Device and method for reducing nonsteady side loads acting on a rocket nozzle
|510 - Abstract:|
|A rocket nozzle comprises a combustion chamber where exhaust gases are generated, a divergent portion in which supersonic flow of exhaust gases occurs and a throat connecting the combustion chamber to the divergent portion. The offered technology reduces nonsteady side loads acting on this nozzle during the startup phase. Industrial partners that can apply this technology in different fields (e.g aeronautics) are sought.|
Description of the offer:
The offered technology relates to a device and a method for reducing the nonsteady side loads acting on a nozzle of a rocket engine, particularly during the startup or ignition phase of the engine. It can be used in particular to eliminate, or at least substantially limit, the nonsteady side loads occurring in the nozzle of a rocket engine during its ignition (caused by the effect known as ‘jet separation’), the separation of the boundary layer, or a separation by internal recirculation in the jet.
The idea underlying the offered technology consists in causing the formation of a stable, predictable detached shock wave inside the nozzle, this shock wave being incident to the nozzle wall at a position in which the interaction between the shock wave and the boundary layer of the flow close to the nozzle wall causes the separation of the boundary layer, that is, the separation of the jet. In contrast to the case of ‘natural’ jet separation, caused by the ambient pressure, the jet separation caused by the shock wave is stable, localised and independent of any disturbance from downstream, making it possible to eliminate, or at least to substantially reduce the nonsteady side loads.
Through the insertion of a body of rounded shape along the nozzle axis, it is possible to control the shock wave in order to make it incident to the wall of the divergent portion at an axial position corresponding to the downstream limit of the region of the divergent portion. In this way, in the position where a spontaneous jet separation or a spontaneous separation occurs, the effect of the ambient pressure is reduced.
Innovations and advantages of the offer:
The biggest advantage of this solution is the drastic reduction of non-steady side loads during the ignition phase of a rocket engine.
Domain of Application:
- Airfield and other transportation services
Last update: 15 January 2013