Prediction of Compressor Stage Performance From Choke Through Stall

The results of an investigation in which the predicted aerodynamic performance of the NASA Stage35 singlestage compressor is compared with the measured experimental data over the entire design speedline from choke through stall are presented. Particular attention has been given to the geometric model and boundary conditions in the numerical study to enable the aerodynamic performance to be predicted through stall. The total pressure ratios of both the rotor and stator as well as circumferential profiles of the total pressure and total temperature up- and downstream of the rotor are compared with experimental data. A time-accurate approach for predicting stall inception caused by both long- and short-wave length phenomena is introduced. The results from a series of Stage35 unsteady-flow simulations near stall with this approach are presented to demonstrate the flow physics responsible for stall inception.