Design and Development of Supersonic Turbine Nozzles
Final engineering rept. Oct 1970-1971
GENERAL APPLIED SCIENCE LABS INC WESTBURY NY
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A nozzle stator component for a supersonic turbine stage has been designed and tested. The design was three-dimensional, with the nozzle exit Mach number varying from 1.68 at the hub to 2.23 at the tip, according to simple- radial-equilibrium theory. The hubtip ratio was .83, and the aspect ratio .35, with a 1-inch blade height. The supersonic contour was based on the Busemann sharp-edged-throat concept. The nozzle was tested over a range of pressure ratios from 1.9 to 10.5 and Reynolds numbers from 650,000 to 3,800,000, based on exit conditions and the blade chord. A blow-down wind tunnel was used, with atmospheric discharge. The performance of the nozzle corresponded well to theoretical predictions in the regions of the exit flow that were traversed and along the walls where pressure taps were installed. The test program was terminated before a complete map of the exit flow had been obtained, because of vibratory cracks in some of the blades.
- Fluid Mechanics
- Jet and Gas Turbine Engines