The presented overall aero-thermodynamic cycle analysis and engine flight altitude-velocity performance simulation revealed that with a group of well compromised parameters

the micro-turbofan engines with today commonly used low pressure ratio is still efficient for a lower specific fuel consumption(SFC) than that of turbojet.Furthermore

to resolve the difficulties of complex structure in micro-turbofan engines

a newly conceived integral fan-compressor component with both high-low blades and splitter blades is claimed.The features of the aerodynamic design and structural design of the new type fan-compressor component are introduced briefly.Finally one of the principia overall structure design of this kind of turbofan engine was worked out.