TRANSIENT AND STEADY-STATE PERFORMANCE OF A SINGLE TURBOJET COMBUSTOR WITH FOUR DIFFERENT FUEL NOZZLES

摘要

Acceleration and steady-state performance of a single tubular com-bustor operating with four different fuel nozzles were determined at two simulated altitude, part-throttle conditions. The nozzles were the dual-entry duplex nozzle usually used in this combustor, a single-entry duplex type, and two simplex nozzles. Additional tests were made over a range of initial fuel flows (heat-release rate) while maintaining the combustor-inlet air variables constant at the two altitude - engine speed conditions.