抄録
The influence of propelling nozzle exit area on a turbo jet engine performance has been investigated in this paper. The experiments have been conducted for a small turbo jet engine with a standard propelling nozzle and six different nozzles whose nozzle exit areas were varied by ±5%,±10%,±15% from that of the standard nozzle. It has been observed that the running lines on the compressor performance map for enlarged propelling exit areas have been moved away from the surge line, resulting in lowering turbine inlet temperatures and hence specific thrusts as well. On the other hand, the reduction of propelling nozzle exit area has caused the opposite effect for the running lines.
