发明名称 |
Endwall shape for use in turbomachinery |
摘要 |
The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.
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申请公布号 |
US6669445(B2) |
申请公布日期 |
2003.12.30 |
申请号 |
US20020093989 |
申请日期 |
2002.03.07 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
STAUBACH J. BRENT;WAGNER JOEL H.;AGGARWALA ANDREW S. |
分类号 |
F01D5/30;F01D5/14;F04D29/32;(IPC1-7):F01D5/12 |
主分类号 |
F01D5/30 |
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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