Mixing Characteristics of Supersonic Jet from Bevelled Nozzles

Kumar, Bholu; Verma, Suresh Kant; Srivastava, Shantanu

doi:10.18280/ijht.390226

Cited by 3 publications

(2 citation statements)

References 28 publications

(32 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Regarding CFD solvers for transient compressible flows like the SIJ configuration, there are in general three categories, namely, commercial, in-house, and open-source. Typically well validated and widely used for engineering problems, commercial CFD solvers like ANSYS Fluent [18,19] and Simcenter STAR-CCM+ [20,21] offer the advantages of direct support for troubleshooting, user-friendly graphical user interfaces, and solver runtime stability. There are, however, two main drawbacks.…”

Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulations of a Supersonic Impinging Jet Using OpenFOAM

You,

New,

Chan

2024

Computation

View full text Add to dashboard Cite

Supersonic impinging jets are a versatile configuration that can model the compressible flows of cold-spray manufacturing and vertical take-off-and landing strategy. In this work, rhoCentralFoam, solver of the OpenFOAM framework, and a large-eddy simulation formulation were used to simulate an underexpanded supersonic jet of Mach 1.45 and nozzle pressure ratio of 4, impinging on a flat wall situated at 1.5 nozzle diameters away from the jet outlet. Care was taken in the mesh construction to properly capture the characteristic standoff shock and vortical structures. The grid convergence index was evaluated with three meshes of increasing spatial resolution. All meshes can generally be considered as sufficient in terms of results focused on time-averaged values and mean physical properties such as centerline Mach number profile. However, the highest resolution mesh was found to capture fine shear vortical structures and behaviors that are absent in the coarser cases. Therefore, the notion of adequate grid convergence may differ between analyses of time-averaged and transient information, and so should be determined by the user’s intention for conducting the simulations. To guide the selection of mesh resolution, scaling analyses were performed, for which the current rhoCentralFoam solver displays a good weak scaling performance and maintains a linear strong scaling up to 4096 cores (32 nodes) for an approximately 40 million-cell mesh. Due to the internode communication bottlenecks of OpenFOAM and improvements in central processing units, this work recommends, for future scaling analyses, adopting a “cells-per-node” basis over the conventional “cells-per-core” basis, with particular attention to the interconnect speed and architecture used.

show abstract

Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulations of a Supersonic Impinging Jet Using OpenFOAM

You,

New,

Chan

2024

Computation

View full text Add to dashboard Cite

show abstract

“…The best alternative which meets the above demands is only the computational work. The computational works on the jet were also carried out in the past but in limited quantity, [29][30][31][32][33][34][35][36][37][38][39] and thus, further computational investigations are required to look into the dynamics of free shear flow and the vortical structures in detail.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of mixing performance for controlled supersonic jet

Kumar

Verma

Srivastava

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

In the present study, the mixing characteristics of the Mach 1.86 jet from a convergent-divergent nozzle of square cross-section from inlet to exit were investigated numerically. The jet studied were uncontrolled and controlled with limiting tab of rectangular and circular cross-sections. The nozzle pressure ratio is varied from 4 to 6 with a step size of one, leading to the confinement of the present study for the over-expansion and near correct expansion levels of the jet. It is observed that the core length, which is a direct indication of the extent of jet mixing, reduced significantly for the jet controlled with limiting tab as compared to that with the uncontrolled counterpart. Also, among the circular and rectangular limiting tabs, the tab with rectangular cross-section caused maximum core length reduction. The jet spread and the waves prevailing in the jet field were studied and visualized using pressure profiles and Mach contours, respectively. The present work may be used in understanding and solving complex phenomena occurring in the fields of aeroacoustics noise suppression, reduction of base heating of launch vehicles, supersonic combustion, mitigation of infrared radiations due to chimney smoke, etc., where jet mixing is highly desirable.

show abstract

Mixing enhancement with minimal thrust loss for the Mach 1.76 jet issuing from different beveled collar nozzles

Kumar,

Verma,

Srivastava

2024

Proceedings of the Institution of Mechanical Engineers, Part E:

View full text Add to dashboard Cite

The main objective of the present investigation is to enhance the jet mixing by introducing a nozzle collar exit inclination having bevel angles of 30°, 45°, and 60°. In addition to this, the present study also addresses the problem of investigating the jet which attains maximum mixing from beveled collar nozzle with the imposition of a minimal overall thrust loss penalty. The nozzles of the present study have been designed to deliver a uniform Mach 1.76 jet at the nozzle collar exit. The results thus obtained through numerical computations have been compared with that of the reference nozzle which has zero exit inclination. The investigations have been performed under both design and off-design conditions of the jet by varying the nozzle pressure ratio (NPR) from 4.5 to 6.5 with unit step size. It is seen that the rate of jet mixing is augmented with the increase in the bevel angle. Thus, the 60° beveled collar nozzle demonstrated the highest jet mixing in comparison to the reference nozzle, 30° and 45° beveled collar nozzle at each nozzle pressure ratio. However, 60° beveled collar nozzle has been substantially penalized with the highest thrust loss of about 6.5% at nozzle pressure ratio 4.5 and about 3.5% at nozzle pressure ratio 5.5 with respect to the reference nozzle and other nozzles of the present study. The 45° and 30° beveled collar nozzles reported the thrust penalty below 2.3% and 1%, respectively. The overall performance, which includes mixing enhancement along with the minimal thrust loss, has been found in the 45° beveled collar nozzle, which clearly justifies its preference over the other investigated nozzle configurations.

show abstract

Mixing Characteristics of Supersonic Jet from Bevelled Nozzles

Cited by 3 publications

References 28 publications

Large-Eddy Simulations of a Supersonic Impinging Jet Using OpenFOAM

Large-Eddy Simulations of a Supersonic Impinging Jet Using OpenFOAM

Numerical investigation of mixing performance for controlled supersonic jet

Mixing enhancement with minimal thrust loss for the Mach 1.76 jet issuing from different beveled collar nozzles

Contact Info

Product

Resources

About