Critical Designing and Flow Analysis of Various Nozzles using CFD Analysis

Joshi, None Prapti; Gandhi, Tarun; Parveen, Sabiha

doi:10.17577/ijertv9is020208

Cited by 4 publications

(1 citation statement)

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“…Joshi et al, [15] examined the design of nozzles for scientific exploration of celestial bodies, with a specific emphasis on their effectiveness in various atmospheric conditions. The analysis takes into account variables such as Mach velocity, temperature, and pressure, and use computational fluid dynamics (CFD) simulations to comprehend the efficiency across various settings.…”

Section: Literature Surveymentioning

confidence: 99%

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Vinayaka Nagarajaiah,

Sara Solomon Raj,

Ayampalayam Nanjappan Swaminathen

et al. 2024

ARFMTS

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A nozzle is a tubular structure designed to facilitate the flow of hot gases. Rocket nozzle designs typically consist of a stationary convergent section and a stationary divergent section. The term "CD" is an abbreviation for "convergent-divergent" and is used to refer to this specific nozzle type. Upgrades are being made to nozzles and other engine components in order to enhance performance and optimise thrust delivery. Application-specific improvements will be made to rocket nozzles and other current combustion expansion systems. An instance of such progress is the implementation of the bell and twin bell nozzle. This study conducted a comparative analysis of two kinds of nozzles, namely bell and conical, at different Mach speeds to ascertain which one yields the most optimal flow. Subsequently, the flow parameters were modelled with computational fluid dynamics (CFD). Ensuring optimal pressure thrust integral throughout the supersonic zone of the nozzle surface while taking the base pressure into account was the aim of the problem formulation. The research focused on irrotational flow, taking into consideration the impacts of boundary layers.

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Section: Literature Surveymentioning

confidence: 99%

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Vinayaka Nagarajaiah,

Sara Solomon Raj,

Ayampalayam Nanjappan Swaminathen

et al. 2024

ARFMTS

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Effect of the length of truncated nozzle with a tip on its thrust characteristics

Ternova¹

2022

Teh. Meh.

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Nowadays, for solving new problems, rocket engine nozzle developers are increasingly turning to non- traditional nozzle configurations that differ from the classic Laval one. A relatively new line in the design of supersonic nozzles is the development of the so-called bell-shaped nozzle, which, unlike the classical Laval nozzle, has a larger angle of entry into the supersonic part of the nozzle. In this case, dual bell nozzles, which have two flow expansion sections in their supersonic part, are considered. However, the effect of the length ratio of the two flow expansion sections of a truncated nozzle on its characteristics has not yet been studied. The goal of this work is to determine the effect of the length of the upstream conical supersonic section on the static pressure distribution in the nozzle and its thrust characteristics with the shape of the bell-shaped tip kept unchanged. The nozzle characteristics were studied using the ANSYS Fluent computing package. It was shown that the flow patterns in the nozzle (velocity fields) change with the length of the conical part upstream of the tip and the underexpansion degree. Under terrestrial conditions (Pн = 1 bar), all variants show a developed separation zone that starts from the corner point where the tip is connected to the conical part. In this case, the pressure on the nozzle wall is nearly equal to the ambient pressure. At a large flow underexpansion degree (P0 = 300 bar) and in low-pressure conditions conditions (Pн =0.1 bar), the flow in the tip is adjacent to the wall. At a large flow underexpansion degree, the pressure in the nozzle increases from the corner point to the tip exit, and the pressure at the tip exit increases with decreasing tip length. The nozzle thrust coefficient decreases with increasing flow underexpansion degree, and it reaches a constant value after the flow becomes adjacent to the tip wall downstream of the corner point where the tip is connected to the nozzle. At high flow underexpansion degrees, the nozzle thrust coefficient is higher for a nozzle with a longer conical part. The calculated results are in good agreement with experimental data on nozzles of this type.

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Wave structure of the gas flow in a truncated nozzle with a long bell-shaped tip

Strelnikov¹,

Pryadko²,

Ternova³

2023

Teh. Meh.

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In recent years, more and more attention has been paid to nozzles with an unconventional profile, which differs from that of the classical streamline-profiled Laval nozzle. In such nozzles, the flow fields typically include interacting supersonic and subsonic flows, often with recirculation regions and a complex wave structure of the flow. This work is concerned with a numerical study of the wave structure of the gas flow in a truncated supersonic nozzle with an elliptical bell-shaped tip whose length is long in comparison with the conical section upstream of the tip. The gas flow inside the nozzle and in the surrounding space was simulated using the ANSYS software package. The calculations were carried out in a non-stationary axisymmetric formulation based on the Reynolds-averaged Navier–Stokes equations closed with the use of the SST turbulence model with near-wall functions and a compressibility correction. In the calculations, the nozzle inlet pressure and the ambient pressure were varied. The correctness of the methodological approaches to the solution of the problem was confirmed in the authors’ previous works. The study showed the following. At low values of the nozzle inlet pressure (P0 < 50 bar) and an ambient pressure of 1 bar, the tip wall exhibits a developed separation zone with a large-scale vortex and a small-scale one (near the tip exit). The first "barrel" of the outflowing gas shows a "saddle" low-intensity compression wave structure. In the case of a separated flow, the tip wall pressure in the separation zone is about 15% less than the ambient pressure. At P0 > 100 bar, the tip wall pressure is nearly proportional to the nozzle inlet pressure. In the upper atmosphere, when going in a radial direction from the nozzle axis at the tip exit cross-section, the static pressure monotonically decreases, reaches a minimum, and then increases linearly to the its maximum value on the tip wall. In the case of a separated flow in the tip at a sea-level ambient pressure, the static pressure at the tip exit cross-section behaves in the same manner for inlet pressures P0 > 50 bar. At P0 = 50 bar, there exist two extrema: the pressure first deceases to its minimum value, then increases to its maximum value, and then decreases slightly to its value on the tip wall.

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Critical Designing and Flow Analysis of Various Nozzles using CFD Analysis

Cited by 4 publications

References 0 publications

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Effect of the length of truncated nozzle with a tip on its thrust characteristics

Wave structure of the gas flow in a truncated nozzle with a long bell-shaped tip

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