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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Transonic stator with multiple circular arc airfoils and minimum curvature tested over range of flow angles and velocities - stator B
Transonic stator with double circular arc airfoils tested over range of flow angles and velocities
Multiple circular-arc slotted stator for transonic speed operation
Test on overall and blade element performance of single slotted 0.65 hub diffusion factor stator with self energized blowing boundary layer control
Performance tests of variable camber guide vane and stator to extend range of axial flow compressors
Boundary layer hub diffusion-factor stator blowing technique
Boundary layer bleed techniques for high lift compressor stator blades
Performance tests on slotted hub diffusion factor stator with boundary layer bleed
Aerodynamic performance, and noise measurements of highly loaded low speed fan
Characteristics of highly-loaded, high Mach number, single stage compressor
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol. 1
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol. 2
Inlet flow distortion testing of high Mach number transonic fan stages - Vol. 1
Test description and results for high Mach number transonic fan stages to determine range and distortion tolerance for various rotor tip casing treatment configurations
Slotted blades and vanes and rotor tip design for highly loaded, low speed fan stage applicable to low noise aircraft engines
Performance tests and efficiency measurement of hub-slit-suction stator in single stage compressor
Stage A, comprised of a conventional rotor and stator, was designed and tested to establish a performance baseline for comparison with the results of subsequent tests planned for two tandem-blade stages. The rotor had an inlet hub/tip ratio of 0.8 and a design tip velocity of 757 ft/sec. At design equivalent rotor speed, rotor A achieved a maximum adiabatic efficiency of 85.1 percent at a pressure ratio of 1.29. The stage maximum adiabatic efficiency was 78.6 percent at a pressure ratio of 1.27.
A single stage fan with a rotor tip speed of 1000 ft/sec(304.8 m/sec) and a hub-to-tip ratio of 0.392 was retested with a redesigned stator. Tests were conducted with uniform inlet, tip-radial, hub-radial, and circumferential inlet distortions. With uniform inlet flow, stall margin was improved 12 percentage points above that with the original stator. The fan demonstrated an efficiency of 0.883 and a stall margin of 15 percent at a pressure ratio of 1.488 and a specific flow of 41.17 lb/sec/sq ft. Tests were also made with a redesigned casing treatment consisting of skewed slots over the rotor blade tips. This casing treatment gave a 7 percentage point improvement in stall margin when tested with tip radial distortion (when the rotor tip initiated stall). Noise measurements at the fan inlet and exit indicate no effect from closing the stator 10 degrees, nor were there measurable effects from adding skewed slots over the blade tips.