Abstract: A jet engine, comprising a long, tube-shaped casing open at both ends, a shaft supported centrally in the casing, a compressor and gas turbine rigidly connected to the shaft, and a combustion chamber with fuel supply located between the compressor and turbine. The engine is equipped with two coaxial compressors with radial blades. The compressors are separated by a backwardly-diverging, conical partition, by a radial turbine disposed immediately back of the compressor in connection with the back end of the conical partition. A rear wall is disposed in back of the turbine. The combustion chamber is bound by said wall, said conical partition and the turbine blades.