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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... critical velocity ratios of 0. 57 to 0.90 . The design value for the vane is 0. 778. Vane surface static - pressure distributions were measured and corresponding critical velocity ratios were compared with theoretical results . The ...
... critical velocity ratios of 0. 57 to 0.90 . The design value for the vane is 0. 778. Vane surface static - pressure distributions were measured and corresponding critical velocity ratios were compared with theoretical results . The ...
Page 10
... critical velocity ratio . The difference in the mean radius and overall aftermixed efficiencies is 0.018 ( i . e . , 0.978 0.960 ) at design critical velocity ratio and is due to end wall and secondary flow losses . Second- ary flow ...
... critical velocity ratio . The difference in the mean radius and overall aftermixed efficiencies is 0.018 ( i . e . , 0.978 0.960 ) at design critical velocity ratio and is due to end wall and secondary flow losses . Second- ary flow ...
Page 11
... critical velocity ratios of 0. 57 to 0.90 . The design value for the vane is 0.778 . Vane surface static - pressure distri- butions were measured and corresponding critical velocity ratios were compared with theoretical results . The ...
... critical velocity ratios of 0. 57 to 0.90 . The design value for the vane is 0.778 . Vane surface static - pressure distri- butions were measured and corresponding critical velocity ratios were compared with theoretical results . The ...
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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