| 摘要 |
This gas turbine is of the type of those including a first and a second ejection nozzle spaced from one another and capable of pivoting so as to allow vertical or very short take-off of the aircraft. The air leaving a compressor 10 is divided (at 11A) in order to feed a first combustion chamber 17, the exhaust of which takes place through the first ejection nozzle 15, and a second combustion chamber 21, the exhaust of which takes place through the second ejection nozzle 27. A passage 11, 11A between the compressor and the first combustion chamber is connected to another passage 24 between the second combustion chamber and the second nozzle. The connection takes place by means of a pipe 30, in which a valve 31 is mounted. In a typical operating mode, the two chambers are in service and the valve is open so that part of the air leaving the compressor towards the first chamber is deflected onto the second nozzle. If the first chamber is not operating, the valve is closed in order to increase the mass flow rate through the first nozzle and keep the thrust ratio between the two nozzles constant and thus maintain the attitude (trim) of the aircraft. In the latter, the nozzles are placed respectively in front of and behind the centre of gravity of the device. The valve may be utilised for adjusting the attitude. <IMAGE> |
