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US08397511B2 System and method for cooling a wall of a gas turbine combustor 有权
用于冷却燃气轮机燃烧器的壁的系统和方法

System and method for cooling a wall of a gas turbine combustor
Abstract:
A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening on a hot-side, and a section of thermal barrier coating (TBC) applied on the cold-side and having an opening that generally circumscribes the first opening.
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