Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
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Ritul Raj
,
Sunil Chandel
and
Ranjan Kumar Mishra
Abstract
A computational study of a three ramped dual duct Rocket Based Combined Cycle (RBCC) engine inlet at scramjet mode using different types of MVG (micro vortex generator) arrays were conducted. The definite geometry of engine inlet was operated at hypersonic speeds of Mach 5 and 7 to study the effect of the arrays of delta ramp (DR), rectangular vane (RRV) and ramp vane (RV) on the pressure recovery, exit Mach number, the mass flow rate and Shock wave Boundary Layer interaction (SWBLI). The study was performed considering same heights for all the configurations of MVG array and were positioned at the point of shock impingement on the ramp which caused the separation bubble. The computational analysis was done using k-omega model in Fluent Workbench of Ansys.
Nomenclature (SI units)
- Vane angle (deg):
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Angle of the vane relative to the flow direction (degrees)
- c/h:
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Chord to height ratio of the vane
- s/h:
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Ratio of centre-to-centre inter-device spacing to height
- P:
-
pressure (Pa)
- T:
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Air temperature (K)
- ṁ:
-
Mass flow rate of air (kg/s)
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Research ethics: All research ethics are followed in this work.
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Author contribution: The authors have accepted responsibility for the entire content of this manuscript and approved its submission. Ritul Raj – Meshing, Modelling, CFD Analysis, Writing. Ganapati N. Joshi – Results analysis and writing. Sunil Chandel – Results analysis and writing. Ranjan Kumar Mishra – Results analysis and writing.
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Competing interests: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
References
1. Zhang, T, Wang, Z, Huang, W, Chen, J, Sun, M-B. The overall layout of rocket-based combined-cycle engines: a review. J Zhejiang Univ Sci A 2019;20:163–83. https://doi.org/10.1631/jzus.A1800684.Search in Google Scholar
2. Schnurstein, W, Escher, R. A retrospective on early cryogenic primary rocket subsystem designs as integrated into rocket-based combined-cycle (RBCC) engines. In: 29th joint propulsion conference and exhibit. Monterey, CA; 1993.Search in Google Scholar
3. Shinji Kubota, KT. Aerodynamic performances of a combined cycle inlet. J Propul Power 2006;22:900–4. https://doi.org/10.2514/1.17777.Search in Google Scholar
4. Bulman, RJ. Demonstrating the performance benefits of the strutjet RBCC for space launch architectures. In: 11th annual symposium on propulsion. Propulsion Engineering Research Center, The Pennsylvania State; 1999.Search in Google Scholar
5. Charles, T. An air-breathing launch vehicle concept for single-stage-to orbit. Cleveland, OH; 1999.Search in Google Scholar
6. Gu, R, Sun, M, Cai, Z, Chen, J, Li, P, Dong, Z, et al.. Experimental study on the rocket-ejector system with a throat in the secondary stream. Aerospace Sci Technol 2021;113:106697.10.1016/j.ast.2021.106697Search in Google Scholar
7. Seibenhaar, A, Bulman, M, Bonnar, DK. The strutjet rocket based combined cycle engine. Sacramento, CA; 1998.Search in Google Scholar
8. Liu, X, Shi, L, Liu, P, Fei, Q, He, G. Design and numerical investigations on a dual-duct variable geometry RBCC inlet. Int J Turbo Jet Engines 2017;37:111–22. https://doi.org/10.1515/tjj-2017-0012.Search in Google Scholar
9. Saad, MR, Zare-Behtash, H, Che-Idris, A, Kontis, K. Micro-ramps for hypersonic flow control. Micromachines 2012;3:364–78. https://doi.org/10.3390/mi3020364.Search in Google Scholar
10. Babinsky, H. Understanding micro-ramp control of supersonic shock wave boundary layer interactions. UK: Cambridge University; 2007.10.21236/ADA476419Search in Google Scholar
11. Anderson, JM, Burdisso, R, Ng, W. An active flow distortion control system for serpentine inlets. In: ASME international mechanical engineering congress and exposition. Noise Control and Acoustics; 2002: 169–76 pp.10.1115/IMECE2002-33049Search in Google Scholar
12. Holger Babinsky, NJ. Micro-vortex generator flow control for supersonic engine inlets. In: 45th AIAA aerospace sciences meeting and exhibit. AIAA; 2007.10.2514/6.2007-521Search in Google Scholar
13. Singh, N. Control of Laminar separation bubble using vortex generators. J Appl Fluid Mech 2019;12:891–905. https://doi.org/10.29252/jafm.12.03.29352.Search in Google Scholar
14. Martis, RR, Misra, A. Effect of height of microvortex generators on swept shock wave boundary layer interactions. CEAS Aeronaut J 2013;4:315–26. https://doi.org/10.1007/s13272-013-0075-y.Search in Google Scholar
15. Verma, SB, Manisankar, C. Separation and flow unsteadiness control in a compression corner induced interaction using mechanical vortex generators; effects of vane size and inter-device spacing. Phys Fluids 2022;34:096105. https://doi.org/10.1063/5.0106767.Search in Google Scholar
