Effect of stage spacing on performance of 3.75-inch-mean-diameter two-stage turbine having partial admission in the first stage
William J. Nusbaum, Robert Young Wong, Lewis Research Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1964 - Technology & Engineering - 22 pages
"The design and the experimental investigation of a 3.75-inch-mean-diameter partial-admission two-stage turbine are presented herein. The investigation was made to determine the effect on two-stage-turbine performance of a change in the axial distance between stages for a turbine with partial admission in the first stage. Accordingly, the turbine was designed with 31.3-percent admission in the first stage, full admission in the second stage, and provision for changing the axial distance between stages. The results of the two-stage investigation are presented for each of the axial distances between stages of 0.25, 0.50, 0.75, 1.00, 1.50, and 2.00 inches. The results of the first-stage investigation are also presented, together with a calculated efficiency for the second stage, at each value of stage spacing as calculated from the two-stage and first-stage results."--P. .
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3.75-INCH-MEAN-DIAMETER TWO-STAGE TURBINE 31.3-percent admission airbrake arc of admission axial distance Axial-Flow calculated D-2335 National Aeronautics design speed design value diffusion parameter distance between stages distance of 2.00 edge of second-stage EFFECT OF STAGE efficiency from 0.584 equivalent weight flow experimental investigation first-stage rotor first-stage stator free-stream velocity diagrams full admission horsepower inch increase in efficiency increased from 0.25 inlet collector inlet total pressure jet-speed ratio Lewis Research Center load cell NASA TN Nusbaum and Robert overall pressure ratio PARTIAL ADMISSION Performance characteristics PERFORMANCE OF 3.75-INCH-MEAN-DIAMETER presents the design pressure-surface second stage second-stage rotor second-stage stator shown in figure SPACING ON PERFORMANCE specific work output stage and full STAGE SPACING stages of 0.25 stages was increased stagger angle static pressure static to inlet station just upstream tance between stages TECHNICAL NOTE D-2335 torque total-to-static efficiency trailing edge trailing-edge radius TURBINE HAVING PARTIAL two-stage investiga upstream of trailing value of blade Wong