The Transonic Turbine Test Rig installed in the Turbo-Propulsion Laboratory at the Naval Postgraduate School was designed such that losses in nozzles and rotor blading and overall performance characteristics can be determined for operation at several combinations of blade configurations, pressure ratios and speeds. This study relates the empirical data for stator loss coefficients to those determined for the converging-nozzle stator presently installed, and discusses reasons for some of the discrepancies. Also discussed are results of the flow nozzle calibration, locked rotor data, and temperature and inlet swirl effects. A method is proposed to reduce these effects for future work on the Turbine Test Rig.

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http://archive.org/details/aninvestigationo1094512496

Captain, Canadian Armed Forces