Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
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Nithya Subramani
,
Sangeetha M
Abstract
This paper presents the numerical analysis of a convergent-divergent circular nozzle with the exit Mach number of 1.69 with and without passive control at the exit. The passive control method opted for this analysis was inward and outward ascending triangular protrusion. This paper explores the influence of the passive control geometry and its blockage area concerning the nozzle exit. The nozzle pressure ratio (NPR) used for carrying out the flow analysis were 3, 4.932, and 6. Two different inward and outward protrusions were used with a height of 1.5 mm and 3 mm. From the results, the potential core length of the protrusion 1.5 mm height was not much changed in the both outward and inward cases. But when the height of the protrusion was increased to 3 mm, there was a noticeable core length reduction at all NPR but with different cases. At the NPR of 6, the potential core length of the inward protrusions 3 mm was reduced by 44 % compared to the plain CD nozzle.
Nomenclature
- CFD
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Computational fluid dynamics
- CD Nozzle
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convergent-divergent nozzle
- NPR
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nozzle pressure ratio
- X/D
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Distance from nozzle exit/diameter of the exit
- ΔL C
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Potential core length reduction
- L s
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Shock cell length
- P t
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total pressure
- P 0
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settling chamber pressure
Acknowledgments
I would like to thank everyone who helped me during the research.
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Research ethics: Not applicable.
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Author contributions: 1 S. Nithya – Conceptualization, Analysis. 2 M. Sangeetha – Supervision. 3 G. Gowtham – Validation and Writingen.
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Competing interests: The author(s) state(s) no conflict of interest.
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Research funding: None declared.
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Data availability: The raw data can be obtained on request from the corresponding author.
References
1. Kumar, A, Rathakrishnan, E. Triangular tabs for supersonic jet mixing enhancement. Aeronaut J 2014;118:1245–78. https://doi.org/10.1017/s0001924000009969.Search in Google Scholar
2. Phanindra, BC, Rathakrishnan, E. Corrugated tabs for supersonic jet control. AIAA J 2010;48:453–65. https://doi.org/10.2514/1.44896.Search in Google Scholar
3. Gu, B, Baek, SW, Jegal, H, Choi, SM, Kim, WC. Infrared signature characteristic of a microturbine engine exhaust plume. Infrared Phys Technol 2017;86:11–22. https://doi.org/10.1016/j.infrared.2017.08.014.Search in Google Scholar
4. Tam, CK, Tanna, HK. Shock associated noise of supersonic jets from convergent-divergent nozzles. J Sound Vib 1982;81:337–58. https://doi.org/10.1016/0022-460x(82)90244-9.Search in Google Scholar
5. Chand, DS, Thanigaiarasu, S, Elangovan, S, Rathakrishnan, E. Perforated arc tabs for jet control. Int J Turbo Jet Engines 2011;28:133–8. https://doi.org/10.1515/tjj.2011.012.Search in Google Scholar
6. Rathakrishnan, E. Experimental studies on the limiting tab. AIAA J 2009;47:2475–85. https://doi.org/10.2514/1.43790.Search in Google Scholar
7. Fharukh, AG, Alrobaian, AA, Aabid, A, Khan, SA. Numerical analysis of convergent-divergent nozzle using finite element method. Int J Mech Prod Eng Res Dev 2018;8:373–82. https://doi.org/10.24247/ijmperddec201842.Search in Google Scholar
8. Ezhilmaran, G, Khandai, SC, Pavithrabalan, S, Udhayakumar, K. Supersonic jet control by tabs with slanted perforation. Int J Turbo Jet Engines 2021;38:331–9. https://doi.org/10.1515/tjj-2018-0034.Search in Google Scholar
9. Ezhilmaran, G, Khandai, SC, Sinha, YK, Thanigaiarasu, S. Numerical simulation of supersonic jet control by tabs with slanted perforation. Int J Turbo Jet Engines 2022;39:331–42. https://doi.org/10.1515/tjj-2019-0015.Search in Google Scholar
10. Knowles, K, Saddington, AJ. A review of jet mixing enhancement for aircraft propulsion applications. Proc Inst Mech Eng G J Aerosp Eng 2006;220:103–27. https://doi.org/10.1243/09544100g01605.Search in Google Scholar
11. Maruthupandiyan, K, Rathakrishnan, E. Shifted triangular tabs for supersonic jet control. J Aero Eng 2018;31:04018067. https://doi.org/10.1061/(asce)as.1943-5525.0000893.Search in Google Scholar
12. Zaman, KB. Streamwise vorticity generation and mixing enhancement in free jets by delta-tabs. In: 3rd shear flow conference; 1993:3253 p.10.2514/6.1993-3253Search in Google Scholar
13. Bradbury, LJ, Khadem, AH. The distortion of a jet by tabs. J Fluid Mech 1975;70:801–13. https://doi.org/10.1017/s0022112075002352.Search in Google Scholar
14. Zuraidi, NH, Khan, SA, Aabid, A, Baig, M, Shaiq, IM. Passive control of base pressure in a converging-diverging nozzle with area ratio 2.56 at Mach 1.8. Fluid Dynam Mater Process 2023;19:807–29. https://doi.org/10.32604/fdmp.2023.023246.Search in Google Scholar
15. Arun Kumar, P, Aileni, M, Rathakrishnan, E. Impact of tab location relative to the nozzle exit on the shock structure of a supersonic jet. Phys Fluids 2019;31:1–18. https://doi.org/10.1063/1.5111328.Search in Google Scholar
16. Akram, S, Rathakrishnan, E. Control of supersonic elliptic jet with ventilated tabs. Int J Turbo Jet Engines 2020;37:267–83. https://doi.org/10.1515/tjj-2017-0033.Search in Google Scholar
17. Dash, SM, Sinha, N, Kenzakowski, DC, Kennepalli, C, Ungewitter, RJ. CFD. Studies supporting the design, testing, and evaluation of noise reduction concept for military aircraft, RTO-MP-AVT-158. Pipersville: Flow Technology, Inc. (CRAFT Tech); 2018.Search in Google Scholar
18. Chidambaram, S. Supersonic jet flow control using semi-circular corrugated tabs. Aircraft Eng Aero Technol 2019;91:1340–52. https://doi.org/10.1108/aeat-01-2019-0021.Search in Google Scholar
19. Clement, S, Rathakrishnan, E. Characteristics of sonic jets with tabs. Shock Waves 2006;15:219–27. https://doi.org/10.1007/s00193-006-0017-2.Search in Google Scholar
20. Elangovan, S, Rathakrishnan, E. Studies on high speed jets from nozzles with internal grooves. Aeronaut J 2004;108:43–50. https://doi.org/10.1017/s000192400000498x.Search in Google Scholar
21. Thanigaiarasu, S, Karthick, R, Arun Prasad, R, Syed Musthafa, H, Elangovan, S, Rathakrishnan, E. Numerical simulation of underexpanded sonic jets. Int J Turbo Jet Engines 2013;30:101–9.10.1515/tjj-2012-0023Search in Google Scholar
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Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
