| 摘要 |
A gas turbine (1), in particular for model aircraft, model helicopters and other small propulsion units, comprising a drive shaft (3) rotatably mounted by means of two main bearings (13, 13') and extending through an annular combustion chamber (2) and to which a compressor impeller (4) and a turbine wheel (11) are non-rotationally connected, and a driven shaft (14) driven by said drive shaft (3), wherein a device comprised of front toothed wheels is provided for transmitting the torque from the drive shaft (3) to the driven shaft (14) between the two main bearings (13, 13').
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