Simulation of three-dimensional viscous flow within a multistage turbineThis work outlines a procedure for simulating the flow field within multistage turbomachinery which includes the effects of unsteadiness, compressibility, and viscosity. The associated modeling equations are the average passage equation system which governs the time-averaged flow field within a typical passage of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and a one-half turbine will be presented and compared with experimental measurements. It will be shown that the secondary flow field generated by the rotor causes the aerodynamic performance of the downstream vane to be significantly different from that of an isolated blade row.
Document ID
19900036786
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adamczyk, John J. (NASA Lewis Research Center Cleveland, OH, United States)
Celestina, Mark L. (NASA Lewis Research Center Cleveland, OH, United States)
Beach, Tim A. (NASA Lewis Research Center; Sverdrup Technologies, Inc. Cleveland, OH, United States)
Barnett, Mark (United Technologies Research Center East Hartford, CT, United States)