发明名称 |
System and method for airfoil film cooling |
摘要 |
An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface
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申请公布号 |
US2003007864(A1) |
申请公布日期 |
2003.01.09 |
申请号 |
US20010899305 |
申请日期 |
2001.07.05 |
申请人 |
SHELTON MONTY LEE;WALLACE THOMAS TRACY;FREDERICK ROBERT ALAN |
发明人 |
SHELTON MONTY LEE;WALLACE THOMAS TRACY;FREDERICK ROBERT ALAN |
分类号 |
F01D5/18;F01D9/02;F02C7/18;(IPC1-7):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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