| 摘要 |
This propulsion system for aircraft comprises gas turbine jet engines, which in accordance with Fig. 1 have two separate combustion devices (11) and (12) and three flow circuits for generating thrust, which circuits obtain their flow energy from a crossflow fan (17) connected on the inlet side, the rollers (13) and (18) of which are driven by a turbofan (14), which is acted upon by the gas jets both of the main flow circuit (8) and of the by-pass flow circuit (9). An axial displacement of the rollers deprives the main flow circuit of energy and results in connection of the radial flow circuit (10), which is located in a swivelling flow housing (19), mounted perpendicular to the engine longitudinal axis and serves for generating the radial or vertical thrust. In this switching process, however, the horizontal thrust of the by-pass flow circuit remains undiminished. Furthermore, this propulsion system has no air inlet apertures pointing in the direction of flight, since the intake mouth (5) of the air inlet section (6) is directed towards the tail and draws the operating air for the crossflow fan from the mixing flow of the thrust jet. <IMAGE>
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