Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity
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Srinivas Prasad Sanaka
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Ramanaiah Kandula
Abstract
The objective of the study is realizing the effect of fuel mass flow rate and flight speed on combustion in scramjet engine. DLR conical strut based scramjet combustor configuration was chosen and simulated the chemical reaction between the air and hydrogen fuel. A slot of size 40 mm × 0.295 mm provided at the center of the strut to injected hydrogen fuel from the rare side in to the downstream flow. ICEM CFD software is used for the generation of structured elements in computational domain for three dimensional flow analyses. Standard k-epsilon turbulence model and species transport equation is used in ANSYS fluent solver. The predicted temperature, velocity distribution along the axial length was compared with the experimental results and validated. The temperature distribution at different Mach numbers and mass flow rate reveals that the peak temperature increased with the flight speed and inlet fuel mass flow rate. The peak temperature noticed at the center of the combustor is around 3500 K at a flight speed of Mach 4. The predicted variation of temperature, pressure, velocity in the combustor and the flow structure for reacting flow facilitate good understanding of the combustion process in scramjet combustor.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Kummitha, OR, Pandey, KM. Hydrogen fueled scramjet combustor with a wavy-wall double strut fuel injector. Fuel 2021;304:121425. https://doi.org/10.1016/j.fuel.2021.121425.Search in Google Scholar
2. Huang, W, Wang, ZG, Luo, SB, Liu, J. Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chin Sci Bull 2011;56:3871–7. https://doi.org/10.1007/s11434-011-4823-2.Search in Google Scholar
3. Pan, Y, Tan, JG, Liang, JH, Liu, WD, Wang, ZG. Experimental investigation of combustion mechanisms of kerosene-fueled scramjet engines with double-cavity flameholders. Acta Mech Sin 2011;27:891–7. https://doi.org/10.1007/s10409-011-0470-8.Search in Google Scholar
4. Pandey, KM, Sivasakthivel, T. Recent advances in scramjet fuel injection – a review. Int J Chem Eng 2010;1:294–301. https://doi.org/10.7763/ijcea.2010.v1.52.Search in Google Scholar
5. Sankaran, A, Sundararaj, K. A CFD based numerical analysis of scramjet combustor. Int J Eng Res Technol 2016;5:1–4.10.17577/IJERTV5IS120001Search in Google Scholar
6. Animhons, A, Nirmalkumar, D, Johnsree, A. Numerical simulation of scramjet engine. Int J Eng Res Gen Sci 2015;3:420–41.Search in Google Scholar
7. Soni, RK, De, A. Investigation of strut-ramp injector in a scramjet combustor: effect of strut geometry, fuel and jet diameter on mixing characteristics. J Mech Sci Technol 2017;31:1169–79. https://doi.org/10.1007/s12206-017-0215-0.Search in Google Scholar
8. Dharavath, M, Manna, P, Chakraborty, D. Thermochemical exploration of hydrogen combustion in generic scramjet combustor. Aero Sci Technol 2013;24:264–74. https://doi.org/10.1016/j.ast.2011.11.014.Search in Google Scholar
9. Tourani, C. Computational simulation of scramjet combustors – a comparison between quasi-one dimensional and 2-D numerical simulations. In: Proc. 17th AIAA international space planes and hypersonic systems and technologies conference. San Francisco: California; 2011:11–4 pp.10.2514/6.2011-2285Search in Google Scholar
10. Zhang, H, Zhao, M, Huang, Z. Large eddy simulation of turbulent supersonic hydrogen flames with OpenFOAM. Fuel 2020;282:118812. https://doi.org/10.1016/j.fuel.2020.118812.Search in Google Scholar
11. Cai, Z, Liu, X, Gong, C, Sun, M, Wang, Z, Bai, XS. Large eddy simulation of the fuel transport and mixing process in a scramjet combustor with rearwall-expansion cavity. Acta Astronaut 2016;126:375–81. https://doi.org/10.1016/j.actaastro.2016.05.010.Search in Google Scholar
12. Verma, KA, Pandey, KM, Sharma, KK. Impact of parametric variation on combustion characteristics of hydrogen-fueled strut based scramjet combustor at supersonic speed. Int J Energy Res 2020;44:1–20. https://doi.org/10.1002/er.5822.Search in Google Scholar
13. Athithan, AA, Jeyakumar, S, Sczygiol, N, Urbanski, M, Hariharasudan, A. The combustion characteristics of double ramps in a strut-based scramjet combustor. Energies 2021;14:831–51. https://doi.org/10.3390/en14040831.Search in Google Scholar
14. Verma, KA, Pandey, KM, Ray, M, Sharma, KK. The numerical investigation of combustion performance of scramjet combustor with variation in angle of attack. Results Eng 2022;15:1–11. https://doi.org/10.1016/j.rineng.2022.100507.Search in Google Scholar
