In earlier days rocket nozzles were made up of monolithic ceramics, zirconium, and nimonic alloys. Though the materials have the capability to withstand enough temperature, they have the drawbacks such as manufacturing cost & time, strength to weight ratio.In order to cut the manufacturing cost & time, the strength to weight ratio and also to improve the capability to withstand high temperature, a composite material—C/SiC—shows enough required properties in the bell-shaped nozzles for rocket. Bell-shaped nozzle has been taken into consideration since it is being widely used in the modern days. This material could withstand temperature upto 2200 °C. The nozzle has been manufactured with liquid phase infiltration process which results in efficient strength to weight ratio.The properties of the above said material has been collected and the analysis work has been carried out in ANSYS software.Thermal& flow analysis has been carried out for determining the accuracy of the concept, in addition to compensate the erosion caused due to high velocity at the throat of the nozzle. A band with the desired thickness has been given at the throat and the expected results are achieved. Keywords:Nozzle, liquid phase infiltration, ANSYS, thermal& flow analysisCite this Article MuraliK, Sridhar SM, Sabik NAet al. Advanced ceramic matrix composites in rocket nozzle.Journal of Thermal Engineering and Application.2015; 2(3):32–40p.
