This paper describes optimization of specific fuel consumption (SFC) of mini-jet engine with two ... more This paper describes optimization of specific fuel consumption (SFC) of mini-jet engine with two parameters: inlet Mach number (M 1 ) 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, T 05 ) is 900 K.
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
This paper describes optimization of specific fuel consumption (SFC) of mini-jet engine with two ... more This paper describes optimization of specific fuel consumption (SFC) of mini-jet engine with two parameters: inlet Mach number (M 1 ) 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, T 05 ) is 900 K.
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
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