发明名称 |
Leading edge cooling using chevron trip strips |
摘要 |
A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.
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申请公布号 |
US2007297917(A1) |
申请公布日期 |
2007.12.27 |
申请号 |
US20060473894 |
申请日期 |
2006.06.22 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
LEVINE JEFFREY R.;ABDEL-MESSEH WILLIAM;KAUFMAN ELEANOR |
分类号 |
F01D5/18 |
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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