IRJET- Modelling and Analysis of a Convergent -Divergent Nozzle

IRJET, 2020

A nozzle is a very essential device that is used to control character of the fluid. The main purpose of the nozzle is to increase the velocity in one way or another. De Laval nozzle is a converging-diverging nozzle which has the ability to convert the chemical energy (high pressure) into kinetic energy (high velocity and low pressure). De-Laval nozzle has mainly 3 parts such as throat, diverging part, and converging part. Expansion in C-D nozzle has been studied and analyzed by experimentation moreover as numerically by numerous researchers with an objective to optimize the performance beneath given conditions. Within the gift work, supersonic flow through the rocket nozzle has been simulated mistreatment numerical methodology. The analysis has been performed keeping the same input and according to the shape of the nozzle. Our objective is to investigate the best suit nozzle which gives high exit velocity among the different cross-sections considered. The main aim of this paper is to a proper comparison with theoretical data to determine the behavior of fluid during the movement of fluid inside the nozzle. Therefore CFD analysis is being done using ANSYS 16. The paper contains a proper analysis of the convergent-divergent nozzle. Analysis of Mach number and velocity is done inside the nozzle

IRJET, 2021

Nozzles are flow controlling devices used to either accelerate or decelerate the flow of the gases produced from combustion. Rocket nozzles are convergent-divergent nozzles or otherwise known as the de Laval nozzle. They converts the high temperature, high pressure, and low velocity gas into high velocity and low pressure gas at the exit and hence achieve supersonic speeds. This paper aims to study the variation in flow parameters by modifying the nozzle divergence angle. CFD Analysis is carried out for diverging angles of 5 0 , 10 0 , 11 0 , 12 0 and 15 0. Variation in Mach number and static pressure at the nozzle outlet is studied and the optimum divergence angle for maximum Mach number is found out.

IRJET, 2020

Expansion in C-D nozzle has been studied and analyzed by experimentation moreover as numerically by numerous researchers with an objective to optimize the performance beneath given conditions within the gift work supersonic flow through the rocket nozzle has been simulated mistreatment numerical methodology. The parameters like physicist number, static pressure and shocks square measure discovered for cone-shaped and contour nozzles using axisymmetric model in ANSYS FLUENT 16® computer code. The occurrences of shocks for the cone-shaped nozzles were discovered alongside the opposite parameters for various divergent angles. The parameters beneath observation square measure compared there upon of contour nozzle for individual divergent angles by maintaining the water, outlet and throat diameter and lengths of oblique and divergent parts as same. The convergent portion and throat diameter square measure unbroken constant across the cases. The phenomenon of shock was pictured and also the results showed shut similitude in formation of physicist disk and its reflection patterns as reportable in numerous experimental studies on growth in cone-shaped C-D nozzles with lower divergent angles. No occurrence of shocks is discovered with higher divergent angles. Results delineated higher exit speed and better degree of flow separation with contour nozzles compared to it with corresponding cone-shaped nozzles.

IRJET, 2020

A nozzle is a device that is used to provide the way and direction to gases to come out of the combustion chamber. The nozzle is a device that is used to convert pressure and thermal energy into useful kinetic energy. A rocket nozzle can be used to manage and control the speed flow of pressure and steam being exhausted .rocket nozzle purpose is to convert high pressure, high-temperature gas into a high velocity, low temperature, and pressure. This paper had an analysis of the flow in the nozzle using the software ANSYS 16. The study is being carried out to have knowledge about flow inside the nozzle when the divergent section of the nozzle is being diverted or change to a certain angle using 2-d modeling to carry out the result and effects of the nozzle. The angle will make the effect on all the aspects of nozzle such as Mach number, static pressure, velocity, and temperature. The throat and inlet diameter of supersonic begin remain the same.

IRJET, 2020

A rocket nozzle could be a automation that is meant to manage the speed of flow, speed direction and pressure of stream that exhaust through it. There area unit varied kinds of rocket nozzle that area depending upon the mission of the rocket. This paper contains analysis over a convergent divergent rocket nozzle that is performed by varied quantity of divisions in mesh.The parameters like philosopher number, static pressure and shocks are determined for cone like and contour nozzles using axis-symmetric model in ANSYS FLUENT 14® software system. The occurrences of shocks for the cone like nozzles were determined together with the opposite parameters for various divergent angles. The parameters underneath observation are compared therewith of contour nozzle for individual divergent angles by maintaining the recess, outlet and throat diameter and lengths of focused and divergent parts as same. The convergent portion and throat diameter are unbroken constant across the cases. The phenomenon of shock was unreal and therefore the results showed shut alikeness in formation of philosopher disk and its reflection patterns as according in varied experimental studies on growth in cone like C-D nozzles with lower divergent angles. No occurrence of shocks is determined with higher divergent angles. Results pictured higher exit rate and better degree of flow separation with contour nozzles compared to it off with corresponding cone like nozzle.

