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Off-design performance loss model for radial turbines with pivoting, variable-area statorsAn off-design performance loss model was developed for variable stator (pivoted vane), radial turbines through analytical modeling and experimental data analysis. Stator loss is determined by a viscous loss model; stator vane end-clearance leakage effects are determined by a clearance flow model. Rotor loss coefficient were obtained by analyzing the experimental data from a turbine rotor previously tested with six stators having throat areas from 20 to 144 percent of design area and were correlated with stator-to-rotor throat area ratio. An incidence loss model was selected to obtain best agreement with experimental results. Predicted turbine performance is compared with experimental results for the design rotor as well as with results for extended and cutback versions of the rotor. Sample calculations were made to show the effects of stator vane end-clearance leakage.
Document ID
19810002530
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Meitner, P. L. (NASA Lewis Research Center Cleveland, OH, United States)
Glassman, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AVRADCOM-TR-80-C-13
NASA-TP-1708
E-455
Accession Number
81N11038
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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