Aerodynamic effects of moveable sidewall nozzle geometry and rotor exit restriction on the performance of a radial turbineAttention is given to the experimental results obtained with a high work capacity radial inflow turbine of known performance, whose baseline configuration was modified to accept a variety of movable nozzle sidewall, diffusing or accelerating rotor inlet ramp, and rotor exit restriction ring combinations. The performance of this variable geometry turbine was measured at constant speed and pressure ratio for 31 different test configurations, yielding test data over a nozzle area range from 50 to 100 percent of maximum depending on the movement of the nozzle assembly's forward and rearward sidewalls. Performance comparisons with data for a variable stagger angle vane concept indicate the present system's viability.
Document ID
19840046673
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rogo, C. (Teledyne CAE Toledo, OH, United States)
Hajek, T. (Teledyne CAE Toledo, OH, United States)
Roelke, R. (NASA Lewis Research Center Cleveland, OH, United States)