16. Kumar, VV. Effect of micro-vortex generator in hypersonic inlet. Int J Appl Res Mech Eng 2011;1:10–3. https://doi.org/10.47893/IJARME.2011.1003.Search in Google Scholar
17. Lin, JC. Review of research on low-profile vortex generators to control boundary-layer separation. Prog Aerospace Sci 2002;38:389–420. https://doi.org/10.1016/S03760421(02)00010-6.Search in Google Scholar
18. Gupta, G, Ashok Kumar, A, Sivakumar, R, Kandasamy, J. CFD investigation of shock boundary layer interaction in hypersonic flow and flow control using micro ramps. Aircraft Eng Aerospace Technol 2021;94:862–70. https://doi.org/10.1108/aeat-04-2020-0069.Search in Google Scholar
19. Maheswaran, TG, Prakash, B, Balakrishnan, SR. Computational analysis: the effect of micro vortex generator. Int J Eng Res Technol 2013;02:1100–4. https://doi.org/10.17577/IJERTV2IS50587.Search in Google Scholar
20. Hadi Bagheri, SA. Effects of micro-vortex generators on shock wave structure in a low aspect ratio duct, numerical investigation. Acta Astronaut 2021;178:616–24. https://doi.org/10.1016/j.actaastro.2020.08.012.Search in Google Scholar
21. Kalra, MS, Shewale, Y, Paramasivam, S. Numerical simulation of flow through the inlet and isolator of a Mach 4 dual mode scramjet with micro ramps. In: 2018 joint propulsion conference. Cincinnati, Ohio; 2018.10.2514/6.2018-4935Search in Google Scholar
22. Kaushik, M. Experimental studies on micro-vortex generator controlled shock/boundary-layer interactions in Mach 2.2 intake. Int J Aeronaut Space Sci 2019;20:584–95. https://doi.org/10.1007/s42405-019-00166-5.Search in Google Scholar
23. Yao, Y. Shock induced separating flows in scramjet intakes. Int J Modern Phys 2012:73–83. https://doi.org/10.1142/S2010194512008604.Search in Google Scholar
© 2024 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
- Predicting compressor mass flow rate using various machine learning approaches
- Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1
- Performance analysis of pulse detonation ramjet
- Investigation on flow characteristics and its effect on heat transfer enhancement in a wedge channel with combination of circular, oblong, teardrop, and pencil pin fins
- Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
- Research on performance seeking control of turbofan engine in minimum hot spot temperature mode
- Experimental study on flow field and combustion characteristics of V-gutter and integrated flameholders
- Probabilistic analysis of blade flutter based on particle swarm optimization-deep extremum neural network
- Numerical and experimental study on the critical geometric variation based on sensitivity analysis on a compressor rotor
- Aero-engine direct thrust control based on nonlinear model predictive control with composite predictive model
- Simple model of turbine-based combined cycle propulsion system and smooth mode transition
- Effect of inlet diameter on the flow structure and performance for aluminum-based water-jet engine
- Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber
- Application of KH-RT model in lifting flame of methanol jet atomization
- Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
- Enhancing transonic compressor rotor efficiency by flow analysis-driven blade section modification
- Performance analysis of a planar shaped strut injector based supersonic combustion chamber
- The study of cascading effect in the integration of intake with gas turbine engine bay in subsonic cruise vehicle
Articles in the same Issue
- Frontmatter
- Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
- Predicting compressor mass flow rate using various machine learning approaches
- Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1
- Performance analysis of pulse detonation ramjet
- Investigation on flow characteristics and its effect on heat transfer enhancement in a wedge channel with combination of circular, oblong, teardrop, and pencil pin fins
- Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
- Research on performance seeking control of turbofan engine in minimum hot spot temperature mode
- Experimental study on flow field and combustion characteristics of V-gutter and integrated flameholders
- Probabilistic analysis of blade flutter based on particle swarm optimization-deep extremum neural network
- Numerical and experimental study on the critical geometric variation based on sensitivity analysis on a compressor rotor
- Aero-engine direct thrust control based on nonlinear model predictive control with composite predictive model
- Simple model of turbine-based combined cycle propulsion system and smooth mode transition
- Effect of inlet diameter on the flow structure and performance for aluminum-based water-jet engine
- Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber
- Application of KH-RT model in lifting flame of methanol jet atomization
- Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
- Enhancing transonic compressor rotor efficiency by flow analysis-driven blade section modification
- Performance analysis of a planar shaped strut injector based supersonic combustion chamber
- The study of cascading effect in the integration of intake with gas turbine engine bay in subsonic cruise vehicle
