Computer code for off-design performance analysis of radial-inflow turbines with rotor blade sweep
Peter L. Meitner, Arthur J. Glassman, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1983 - Technology & Engineering - 23 pages
The analysis procedure of an existing computer program was extended to include rotor blade sweep, to model the flow more accurately at the rotor exit, and to provide more detail to the loss model. This report describes the modeling changes and presents all analysis equations and procedures. Program input and output are described and are illustrated by an example problem. Results obtained from this program and from a previous program are compared with experimental data. (Author).
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01 PSIA ACTUAL area at station Blade-jet speed ratio calculated CLFR1 computer program conditions at station critical velocity ratio data input defined by eq defined by equation disk friction loss EBR3D enthalpy EOUIV EQUIV error message exit angle exit blade angle Glassman hydraulic diameter incidence loss input parameter input variables IOPTS ISPL ITERATIONS kinetic energy LBM/S Lewis Research Center linearly interpolates long output loss model Mach number MASS AVG mass flow rate MAX FLOW maximum value medium output NASA off-design performance pressure at station program input program of reference Radial-Inflow Turbines reference 1 code relative total pressure rotor back-sweep rotor blade sweep rotor choke rotor inlet rotor loss rotor trailing edge rotor viscous loss short output slip factor correlation static pressure stator and rotor stator exit Subroutine MAXVAL tangential component tip clearance loss torque total pressure drop total temperature U.S. customary units vaneless space loss