发明名称 |
An airfoil profile with optimized aerodynamic shape |
摘要 |
<p>Provided is an aerodynamic profile for use in gas turbine airfoil (28) and a turbine blade (12) comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections (42) forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line (44) extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line (44) with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.</p> |
申请公布号 |
EP1621729(A2) |
申请公布日期 |
2006.02.01 |
申请号 |
EP20050254743 |
申请日期 |
2005.07.28 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
FUKUDA, TAKAO;MAGGE, SHANKAR S.;PRICE, FRANCIS R. |
分类号 |
F01D5/14 |
主分类号 |
F01D5/14 |
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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