Modelling and Thermal Effects Analysis on Toroidal Aero Spike Nozzle in Hybrid Rocket Engine

Abstract

In toroidal aero spike nozzle combustion gases flow through a constriction (throat) and then the expansion away from the centreline is contained by the diverging walls of the nozzle up to the exit plane. Nozzles are a point design with optimum performance at one specific ambient pressure the combustion occurs in an enclosed chamber, like in a conventional nozzle engine. The hot gasses are accelerated to low supersonic speed in an internal expansion section. In this part of the engine, the flow is still totally enclosed. A way to visualize it is to imagine the gasses moving between two opposite walls which are coming closer to each other and then beginning to separate. At the point where the gasses have reached some low supersonic speed, one of the walls ends. This is the point where the external expansion ends. The other wall continues down and forms the spike contour. At the point where the other wall ends, the gasses expand around the edge of the wall. So in this project high explosive gases flow through the nozzle with high amount of temperature, due increasing of temperature high means thermal stress are devolved in the chamber that stresses are effecting the nozzles due this effects failure are accruing in the nozzles so we have to find out that temperature where nozzles are failure using thermal analysis with the help of ansys software. And modelling is done using mechanical design commercial software catia v5. And ground data acquisition system is described in detail.