A turbojet is a turbine engine. The characteristic is that it relies entirely on gas flow to generate thrust. Typically used to power high-speed aircraft, but have higher fuel consumption than turbofan engines. Turbojet engines are divided into two types: centrifugal and axial flow. The centrifugal engine was invented by the British Sir Frank Whittle in 1930. However, it was not until 1941 that an aircraft equipped with this engine took to the sky for the first time, and it did not participate in the competition. World War II; the axial-flow type was born in Germany and entered the battlefield in the summer of 1944 as the power of the first practical jet fighter Me-262. Compared with centrifugal turbojet engines, axial flow engines have the advantages of small cross-section and high compression ratio. Most of today's turbojet engines are axial flow engines.

Basic parameters
Thrust to weight ratio: represents the ratio of engine thrust to the weight of the engine itself. The greater the value, the better the performance.
Compressor stage: represents the number of stages of compression blades of the compressor. Generally, the larger the stage, the greater the compression ratio.
Turbine stages: represents the number of stages of turbine blades in the turbine.
Compression ratio: The ratio of the pressure of the inlet air after being compressed by the compressor to the pressure before compression. Generally, the greater the pressure, the better the performance.
Maximum net thrust at sea level: The thrust generated by the engine operating at full speed at sea level altitude and conditions when the speed difference (airspeed) with the outside air is zero. The units used include kN (kilonewtons) and kg (kilograms). , lb (pounds), etc.
Fuel consumption per unit thrust per hour: also called specific thrust, the ratio of fuel consumption to thrust. The metric unit is kg/N-h. The smaller the fuel consumption, the more fuel-efficient it is.
Temperature in front of the turbine: the temperature before the high-temperature and high-pressure airflow enters the turbine after combustion. Generally, the higher the temperature, the better the performance.
Gas outlet temperature: The temperature of the exhaust gases as they leave the turbine.
Mean time to failure: The total average time between two failures of each engine. The longer the engine, the less likely it is to fail and generally the lower the maintenance cost.