发明名称 |
Gas turbine engine component with impingement and lobed cooling hole |
摘要 |
A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole is formed in the gas path wall and extends from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface. A longitudinal ridge extends along the cooling hole between the transition and the outlet. The longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes. |
申请公布号 |
US8683814(B2) |
申请公布日期 |
2014.04.01 |
申请号 |
US201213544257 |
申请日期 |
2012.07.09 |
申请人 |
XU JINQUAN;UNITED TECHNOLOGIES CORPORATION |
发明人 |
XU JINQUAN |
分类号 |
F02C7/12 |
主分类号 |
F02C7/12 |
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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