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Aerospace
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Jet Flow Analysis
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Jet Flow Analysis

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (1 July 2022) | Viewed by 12816

Special Issue Editor

Prof. Dr. Valery Zapryagaev

E-Mail Website
Guest Editor
Experimental AeroGazDynamics Laboratory, Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Science, 630090 Novosibirsk, Russia
Interests: supersonic flow

Special Issue Information

Dear Colleagues,

Actuality of the jet flows investigations is stipulated to the use of jets in various fields of industry, including in the creation of aviation and aerospace technics, in metallurgy, in the development of promising nozzle designs for combustion engines, in the development of gas fields, in the processing of materials, etc.

The practical using of supersonic jet flows necessitates the study of the shock-wave structure of the flow, obtaining information on the pulsation characteristics, as well as data on the intensity of acoustic radiation from the jet into the ambient space, which are all typical for high-speed gas jet flow.

In addition to free jets flowing into the environment, it is important to study the process of interaction of a high-speed gas flow with an obstacle. This interaction is accompanied by intense pulsations, the formation mechanism of which depends both on the parameters of the gas flow and on the geometry of the obstacle. The problems of studying the structure of supersonic jets, including the flowing into a concurrent, oncoming, or transverse supersonic flow, have gained a lot of interest. Furthermore, the use of multi-block jets used in modern aviation and aerospace engineering is widespread, as well as jets emanating from nozzles of complex shapes (for example, flat jets, coaxial jets, as well as jets emanating from oblique nozzles or nozzles with chevrons).

The significant element of the jet structure is a shear layer, the existence of which makes it necessary to take into account the state of the jet flow (laminar or turbulent), since the type of flow has a significant effect on both mixing processes at the boundary and the level of acoustic radiation. Additional attention in the study of supersonic off-design jets requires the presence of shock waves, which interact with each other and generate additional flow elements, including rarefaction waves and internal mixing layers.

At present, understanding of the jet flow structure is largely based on advances in the development of the numerical simulation of flows calculation fluid dynamics (CFD). Testing the results of numerical calculations (verification and validation) is an important part of CFD task, in order to obtain reliable experimental data. At present time, experimental data are obtained with contactless and well-mastered measurement methods (for example, PIV, LDA, etc.). In conclusion, we note that the study of the structure of high-speed jet flows is important for scientific and practical value.

Prof. Dr. Valery Zapryagaev
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • gas jet
  • nozzle
  • aerospace technics
  • supersonic
  • shock-wave structure
  • acoustics
  • obstacle
  • chevrons
  • laminar flow
  • turbulent flow
  • CFD
  • verification
  • validation
  • experimental data
  • visualization
  • PIV
  • LDA

Published Papers (6 papers)

