"Prepared for the 41st Gas Turbine and Aeroengine Congress sponsored by the International Gas Turbine Institute of the American Society of Mechanical Engineers, Birmingham, United Kingdom, June 10-13, 1996."
"Performing organization: NASA Lewis Research Center and Vehicle Propulsion Directorate, U.S. Army Research Laboratory"--Report documentation page.
Includes bibliographical references (page 7).
Sponsored by the National Aeronautics and Space Administration and U.S. Army Research Laboratory WU-505-62-0L E-10477
APPROVED FOR PUBLIC RELEASE.
A Dynamic Turbine Engine Compressor Code (DYNTECC) has been modified to model speed transients from 0-100% of compressor design speed. The impetus for this enhancement was to investigate stage matching and stalling behavior during a start sequence as compared to rotating stall events above ground idle. The model can simulate speed and throttle excursions simultaneously as well as time varying bleed flow schedules. Results of a start simulation are presented and compared to experimental data obtained from an axi-centrifugal turboshaft engine and companion compressor rig. Stage by stage comparisons reveal the front stages to be operating in or near rotating stall through most of the start sequence. The model matches the starting operating line quite well in the forward stages with deviations appearing in the rearward stages near the start bleed. Overall, the performance of the model is very promising and adds significantly to the dynamic simulation capabilities of DYNTECC.