Airfoil with supplemental cooling channel adjacent leading edge
An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air...
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| Format: | Patent |
| Sprache: | eng |
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| Zusammenfassung: | An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air onto a suction wall. The supplemental film cooling channel air is generally directed to a location on the suction wall that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating. |
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