Cold-air Annular-cascade Investigation of Aerodynamic Performance of Core-engine-cooled Turbine VanesNational Aeronautics and Space Administration, 1975 - Aircraft gas-turbines |
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... VANES I - SOLID - VANE PERFORMANCE AND FACILITY DESCRIPTION by Louis J. Goldman and Kerry L. McLallin Lewis Research Center SUMMARY The aerodynamic performance of a solid ( uncooled ) version of a core engine cooled stator vane was ...
... VANES I - SOLID - VANE PERFORMANCE AND FACILITY DESCRIPTION by Louis J. Goldman and Kerry L. McLallin Lewis Research Center SUMMARY The aerodynamic performance of a solid ( uncooled ) version of a core engine cooled stator vane was ...
Page 2
... performance of the solid core turbine stator vanes ( full size ) , tested in a two - dimensional cascade , has been reported in reference 2. These results , although indicative of the vane performance at the mean section , do not ...
... performance of the solid core turbine stator vanes ( full size ) , tested in a two - dimensional cascade , has been reported in reference 2. These results , although indicative of the vane performance at the mean section , do not ...
Page 11
... vane is 0.778 . Vane surface static - pressure distri- butions were measured and corresponding critical velocity ratios were compared with theoretical results . The variation in vane efficiency and aftermixed flow conditions with ...
... vane is 0.778 . Vane surface static - pressure distri- butions were measured and corresponding critical velocity ratios were compared with theoretical results . The variation in vane efficiency and aftermixed flow conditions with ...
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Common terms and phrases
Aerodynamic Performance aftermixed critical velocity aftermixed flow angle annular cascade axial chord bellmouth Blade calculated cascade facility centimeter combination probe computer program conservation of mass critical velocity ratio design critical velocity design value downstream end wall boundary End wall total exit flow angle FORTRAN full-annular cascade hub and tip ideal after mixed ideal aftermixed critical incidence angles inlet station Lewis Research Center mean radius mean section mixed critical velocity mixed flow angle NASA TN overall aftermixed efficiency pressure ratio range Rotor secondary flow losses shown in figure solid uncooled solid vanes static pressure suction surface surface critical velocity survey plane station test section test vanes theoretical results tip wall total pressure probe TSONIC program Experimental two-dimensional cascade vane efficiency Vane exit vane height vane inlet vane passage vane performance vane surface critical vane trailing edge velocity ratio distributions vortex core W/Wcr wall boundary layers wall total pressure азм