Analytical Investigation of Supersonic Turbomachinery Blading: Analysis of impulse turbine-blade sectionsNational Aeronautics and Space Administration, 1968 - Turbomachines |
Common terms and phrases
AA and CC arc CD BD arc Straight line arcs AB Upper axial Mach number BD Lower transition Blade design limitations blade sections blade solidities BLADING II CC Circular arcs CD BD Lower consideration of supersonic design parameters figure 14 flow angle ß₁ flow separation problems flow turning angle geometric characteristics impulse turbine-blade sections increase the solidity Inlet and outlet inlet flow angle inlet Mach number inlet Prandtl-Meyer angle Lower transition arc lower-surface Mach number Lower-surface Prandtl-Meyer angle M₁ Mach number level Mach number range Maximum inlet Prandtl-Meyer outlet Mach numbers outlet Prandtl-Meyer angles ratios of 1.3 separation criterion shapes at inlet shown in figure similar surface Mach specific-heat ratio subsonic values supersonic starting criterion surface Mach number surface Prandtl-Meyer angle total flow turning transition arc CD transition arc Straight Turbine-blade shapes u)max Upper transition arc upper-surface Mach number upper-surface Prandtl-Meyer angle Vi)max vortex flow conditions Yes Yes Yes