Turbojet engines are the first to appear in gas turbine engines. Its main features are large reasoning, light weight, and the ability to adapt to high-speed and high-altitude flights. It was the emergence of the turbojet engine that enabled the aircraft to break the "tone barrier" and achieve supersonic flight. However, it also has the disadvantages of high fuel consumption and large energy loss.
The turboprop engine is produced to overcome the shortcomings of the turbojet engine with high fuel consumption. Its main features are low energy loss, high propulsion efficiency and low fuel consumption. However, it also has obvious disadvantages. The flight speed is not fast, and it can only be used for aircraft with Mach number Ma=0.5~0.7. (Mach number Ma is the ratio of the flight speed of the aircraft to the local speed of sound).
The turbofan engine is an engine in which the exhaust gas discharged from the tail pipe and the air accelerated by the fan jointly generate thrust. Its main features are small jet velocity, low noise, low fuel consumption, etc. However, due to the high bypass ratio of the turbofan engine, the windward area is large and the jet velocity is small, which is not suitable for supersonic flight. It is mainly used for various types of civil aviation aircraft.
The turboshaft engine is mainly used for helicopters. The shaft power output from the engine is decelerated and turned by the reducer, driving the rotor to rotate, and the air is discharged downward and backward, generating upward and forward force to make the helicopter fly.
A paddle engine (sometimes referred to as a no-duct engine or an ultra-high-flow ratio turbofan engine) combines the economics of a turboprop engine with the high speed of a turbofan engine to create a new engine. However, due to the high R&D expenses, companies have stopped researching them.
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