IMPINGEMENT COOLING FOR A GAS TURBINE ENGINE COMPONENT
First Claim
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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.
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Abstract
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 Citation
20 Claims
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1. An impingement cooled component comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A method for cooling a component comprising:
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directing a plurality of impingement jets 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 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. - View Dependent Claims (13, 14, 15, 16, 17)
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18. A gas turbine engine component comprising:
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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. - View Dependent Claims (19, 20)
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Specification