Claims
- 1. A method for decreasing a heat load on a combustor liner for a turbine engine, the combustor liner including a plurality of air cooling slots formed by overhanging portions of a combustor liner surface, each overhang portion having a rear facing edge, said method comprising the steps of:shaping each rear facing edge to facilitate reducing combustion gas flow turbulence generated as the flow separates off the rear facing edge relative to a blunt edge; and coating the rear facing edge with a thermal barrier coating.
- 2. A method in accordance with claim 1 wherein the step of shaping each rear facing edge comprises the step of forming a curved rear facing edge.
- 3. A method in accordance with claim 2 wherein the step of shaping the rear facing edge further comprises the step of tapering the overhang portion.
- 4. A method in accordance with claim 1 wherein the step of shaping the rear facing edge comprises the step of forming a chamfered rear facing edge.
Parent Case Info
This application is a divisional of Ser. No. 09/454,708 filed on Dec. 3, 1999 now U.S. Pat. No. 6,250,082 and claims benefit thereto.
US Referenced Citations (5)
Foreign Referenced Citations (5)
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FR |
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