AERODYNAMIC PERFORMANCE OF A THIRD STAGE PLENUM EVACUATION COMPRESSOR OF THE ARNOLD CENTER PROPULSION WIND TUNNEL
ARO INC ARNOLD AFS TN
Pagination or Media Count:
The aerodynamic performance of a third stage compressor of the Plenum Evacuaion System of the PROPULSION Wind Tunnel Facility was determined at inlet guide vane angle settings for minimum, deign, and maximum capaciies. In ddition to the noral steady-state pressure and flow measurements, transient measurements of the pressures in the ducs adjacent to the compresor were obtained uring definition of the compressor stll boundary. the compressor realized a maximm stall boundary pressure raio of 2.15 to 2.26 wth variation of inlet guide vane angle from 15 to -15 deg at an inlet temperature of 100 F. at the compressor design pressure ratio of 2.00 the measured inlet volume flow was 1285 and 1485 cfs at minimum 15 deg and maximum -15 deg inlet guide vane angle settings, respecively. The measured compressor aiabatic efficiency at the design condition was 87 percent. Measurements were aso obtained that defined a double-valued compressor characteristic, composed of the normal characteristic and a stalled branch of the characteristic.