发明名称 Nozzle blade airfoil profile for a turbine
摘要 First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.
申请公布号 US2007177981(A1) 申请公布日期 2007.08.02
申请号 US20060340577 申请日期 2006.01.27
申请人 GENERAL ELECTRIC COMPANY 发明人 VANDEPUTTE THOMAS W.;GREENE JOHN E.;SELENT PETER C.;FARRAL LINDA J.;CHAN SZE BUN B.;ARNESS BRIAN P.
分类号 B64C27/46 主分类号 B64C27/46
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