PERFORMANCE ANALYSIS OF A ROTARY NOZZLE UTILIZING A 30DEG SPIN ANGLE ROTOR,

摘要

Static thrust augmentation experiments have been performed with a rotary nozzle induction device to determine the effect of a large spin angle on performance. A 30deg spin angle rotor with a shroud area to primary nozzle exit area ratio of 19.6was tested over a primary to secondary pressure range of 1.2to 1.8at a primary-secondary temperature ratio of 1.0. (Author)