Single-stage experimental evaluation of boundary layer blowing techniques for high lift stator blades. 1 - Compressor design
Boundary layer blowing techniques for high lift stator blades in axial flow compressors
Chapman, D. C.↗
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Single-stage experimental evaluation of boundary layer bleed techniques for high lift stator blades. Compressors design
Design and evaluation of stator blades for use in boundary layer bleed techniques in axial flow compressor
Chapman, D. C.↗
Single stage experimental evaluation of variable geometry guide vanes and stators. Part 1 - Analysis and design
Variable geometry concepts applied to guide vanes and stators in single stage compressors
Jones, B. A.↗
Single stage experimental evaluation of slotted rotor and stator blading, part 9 Final report
Slotted axial flow compressor rotor and slotted stator tests of slot effect on performance of highly loaded blades
Rockenbach, R. W.↗
Experimental investigation in an annular cascade sector of highly loaded turbine stator blading. Volume 1 - Analysis and design
Application of boundary layer control concepts to highly loaded turbine stator blades in annular cascades
Bettner, J. L.↗
Experimental evaluation of transonic stators Final report
Blade performance of transonic compressor stators
Bartok, J. A.↗
Some measurement problems encountered when determining the performance of certain turbine stator blades from total pressure surveys.
Turbine stator blade performance determination from total pressure surveys downstream of blade row, noting problems in pressure measurement
Moffitt, T. P.↗
Performance of a single-stage turbine as affected by variable stator area.
Stator setting effect on single stage turbine performance, considering blade loss and surface velocity distribution
Moffitt, T. P.↗
Single stage experimental evaluation of variable geometry inlet guide vanes and stator blading, part 6 Final report
Variable geometry inlet guide vanes and stators for extending stable operation of supersonic cruise turbine engine compressor front stage
Jones, B. A.↗
Design and Two-Dimensional Cascade Test of Turbine Stator Blade with Ratio of Axial Chord to Spacing of 0.5
Design and performance of very low-solidity turbine stator blades for first stage jet engine turbine with velocity and pressure diagrams
Stabe, Roy G.↗
Thermal feasibility of using methane or hydrogen fuel for direct cooling of a first-stage turbine-stator
Methane or hydrogen fuel direct cooling of first stage stator of SST aircraft turbine - numerical heat transfer analysis
Colladay, R. S.↗
Split stator vane row for fans and compressors
Operating noise of fans is reduced by adding part span vanes to vane row of stator, reducing the number of full span vanes and maintaining a vane-to-blade ratio of about 2 to 1.
Volk, L. J.↗
Experimental investigation in an annular cascade sector of highly loaded turbine stator blading. 5 - Performance of two tangential jet blades
Testing low reaction jet turbine stator blades in six-blade annular cascade
Bettner, J. L.↗
Single stage experimental evaluation of boundary layer blowing and bleed techniques for high lift stator blades, 5 Final report
Determining feasibility of increasing stator blade loading of single stage compressor rig by bleeding or blowing suction surface boundary layer
Horn, R. A., Jr.↗
Analytical study of the effects of geometric changes on the flow characteristics of tandem- bladed compressor stators
Analytical investigation of effects of geometric changes on flow characteristics of tandem bladed compressor stators
Sanger, N. L.↗
Single stage evaluation of highly loaded high Mach number compressor stages. 4: Data and performance of hub slit suction stator
Performance tests and efficiency measurement of hub-slit-suction stator in single stage compressor
Burger, G. D.↗
Design and two dimensional cascade test of a jet-flap turbine stator blade with ratio of axial chord to spacing of 0.5
A jet-flap blade was designed for a velocity diagram typical of the first-stage stator of a jet engine turbine and was tested in a simple two-dimensional cascade of six blades. The principal measurements were blade surface static pressure and cross-channel surveys of exit total pressure, static pressure, and flow angle. The results of the experimental investigation include blade loading, exit angle, flow, and loss data for a range of exit critical velocity ratios and three jet flow conditions.
Stabe, R. G.↗
Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part 2: Data and performance for stage A
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.
Brent, J. A.↗