Turbojet Thrust Augmentation by Sudden Expansion Type Afterburner

摘要

An axisymmetric sudden expansion afterburner coupled to a small turbojet engine in various configurations, has been studied. The effects of length to diameter ratio variation on performance were investigated. The maximum thrust achieved was 62 pounds without afterburner augmentation, and 92 pounds with afterburner augmentation, each with turbine inlet temperature of 1700F. Various methods of air injection into the combustion zone of the afterburner were examined, and found to be ineffective for purpose of thrust augmentation. An eccentrically mounted afterburner with an eccentricity of 1.25 inch has been operated successfully. The performance of the propulson system decreased in this configuration onlyby a negligible amount. (Author)