Abstract
The aim of this paper is to analyze flow in a rocket nozzle and perform FSI simulation for the thermo-mechanical interaction between fluid and solid structure. The nozzle is most important part of the rocket. The proper design plays a major role in the performance of the nozzle, which is designed aerodynamically while considering NPR values. Nozzle is made with Rhenium and coated with Iridium. High speed flow through Convergent-Divergent nozzle leads to complex loading on surrounding structures. The two different cases are carried out and assist the thermal loading on surrounding structures. Structure Interaction analysis is carried in Star CCM+ by creating three different regions i.e., Fluid, Iridium coating (Solid region of 50 μm) and Rhenium structure (Solid region of 1mm) and this analysis gives a better understanding of the behavior of the thermo-mechanical interaction between solid to fluid regions.
Highlights
A convergent-divergent nozzle is most important component of the rocket engine and it is a combustion chamber extension [1]
The rocket nozzle is designed to control the direction and it is like tube shaped through which hot gases flow
During engine startup and shutdown of the rocket nozzle will operate an over expanded mode where the ambient/operating pressure is greater than the internal pressure acting on nozzle wall [2,3]
Summary
A convergent-divergent nozzle is most important component of the rocket engine and it is a combustion chamber extension [1]. The main role of nozzle is to expand and accelerate the gas. The rocket nozzle is designed to control the direction and it is like tube shaped through which hot gases flow. Nozzles are frequently used to control the rate of flow, flow direction, and the pressure of the stream that emerges from them. Nozzle are used even in the turbojet and ramjet engine. During engine startup and shutdown of the rocket nozzle will operate an over expanded mode where the ambient/operating pressure is greater than the internal pressure acting on nozzle wall [2,3]. The flow first converges down to the throat or minimum area of nozzle and it is expanded through the divergent section to the exit
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