IRJET, 2021

The nozzle is used to convert the chemical thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Nozzle is a device designed to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that exhaust from them. Nozzles come in a variety of shapes and sizes depending on the mission of the rocket, this is very important for the understanding of the performance characteristics of rocket. Convergent divergent nozzle is the most commonly used nozzle since in using it the propellant can be heated in combustion chamber. In this thesis the convergent divergent nozzle changing the different nozzle diameters and different fluids at different velocities. We modeled convergent divergent nozzle changing with different nozzle diameters and Analyzed the convergent divergent nozzle with different mass flow rates to determine the pressure drop, heat transfer coefficient, and velocity and heat transfer rate for the fluid by CFD technique.

CFD is a branch of Fluid Mechanics which rely on numerical methods and algorithms to solve and analyze problem that involves fluid flow. CFD analysis has been conducted to analyze flow pattern of supersonic rocket nozzle at various degree of divergent angle, mach numbers etc. This paper aims to study the behavior of flow in convergent divergent nozzle by analyzing various parameters like pressure, temperature and velocity using computational fluid dynamics software(C.F.D).These results were further plotted comparing them with analytical values.

Journal of Mines, Metals and Fuels, 2022

Rocket nozzle is part of a rocket in which the burnt propellant from the combustion chamber can exhaust through the nozzle to get the desire amount of thrust and required Mach number. The nozzle turns the static high pressure high temperature gas to low pressure, low temperature, and high velocity gases. To analyse this we have used CFD. Where CFD is the fluid mechanics which is integral part of the design, this is based on numerical methods and algorithm method. To analyse the fluid flow in supersonic rocket nozzle the CFD analysis software is used. Mainly in this work had focused on the pressure, temperature, velocity and Mach number of the mass flow in nozzle by changing the divergent angle. The oblique shock is a main conception and the presence of oblique shock which will create the instabilities. And it is visualized that the shock wave is creating in the nozzle at the 5° of divergent angle and it slowly started eliminating from the nozzle after 5° of divergent angle. To overcome this problem some of the trials are made for different divergent angle such as 5°, 10° 11°, 12°, 15°, and 20°. After 12 o of divergent angle the flow parameters will start get reducing. At 20 o the sudden drop of flow parameter will occur. By considering all the results at different divergent angle, the 11° angle is more efficient and found all the flow parameters such as velocity, temperature, pressure and Mach number of the mass flow are at required condition.

IRJET, 2021

A Rocket Nozzle is a mechanical device of varying cross sections modelled to control the rate of flow, speed, direction and pressure of the exhaust gases coming from the combustion chamber. A De Laval Nozzle is a convergentdivergent nozzle, in which the temperature from the combustion chamber increases rapidly into convergent part of the nozzle, after which the temperature will decrease at the exit part of the nozzle. This project deals with CFD analysis of a De Laval nozzle based on number of inlets (one and four) from combustion chamber. The CFD analysis is done to calculate the exit temperature, exit pressure and exit velocity of the De Laval nozzle. These parameters are calculated by varying the Mach number. This analysis will result in a comparative study of the performance of a single inlet nozzle and four inlets nozzle at different Mach Numbers (subsonic, sonic and supersonic). The numerical analysis is carried out using a Computational Fluid Dynamics (CFD) Software, ANSYS Fluent.

5th International Conference on Engineering, Research, Innovation and Education (ICERIE), 2019At: Shahjalal University of Science & Technology (SUST), Sylhet, bangladesh, 2019

A rocket engine nozzle is the main component of the rocket propulsion system. To produce thrust Ramjets, Scramjets and rockets all use nozzles to accelerate hot exhaust. Primary design difficulties arise with the nozzle used in a rocket with a wide Mach number capability. This work centers on the modeling of a convergent-divergent nozzle for compressible flow using computational fluid dynamics (CFD). CFD, a vital branch of fluid dynamics to solve and analysis different fluid flows by using numerical methods and algorithms. Boundary conditions are required to measure the interaction of the fluid with the surfaces. A bell nozzle contour has developed in MATLAB and analyzed it for different thermodynamic parameters. Density and temperature variations often perform a significant role in compressible flow. Hence, by varying the nozzle length this study provides additional information on Mach number behavior, shock location, and pressure distribution. The simulation was performed in ANSYS and both the k-turbulence modeling method was used to compare the results.