Jet Flow Control Using Semi-Circular Corrugated Tab

K, Sathish Kumar; C, Senthil Kumar

doi:10.1515/tjj-2018-0014

Cited by 11 publications

(4 citation statements)

References 10 publications

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“…Then the conditions for inlet, tabs, nozzle, domain and outlet are fed. Shear stress transport model is chosen (Kumar and Chidambaram, 2018;Sathish et al, 2021aSathish et al, , 2021b. The solution for jet flow control is chosen and required discretized equation is then being selected from the solution control for solving.…”

Section: Solver Settingsmentioning

confidence: 99%

Influence of slot profiles on the characteristics of jets

Krishnaraj

Vinayagamurthy²

2022

AEAT

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Purpose The purpose of this research is to study and investigate the flow control of 0.8 Mach jet using three tab configurations. The tabs with the slots will eventually lead to generation of vortices and thus enhances the mixing characteristics. Design/methodology/approach The jet flow control is achieved by the usage of three tabs, namely, Tab A, Tab B and Tab C that are placed at the exit plane of the convergent nozzle at 180 degrees apart. Three tabs with different slot profile are designed with the same constant blockage ratio of 7.3%. The tabs produce vortices of varying sizes that directly influence and modify the jet structure, thereby enhancing the efficiency in mass entrainment and mixing. The tabs are studied numerically first and then are compared with the results of the experiments. Findings The results are compared with that of the results of the uncontrolled jet. For Mach 0.8 jet, Tab C is found to reduce the core length and gives reduction of 90.23%, in comparison to Tab A and Tab B, which provides 84.1% and 87.79%, respectively. The results of numerical are then compared with the centerline results obtained via experiments. With the engagement of Tabs A, B and C, the jet structure is seen to have been modified at Mach 0.8 with Tab C performing better. Practical implications The tabs are a passive control device that can be practically enabled in the aircraft nozzles to control the flow and even suppress the noise emanated by the jet. Tabs can be effectively used for better thrust vector control and assist in jet noise suppression. Thus, this study on tabs and its uses are important and essential in aerospace technology. Originality/value This particular study on mechanical slotted tabs is innovatively carried out by designing the tabs in such a way that one such has not been designed before. The slots run through the adjacent sides of the tabs which is a novelty in itself, whereas perforations made only through the opposite sides of the tabs are studied by various researchers till now. The slots in the adjacent faces modify the flow physics in such a way that it enhances mixing by the creation of turbulence because of the interaction between the main stream and the secondary jet exactly at the core. So far, such slots and profiles are not investigated. By the usage of such tabs, the flow to mix faster is much closer to the core of the jet by creating mixed size vortices and thus has higher efficiency.

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Section: Solver Settingsmentioning

confidence: 99%

Influence of slot profiles on the characteristics of jets

Krishnaraj

Vinayagamurthy²

2022

AEAT

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“…The performance of SST is studied and analyzed in many engineering applications. Shear stress transport turbulence model was also used by Kumar and Chidambaram (2018) for the study on triangular tabs with corrugations. The potential core length for the simulation with the SST model and the experiment was as close as 0.87 and 0.88 D e , respectively.…”

Section: Study On Turbulence Modelsmentioning

confidence: 99%

“…The locations/placements of the corrugations on a triangular tab were also varied and studied numerically and experimentally by researchers in the recent times. Numerical comparison of the semicircular corrugated triangular tab with plain triangular tab to control the subsonic jet is investigated by Kumar and Chidambaram (2018), who found that the tab with corrugations yielded better effectiveness. Investigations by Kumar and Chidambaram (2019) on the corrugation locations by differing the spacing of the locations on the triangular tab to control the supersonic jet yielded more accurate results in this domain.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Jet Mixing Characteristics Using Slotted Rectangular Tabs

Krishnaraj

Vinayagamurthy

2021

J. Aerosp. Technol. Manag.

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This article discusses the jet mixing effectiveness of rectangular tab with slots to distort the jet, thereby creating vortices of differing sizes to enhance the mixing. This article numerically investigates the effectiveness of slanted slotted/perforated rectangular tabs with the slot connecting the adjacent faces of the tab to control Mach 0.4 jet. To intensify the jet mixing process, two similar tabs with equal blockage ratio of 7% are placed at diametrically opposite locations of the convergent nozzle exit. The jet flow development in the axial and radial directions of the jet are investigated in detail. To measure the effectiveness of the slotted tabs, the results are compared with the free jet and with the jet operated with solid rectangular tab. The percentage reduction in the core length obtained is 84.1 and 74% for the jet employed with the slotted tab and the solid tab, respectively, when compared with the free jet. The results exhibit that the slotted tab distorts the jet in the near field to a greater extent when compared with the solid rectangular tab.

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“…For the co-flow nozzle, no slip wall condition is chosen. The governing equations are converged to a minimum error of 10 À4 (Sathish Kumar and Chidambaram, 2018).…”

Section: Numerical Detailsmentioning

confidence: 99%

Numerical analysis of supersonic co-flow jet with varying lip thickness

K¹,

Krishnan

Anusindhiya

et al. 2021

AEAT

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Purpose This study aims to present the numerical study on supersonic jet mixing characteristics of the co-flow jet by varying lip thickness (LT). The LT chosen for the study is 2 mm, 7.75 mm and 15 mm. Design/methodology/approach The primary nozzle is designed for delivering Mach 2.0 jet, whereas the secondary nozzle is designed for delivering Mach 1.6 jet. The Nozzle pressure ratio chosen for the study is 3 and 5. To study the mixing characteristics of the co-flow jet, total pressure and Mach number measurements were taken along and normal to the jet axis. To validate the numerical results, the numerical total pressure values were also compared with the experimental result and it is proven to have a good agreement. Findings The results exhibit that, the 2 mm lip is shear dominant. The 7.75 mm and 15 mm lip is wake dominant. The jet interaction along the jet axis was also studied using the contours of total pressure, Mach number, turbulent kinetic energy and density gradient. The radial Mach number contours at the various axial location of the jet was also studied. Practical implications The effect of varying LT in exhaust nozzle plays a vital role in supersonic turbofan aircraft. Originality/value Supersonic co-flowing jet mixing effectiveness by varying the LT between the primary supersonic nozzle and the secondary supersonic nozzle has not been analyzed in the past.

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Jet Flow Control Using Semi-Circular Corrugated Tab

Cited by 11 publications

References 10 publications

Influence of slot profiles on the characteristics of jets

Influence of slot profiles on the characteristics of jets

Investigation of Jet Mixing Characteristics Using Slotted Rectangular Tabs

Numerical analysis of supersonic co-flow jet with varying lip thickness

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