Abstract: A small gas turbine, in particular for powering airplane models, provided with a casing (3), a compressor rotor (1, 2), a combustion chamber (15-17) and a turbine rotor (5), the turbine rotor (5) driving the compressor rotor(1, 2) by a shaft positioned in a shaft tunnel extending through the combustion chamber (15-17) and surrounded by a helical fuel feed and vaporizing tube (22, 23), the combustion chamber (15-17) being defined by a cylindrical outer wall (15) and a frusto-conical inner wall (16) provided with combustion air intake orifices (19-21)the outlet side of the inner wall (16) of the combustion chamber extending into a cylindrical flow element (6, 7) forming an annular gap therewith, which in turn extends into the center opening of the turbine side guide vane ring (4) and is supported by the end (9) of the shaft tunnel (8), and the other end of the shaft tunnel (8) being secured to the casing (3) between the compressor rotor (1, 2) and the front wall (17) of the combustion chamber.