Determination of Rotor and Stator Loss Coefficients for an Axial Turbine with Supersonic Stator Exit Conditions.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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The results of seven different tests of a single stage axial turbine with converging-diverging stator nozzle are reported. From measurements in a special test rig, losses occurring in the stator and rotor blade rows were separately calculated and the performance of the stage was also determined. The rotor speeds varied from 9,500 to 18,600 r.p.m. and the pressure ratios varied from 1.75 to 3.25. The Mach numbers at the stator exit varied from 0.79 to 1. 38. The results for this turbine are appraised and a procedure is demonstrated for smoothing loss coefficient data from the turbine rig.
- Hydraulic and Pneumatic Equipment