Design Optimization of Rocket Thrust Chamber

A rocket engine is a jet engine that uses specific propellant mass for forming high speed propulsive exhaust jet. The reaction of nozzle wall to the gas pressure provides accelerating force, as the gas expands. A model was developed to determine the pressure, temperature and flow distribution in the combustion chamber region. The model includes various parameters of the jet- and ambient gas and can therefore be used for hot gases. Computational solutions based on the Navier-Stokes equations, finite rate chemistry, and the k-E turbulence closure are generated with design of experiment techniques, and the response surface method is employed as the optimization tool. In addition to establishing optimum designs by varying emphasis on the individual objectives, better insight into the interplay between design variables and their impact on the design objectives is gained. When the fuel and air is enter in the combustion chamber according to the x and y plot, its burn due to high velocity and temperature and then temperature increase rapidly in combustion chamber and convergent part of the nozzle and after that temperature decrease in the exit part of the nozzle. The design optimization is done using 4 fuel inlets for the rocket thrust chamber.