The main structure of the axial-flow turbojet engine figure, air first enters the inlet, because the flight state is changing, need to ensure that the air inlet can finally enter the next structure smoothly: compressor (compressor). The main function of the inlet is to adjust the air to the engine before it enters the compressor. In supersonic flight, head and gas inlet will produce shock wave (shockwave), after the air wave pressure will be increased, so the inlet can play a role of pre compression, uneven but inappropriate shock position will cause local pressure, there may even damage the compressor. Therefore, the inlet of an ordinary supersonic aircraft has a shock wave adjusting cone, and the position of the shock wave is adjusted according to the speed of the air.
Compared to centrifugal turbojet engines, axial flow has the advantage of small cross section and high compression ratio, but requires higher quality material which does not exist around 1945. Today's turbojet engines are axial flow type.
Turbojet engine is divided into centrifugal and axial flow type two, centrifugal made by Sir Frank Whittle in 1930 the British invention patent, but until 1941 with this engine was the first aircraft to heaven, did not participate in the Second World War, Kaplan was born in Germany, and as a kind of practical power of the first jet fighter Me-262 participated in the battle at the end of 1944.
A typical axial flow turbo jet engine (blue arrow diagram for the air flow) picture: 1 - 2 - low suction, compression, 3 - 4 - high pressure compressor, combustion, exhaust 5 -, 6 - hot region, 7 - 8 - turbine combustor, 9 cold region, 10 - the air inlet turbo jet engine (Turbojet) (referred to as the turbojet engine) is a kind of [1] turbine engine. The utility model is characterized by completely relying on the gas flow to generate thrust. Power usually used as a high speed aircraft. The fuel consumption is higher than the turbofan engine.
