24 research outputs found
Two-dimensional Cascade Investigation of the Maximum Exit Tangential Velocity Component and Other Flow Conditions at the Exit of Several Turbine Blade Designs at Supercritical Pressure Ratios
The nature of the flow at the exit of a row of turbine blades for the range of conditions represented by four different blade configurations was evaluated by the conservation-of-momentum principle using static-pressure surveys and by analysis of Schlieren photographs of the flow. It was found that for blades of the type investigated, the maximum exit tangential-velocity component is a function of the blade geometry only and can be accurately predicted by the method of characteristics. A maximum value of exit velocity coefficient is obtained at a pressure ratio immediately below that required for maximum blade loading followed by a sharp drop after maximum blade loading occurs
Turbine-rotor-blade Designs Based on One-dimensional-flow Theory I : Performance of Single-stage Turbine Having 40-percent Reaction
Experimental Investigation of Effect of High-aspect-ratio Rotor Blades on Performance of Conservatively Designed Turbine
A Two-dimensional Cascade Study of the Aerodynamic Characteristics of a Turbine-rotor Blade Suitable for Air Cooling
Experimental Investigation of a High Subsonic Mach Number Turbine Having High Rotor Blade Suction-surface Diffusion
Investigation of high subsonic turbine with high rotor blade suction-surface diffusio
Comparison of results of experimental and theoretical studies of blade-outlet boundary-layer characteristics of stator blade for a high subsonic Mach number turbine
Experimental Investigation of a High Subsonic Mach Number Turbine Having Low Rotor Suction-surface Diffusion
The quasi-three-dimensional method for the aerodynamic design of both stator and rotor blades is presented for a turbine having high weight flow and high specific work output. The turbine was designed for a relative critical velocity ratio of 0.82 at the rotor hub inlet. At the condition of equivalent design work output and blade speed, the efficiency based on the overall actual total-pressure ratio was 0.875, which is almost at high as those obtained for conservatively designed turbines
Study of Flow Conditions and Deflection Angle at Exit of Two-dimensional Cascade of Turbine Rotor Blades at Critical and Supercritical Pressure Ratios
Experimental Investigation of a High Subsonic Mach Number Turbine Having a 40-blade Rotor with Zero Suction-surface Diffusion
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NACA Research Memorandums
The quasi-three-dimensional method for the aerodynamic design of both stator and rotor blades is presented for a turbine having high weight flow and high specific work output. The turbine was designed for a relative critical velocity ratio of 0.82 at the rotor hub inlet. At the condition of equivalent design work output and blade speed, the efficiency based on the overall actual total-pressure ratio was 0.875, which is almost at high as those obtained for conservatively designed turbines