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Research

20 pages, 13255 KiB  
Article
Numerical Study of the Induced Shock on the Mixing Augmentation of Hydrogen Counter-Flow Jet in the Supersonic Flow
by Yi Han, Chibing Shen, Zhaobo Du and Haoran Tang
Aerospace 2022, 9(9), 506; https://doi.org/10.3390/aerospace9090506 - 11 Sep 2022
Cited by 3 | Viewed by 1830
Abstract
In the scramjet engine, the injection and mixing of fuel are the basis for organizing efficient combustion. The shock wave/jet shear layer interaction is one of the methods used to enhance fuel mixing in supersonic flow. In this research, the effect of the [...] Read more.
In the scramjet engine, the injection and mixing of fuel are the basis for organizing efficient combustion. The shock wave/jet shear layer interaction is one of the methods used to enhance fuel mixing in supersonic flow. In this research, the effect of the induced shock wave on the mixing augmentation of fuel counter-flow jet is studied in the supersonic crossflow. The results show that the symmetrical setting of the shock wave generators (SWGs) has the highest mixing efficiency but brings a greater total pressure loss. In the specific range, the mixing efficiency increases with the increase in the angle of the SWG, while the total pressure recovery coefficient is the opposite. The induced oblique shock wave acting on the front of the fuel jet has an obvious influence on the flow field, resulting in the highest mixing efficiency. In the end, the analytic hierarchy process (AHP) is used to evaluate the extent of mixing augmentation by mixing parameters, which provides a decision-making idea for the scheme decision of mixing augmentation. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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16 pages, 5713 KiB  
Article
The Relationship between Contraction of the Ejector Mixing Chamber and Supersonic Jet Mixing Layer Development
by Qi Jing, Wanwu Xu, Wei Ye and Zhiyan Li
Aerospace 2022, 9(9), 469; https://doi.org/10.3390/aerospace9090469 - 23 Aug 2022
Cited by 5 | Viewed by 1514
Abstract
Supersonic mixing layer development seriously impacts on the performance of an ejector, and the effect of mixing chamber contraction angle on supersonic jet mixing has been poorly studied. Numerical simulations are applied to investigate the effect of the mixing chamber contraction angle ( [...] Read more.
Supersonic mixing layer development seriously impacts on the performance of an ejector, and the effect of mixing chamber contraction angle on supersonic jet mixing has been poorly studied. Numerical simulations are applied to investigate the effect of the mixing chamber contraction angle (φ) on the performance of a central ejector and supersonic mixing layer development pattern. The main findings of this study are as follows: the non-mixed length (l) is reduced by 22.12% when the mixing chamber contraction angle (φ) increases from 2° to 6°. Meanwhile, the secondary stream mass flow rate (ms) is reduced by 35.02%, and the total pressure loss is decreased by 18.37% at the outlet. l is positively correlated with ms and negatively correlated with the mixing layer thickness (σ). The mixing layer thickness (σ) grows highly linearly before the secondary flow is covered completely. The pressurization (P0δ/P0s) performance of the mixing layer will be progressively weaker than the total pressure loss because of the complex shock structure. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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28 pages, 9780 KiB  
Article
Numerical Simulation of the Flow in Two-Phase Supersonic Underexpanded Gas–Particle Jets Exhausting into a Slotted Submerged Space
by Sergey Kiselev, Vladimir Kiselev and Viktor Zaikovskii
Aerospace 2022, 9(8), 432; https://doi.org/10.3390/aerospace9080432 - 05 Aug 2022
Cited by 1 | Viewed by 1643
Abstract
A simplified 2D model for calculating two-phase gas–particle flows in a slot space has been developed. The model can be used for fast calculation and estimation of supersonic-flow parameters in the slot space. Using this model, a numerical simulation of the flow in [...] Read more.
A simplified 2D model for calculating two-phase gas–particle flows in a slot space has been developed. The model can be used for fast calculation and estimation of supersonic-flow parameters in the slot space. Using this model, a numerical simulation of the flow in two-phase gas–particle supersonic jets exhausting into a submerged slot space bounded by two parallel disks was performed. The presence of particles led to the splitting of the gas jet into an internal two-phase jet and an external gas jet. In the present study, we investigated the structure of a two-phase jet as dependent on the spacing between the disks for conditions of cold spraying. A new effect was found in the flow at a small spacing between the disks (of the order of 0.2 mm) and a high-velocity internal two-phase gas–particle jet was formed. The distribution of the concentration of particles in the particle jet proved to be essentially non-uniform, with a caustic formed at the upper jet boundary. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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15 pages, 6766 KiB  
Article
Impulse Air Jet Action on the Convective Heat Exchange Tubular Surfaces in Boilers
by Valentin Kislovsky and Alexey Melnikov
Aerospace 2022, 9(8), 418; https://doi.org/10.3390/aerospace9080418 - 01 Aug 2022
Viewed by 1298
Abstract
Calculation and experimental investigations were carried out to determine the parameters of the impulse air jet created by the pneumatic generator of the air-impact system of the cleaning of tubular heat exchangers in boilers. Two configurations (lengthwise and checkerboard) of the arrangement of [...] Read more.
Calculation and experimental investigations were carried out to determine the parameters of the impulse air jet created by the pneumatic generator of the air-impact system of the cleaning of tubular heat exchangers in boilers. Two configurations (lengthwise and checkerboard) of the arrangement of tubular heat exchangers located at distances from 1.0 m to 2.5 m of nozzle exit were experimentally investigated and the forces acting on them were determined. Numerical modeling of the impulse jet impact on heat exchange tubes was carried out. It was shown that an increase in the pressure of the generated impulse jet to 2.35 MPa makes it possible to significantly increase the acting force from 78 N to 1881 N at a large distance from the exhaust nozzle. The results obtained can be used in the development of specific systems for air impact cleaning systems of boiler units with other sizes and configurations of the heat exchange tubes. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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12 pages, 6358 KiB  
Article
Penetration of a Pulsed Gas Jet through a Package of Heat Exchange Tubes
by Valery Zvegintsev
Aerospace 2022, 9(8), 404; https://doi.org/10.3390/aerospace9080404 - 27 Jul 2022
Viewed by 1312
Abstract
The slagging of heating surfaces by fly ash significantly complicates the long term operation of solid-fuel boilers. Gas pulse technologies offer a potentially convenient, inexpensive, yet efficient way for online slag deposits removal. The creation and application of real boiler cleaning systems using [...] Read more.
The slagging of heating surfaces by fly ash significantly complicates the long term operation of solid-fuel boilers. Gas pulse technologies offer a potentially convenient, inexpensive, yet efficient way for online slag deposits removal. The creation and application of real boiler cleaning systems using gas pulse technologies is a relatively new direction in the energy sector and requires scientific research on various aspects. In this work, the numerical investigation of the gas-dynamic flow arising when the package of heat-exchange tubes is blown with single air jet created by a pneumopulse cleaning system has been carried out. The forces acting on the heat-exchange tubes located at distances 1.0 m and 2.0 m from the exhaust nozzle with various configurations of tubes in the package have been determined. It is shown that an increase in the pressure of the generated air jet makes it possible to significantly increase the acting forces at large distances from the exhaust nozzle. The results of this study and similar calculations for real geometry will increase the validity of engineering solutions used in the development of pneumopulse cleaning systems for large power boilers. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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15 pages, 5540 KiB  
Article
Flow Feature in Supersonic Non-Isobaric Jet near the Nozzle Edge
by Valeriy Zapryagaev, Ivan Kavun and Nikolay Kiselev
Aerospace 2022, 9(7), 379; https://doi.org/10.3390/aerospace9070379 - 13 Jul 2022
Viewed by 2404
Abstract
Using the example of studying the supersonic underexpanded jet initial section, the issue of interpreting the experimental visualization data and Pitot pressure measurement data using the results of numerical calculations (2d RANS k-ω SST) is discussed. It is shown that the gradient S-shaped [...] Read more.
Using the example of studying the supersonic underexpanded jet initial section, the issue of interpreting the experimental visualization data and Pitot pressure measurement data using the results of numerical calculations (2d RANS k-ω SST) is discussed. It is shown that the gradient S-shaped feature of the gas-dynamic structure near the nozzle exit, observed in the form of a barrel shock, is a characteristic that separates the expansion and compression regions, and downstream is transformed into a barrel shock. It has been established that the reason for the observed S-shaped curvature of this feature is the axisymmetric nature of the jet flow. Full article
(This article belongs to the Special Issue Jet Flow Analysis)
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