15. Cao, C, Ye, T, Zhao, M. Large eddy simulation of hydrogen/air scramjet combustion using tabulated thermo-chemistry approach. Chin J Aeronaut 2015;28:1316–27. https://doi.org/10.1016/j.cja.2015.08.008.Search in Google Scholar
16. Ding, HM, Zhuo, CF, Hu, WJ, Deng, HY, Chen, X. Numerical study on the effect of jet on the operation of powder fuel scramjet. J Appl Fluid Mech 2022;15:117–27.10.47176/jafm.15.01.32880Search in Google Scholar
17. Luo, F, Song, W, Li, J, Chen, W, Long, Y. Experimental study of kerosene supersonic combustion with pilot hydrogen and fuel additive under low flight Mach conditions. Energy J 2021;222:119858. https://doi.org/10.1016/j.energy.2021.119858.Search in Google Scholar
18. Sebastin, JS, Jeyakumar, S, Karthik, K. The non-reacting flow characteristics of pylon and wall injections in a dual combustion ramjet engine. Int J Engine Res 2021;23:1495–502. https://doi.org/10.1177/14680874211017856.Search in Google Scholar
19. Savino, R, Pezzella, G. Numerical analysis of supersonic combustion ramjet with upstream fuel injection. Int J Numer Methods Fluid 2003;43:165–81. https://doi.org/10.1002/fld.602.Search in Google Scholar
20. Gugulothu, SK. Significance of fluid flow characteristics in the hydrogen-fuelled scramjet combustor using flame stabilisation analysis. Aust J Mech Eng 2019;19:1–11.10.1080/14484846.2019.1601064Search in Google Scholar
21. Swain, TK, Kishan, PA, Kumar, S. Evaluation of fuel and air mixing in a scramjet engine using an asymmetric strut-based fuel injection using CFD. Combust Sci Technol 2020;194:1–22.10.1080/00102202.2020.1791838Search in Google Scholar
22. Oamjee, A, Sadanandan, R. Effects of pylon geometry on mixing enhancement in a scramjet pylon-cavity flame holder. Aeronaut J 2020;124:1–19. https://doi.org/10.1017/aer.2020.27.Search in Google Scholar
23. Choi, J. Parametric scramjet analysis [Electronic theses and dissertations]; 2014:535 p.Search in Google Scholar
24. Wang, P. The model constant A of the eddy dissipation model. Prog Comput Fluid Dynam Int J 2016;16:118–25. https://doi.org/10.1504/pcfd.2016.075154.Search in Google Scholar
25. Magnussen, BF, Hjertager, BH. Sixteenth symposium (international) on combustion. Pittsburgh: The Combustion Institute; 1976:719–29 pp.10.1016/S0082-0784(77)80366-4Search in Google Scholar
26. Waidmann, W, Alff, F, Bohm, M, Brummund, U, Clauß, W, Oschwald, M. Supersonic combustion of hydrogen/air in a scramjet combustion chamber. Space Technol 1995;15:421–9.10.1016/0892-9270(95)00017-8Search in Google Scholar
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Articles in the same Issue
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Articles in the same Issue
- Frontmatter
- Numerical investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel
- An efficient flow control technique based on co-flow jet and multi-stage slot circulation control applied to a supercritical airfoil
- Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity
- Installed performance seeking control based on supersonic variable inlet/engine coupling model
- Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation
- The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion
- Flow structure comparison of film cooling versus hybrid cooling: a CFD study
- Experimental investigation on a Jeffcott rotor with combined coupling misalignment using time-frequency analysis
- Effect of free boundary on the performance of single expansion nozzle
- Optimization and numerical investigation of combined design of blade and endwall on rotor 67
- Numerical study on the effect of distortion of S-duct on flow field and performance of a full annulus transonic fan
- Research on a high-precision real-time improvement method for aero-engine component-level model
- Uncertainty quantification by probabilistic analysis of circular fins
- Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine
- Study on the water ingestion performance of compressor with inlet particle separator
- The role of volume effect on the transient behavior of a transonic compressor
- Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall
- Numerical study of the impact of hydrogen addition, swirl intensity and equivalence ratio on methane-air combustion
- Active subspace-based performance analysis of supersonic through-flow fan rotor
- Assessment of performance degradation of a mixed flow low bypass turbofan engine through GasTurb simulation
- Numerical investigation of tip clearance flow in a variable geometry turbine with non-uniform partial clearance
