发明名称 |
GAS TURBINE ENGINE TURBINE BLADE AIRFOIL PROFILE |
摘要 |
<p>A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.</p> |
申请公布号 |
WO2014007939(A1) |
申请公布日期 |
2014.01.09 |
申请号 |
WO2013US44677 |
申请日期 |
2013.06.07 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
NASH, TIMOTHY CHARLES |
分类号 |
F02C7/00;F01D5/00;F01D5/30 |
主分类号 |
F02C7/00 |
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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