A quasi-three-dimensional method for calculating blade surface velocities for an axial flow turbine blade
Quasi three-dimensional compressible flow analysis to determine aerodynamic velocity distribution on turbine blades
TURBINE BLADE↗
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Gas turbine efficiency as affected by discharge of coolant air from the stationary blades into the blading
Effects of vane air cooling discharge into turbine blading
BLADE↗
Experimental investigation of air-cooled turbine blade in turbojet engine VIII : rotor blades with capped leading edges
An air-cooled turbine blade with a capped leading edge was investigated in a modified commercial turbojet engine over a range of engine speed from 4000 to 11,350 rpm. The cooling performance of the caped-leading-edge configuration was superior to all leading-edge cooling modifications previously investigated.
TURBINE COOLING↗
Analytical investigation of supersonic turbomachinery blading. 1 - Computer program for blading design
FORTRAN computer program for supersonic turbomachinery blading design calculations
Goldman, L. J.↗
Analytical investigation of supersonic turbomachinery blading. 2 - Analysis of impulse turbine-blade sections
Surface Mach numbers, inlet flow angle, and specific heat ratio effects on geometric features of supersonic impulse turbine blade sections in Mach range 1.5 to 5.0
Goldman, L. J.↗
Experimental investigation of advanced concepts to increase turbine blade loading. 2 - Performance evaluation of plain rotor blade
Performance of single stage turbine with rotor blade surface diffusion factor of 0.3
Lueders, H. G.↗
Experimental investigation of advanced concepts to increase turbine blade loading. 3 - Performance evaluation of tandem rotor blade
Performance evaluation of tandem rotor blade of single stage turbine
Lueders, H. G.↗
Revised FORTRAN program for calculating velocities and streamlines on a blade to blade stream surface of a turbomachine
Computer program for aerodynamic analysis of turbomachine blades
Katsanis, T.↗
FORTRAN program for calculating velocities in a magnified region on a blade to blade stream surface of a turbomachine
FORTRAN computer program for detailed solution of compressible, subsonic, nonviscous flow at leading or trailing edges of blade surface
Katsanis, T.↗
Experimental investigation in an annular cascade sector of highly loaded turbine stator blading. Volume 3 - Performance of tandem blade
Performance of tandem turbine blade and its influence on flow separation and visualization
Bettner, J. L.↗
Experimental investigation of advanced concepts to increase turbine blade loading. 4 - Performance evaluation of plain rotor blade with plow type vortex generators
Performance evaluation of plain rotor blade with plow type vortex generators
Lueders, H. G.↗
Experimental investigation in an annular cascade sector of highly loaded turbine stator blading. Volume 2 - Performance of plain blade and effect of vortex generators
Aerodynamic characteristics of annular cascade of blades
Bettner, J. L.↗
Experimental investigation of advanced concepts to increase turbine blade loading. Part 6 - Performance evaluation of modified tandem rotor blade
Performance tests on single-stage turbine with modified tandem rotor blade
Lueders, H. G.↗
Cold-air investigation of a turbine with transpiration-cooled stator blades. 2 - Stage performance with discrete hole stator blades
Cold air tests on axial flow turbine with transpiration cooled discrete hole stator blades to determine coolant flow ejection effect on turbine aerodynamic performance
Behning, F. P.↗
Experimental investigation of advanced concepts to increase turbine blade loading. Volume 7 - Performance evaluation of modified jet-flap rotor blade
Single stage turbine performance with modified jet flap rotor blade
Lueders, H. G.↗
Cold air investigation of a turbine with transpiration cooled stator blades 4 - Stage performance with wire-mesh shell stator blading
Cold-air tests to determine performance characteristics of single-stage turbine with stator blades employing transpiration coolant ejection through wire mesh shell
Behning, F. P.↗
Overall and blade-element performance of a multiple-circular-arc bladed transonic compressor rotor with tip speed of 1375 feet per second
The design and experimental performance of a 20-inch-diameter multiple-circular-arc bladed axial-flow transonic compressor rotor is presented. Radial surveys of the flow conditions were made. At design speed the peak efficiency was 0.882 and occurred at a weight flow of 64.0 pounds per second. At this point the total-pressure and total-temperature ratios were 1.79 and 1.205, respectively. The stall margin at design speed was 8 percent based on weight flows and total-pressure ratios at experimental peak efficiency and near stall. The measured stall margin was 20 percent at design weight flow and speed.
Kovich, G.↗
Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 deg
A 51-cm-diam model of a fan stage for short haul aircraft was tested in a single stage compressor research facility. The rotor blades were set 7 deg toward the axial direction (opened) from the design setting angle. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed and a weight flow of 30.9 kg/sec, the stage pressure ratio and efficiency were 1.205 and 0.85, respectively. The design speed rotor peak efficiency of 0.90 occurred at a flow rate of 32.5 kg/sec.
Lewis, G. W., Jr.↗