Performance Optimization of Mini-Jet Engine

Abstract

This paper describes optimization of specific fuel consumption (SFC) of mini-jet engine with two parameters: inlet Mach number (M₁) and compressor pressure ratio (Pr). And also optimum design line is described. The designated mini-jet engine is 47 N in thrust, 62700 rpm in revolution, and 100 mm in diameter, 180 mm in length. The maximum thrust (F) is 75 N, maximum revolution (N) is 120000 rpm and maximum turbine inlet temperature (TIT, T₀₅) is 900 K.