发明名称 |
Airfoil with supplemental cooling channel adjacent leading edge |
摘要 |
An airfoil (59), and in a disclosed embodiment a rotor blade, has film cooling holes (48) formed at a leading edge (41). A supplemental film cooling channel (60) is positioned near the leading edge (41), but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel (60) directs film cooling air onto a suction wall (38). The supplemental film cooling channel air is generally directed to a location on the suction wall (38) 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. |
申请公布号 |
EP1659264(B1) |
申请公布日期 |
2012.11.07 |
申请号 |
EP20050257230 |
申请日期 |
2005.11.23 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
CUNHA, FRANK J.;PIETRASZKIEWICZ, EDWARD F.;CHON, YOUNG;KONTROVITZ, DAVID M.;LEVINE, JEFFREY R.;MONGILLO, DOMINIC;TELLER, BRET |
分类号 |
F01D5/18;F01D5/28;F02C7/12 |
主分类号 |
F01D5/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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