Patent ID: 7021043

Claim:
A jet engine comprising: a body; a burner installed in the body to inject and burn fuel in compressed air; a high-pressure turbine having a plurality of rotors, the high-pressure turbine being rotated by high-pressure exhaust gas discharged from the burner; a low-pressure turbine having a plurality of rotors, the low-temperature turbine being rotated by low-pressure exhaust gas passing through the high-pressure turbine; a rotary shaft combined to gyratory centers of the high-pressure turbine and the low-pressure turbine; and a fan combined with the rotary shaft at the rear of a last rotor of the low-pressure turbine to rotate together with the rotary shaft in order to provide propulsive force in the exhaust gas, discharged through the low-pressure turbine from the burner, wherein the fan is substantially parallel to a tail portion of the last rotor of the low-pressure turbine at a head portion thereof and curved rearwardly at a tail portion thereof in order to change the lateral component of velocity of the exhaust gas, passing through the low-pressure turbine, to be directed in an axial direction to the utmost when rotating.