said component wall and including a plurality of impingement holes; and
the first surface of the component wall facing said impingement baffle and including a plurality of cooling contours, wherein a peak of each of said cooling contours is aligned with an axis of a corresponding impingement hole.
15. The gas turbine engine component of claim 14 , further comprising a plurality of film cooling holes connecting said first surface and said second surface, and configured to establish a film cooling layer across at least a portion of said second surface.
16. The gas turbine engine component of claim 14 , wherein each of said cooling contours includes at least one angled surface configured to direct a cooling flow from an impingement jet to a valley defined between at least two cooling contours.