Cooling hole for a gas turbine engine component
US-2015377033-A1 · Dec 31, 2015 · US
US9080451B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9080451-B2 |
| Application number | US-201213535540-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 28, 2012 |
| Priority date | Jun 28, 2012 |
| Publication date | Jul 14, 2015 |
| Grant date | Jul 14, 2015 |
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An airfoil includes an interior surface, an exterior surface opposed to the interior surface, a pressure side, a suction side opposed to the pressure side, a stagnation line between the pressure and suction sides, and a trailing edge between the pressure and suction sides and downstream from the stagnation line. A first column of overlapping stagnation trench segments is on the exterior surface, and the stagnation line passes through at least a portion of each of the overlapping stagnation trench segments. At least one cooling passage in each stagnation trench segment provides fluid communication from the interior surface to the exterior surface.
Opening claim text (preview).
What is claimed is: 1. An airfoil, comprising: a. an interior surface; b. an exterior surface opposed to the interior surface, wherein the exterior surface comprises a pressure side, a suction side opposed to the pressure side, a stagnation line between the pressure and suction sides, and a trailing edge between the pressure and suction sides and downstream from the stagnation line; c. a plurality of stagnation trench segments forming a radial column of stagnation trench segme…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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