Air inlet, especially a two-dimensional air inlet set at an angle on one side for gas turbine jet propulsion plants for driving airplanes

In an air inlet for a gas turbine, especially a two-dimensional air inlet set at an angle on one side for gas turbine jet propulsion plants for driving airplanes, having an air inlet channel curved in space, especially double curved, and leading to the compressor of the propulsion plant, and further having, especially one, inlet cross-section for the supersonic operation controllable by means of adjustable ramps arranged overhead which are in the raised position during subsonic operation and which are tilted down during supersonic operation, so that a variable, convergent-divergent air inlet geometry is produced in the air inlet, the improvement comprising at least one flow guide fence (12) arranged in the zone of the air inlet channel (9) in which, due to flight conditions particularly angles of attack of the aircraft used in flight, a separation flow (Sa1) occurs, said flow guide fence (12) reaching substantially radially into said air inlet channel to an extent just sufficient to avoid disadvantages of said separation flow, said flow guide fence following particularly the longitudinal central plane (M) of the air inlet channel, said flow guide fence having an upstream end located in the area of the beginning of the channel curvature and a downstream end extending at least to the end of the channel curvature, said downstream end extending, in case of a doubly bent, air inlet channel (9 or 10, 11) at least to the turning point (W) in the curvature.