Performance analysis of a planar shaped strut injector based supersonic combustion chamber
-
Sukanta Roga
Abstract
This current work presents the performance analysis of a supersonic combustor interface and flow construction through a scramjet engine with a planar shaped strut injector (PSSI) at the supersonic Mach. An important aspect of this study is discovering the fuel mixing mechanism inside the combustion chamber with PSSI. The novel PSSI configuration can enhance mixing and combustion performance. The scramjet configuration is incorporated with a supersonic inlet air temperature of 1250 K, where the vitiated air follows at Mach 3, and this technique is based on a high accelerating effect of the scramjet propulsion mechanism. Scramjet engines can maintain naturalistic high enthalpy conditions in minimum durations. It is observed that the maximum temperature of 3510 K is attained at the recirculating zones produced because of undulation enlargement and therefore the fuel jet losses concentration whereas the maximum combustion efficiency of 86 % is investigated from the current research work.
Acknowledgments
The author expresses his sincere gratitude to the CFD Lab Coordinator, VNIT Nagpur.
-
Research ethics: Not applicable.
-
Author contributions: The author has accepted responsibility for the entire content of this manuscript and approved its submission.
-
Competing interests: The author declare that he has no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.
-
Research funding: None declared.
-
Data availability: Not applicable.
Abbreviations and nomenclature
- a
-
Mole fraction of oxygen in the feed air
- CFD
-
Computational fluid dynamics
- DMD
-
Dynamic mode decomposition
- K
-
Turbulence kinetic energy [J/kg = m2/s2]
- M
-
Molar weight [g/m]
- Pa
-
Pascal
- PSSI
-
Planar shaped strut injector
- SST
-
Shear stress transport
- Ρ
-
Density of hydrogen [kg/m3]
- kω
-
Specific turbulence dissipation rate [m2/s3]
- H2
-
Hydrogen
- X k
-
Propagation of turbulence kinetic energy.
-
-
Hydrogen mass fraction
- G ω
-
Propagation of ω
- Y ω
-
Dissipation of ω
- Z k and Z ω
-
User-defined source terms
- η Comb
-
Combustion efficiency
- Γ k
-
Effective diffusivity of k [m2/s]
- Γ ω
-
Effective diffusivity of ω [m2/s]
References
1. Oevermann, M. Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling. Aero Sci Technol 2000;4:463–80. https://doi.org/10.1016/S1270-9638(00)01070-1.Search in Google Scholar
2. Kummitha, OR, Pandey, KM, Gupta, R. Numerical analysis of hydrogen fueled scramjet combustor with innovative designs of strut injector. Int J Hydrogen Energy 2020;45:13659–71. https://doi.org/10.1016/j.ijhydene.2018.04.067.Search in Google Scholar
3. Peng, J, Cao, Z, Yu, X, Yang, S, Yu, Y, Ren, H, et al.. Analysis of combustion instability of hydrogen fueled scramjet combustor on high-speed OH-PLIF measurements and dynamic mode decomposition. Int J Hydrogen Energy 2020;45:13108–18. https://doi.org/10.1016/j.ijhydene.2020.02.216.Search in Google Scholar
4. Macleod, C, Gerrard, CE. A review of air-fuel mixing and alternative methods in scramjets and scramjet-like engines. J Br Interplanet Soc 2016;69:116–26.Search in Google Scholar
5. Gugulothu, SK. A systematic literature review based on different fuel injection strategies used in scramjet combustors. Heat Transfer-Asian Res 2019;20:1–22. https://doi.org/10.1002/htj.21561.Search in Google Scholar
6. Arora, K, Chakravarthy, K, Chakraborty, D. Large eddy simulation of supersonic, compressible, turbulent mixing layers. Aero Sci Technol 2019;86:592–8. https://doi.org/10.1016/j.ast.2019.01.034.Search in Google Scholar
7. Jindal, S, Kumar, S. CFD modelling of scramjet combustor. In: International conference on theoretical, applied, computational and experimental mechanics. Kharagpur, India; 28-30 December. Singapore: Springer; 2017:1–14 pp.Search in Google Scholar
8. Choubey, G, Devarajan, Y, Huang, W, Mehar, K, Tiwari, M, Pandey, KM. Recent advances in cavity-based scramjet engine – a brief review. Int J Hydrogen Energy 2019;44:13895–909. https://doi.org/10.1016/j.ijhydene.2019.04.003.Search in Google Scholar
9. Huang, W, Yan, L. Numerical investigation on the ram-scram transition mechanism in a strut-based dual-mode scramjet combustor. Int J Hydrogen Energy 2016;41:4799–807. https://doi.org/10.1016/j.ijhydene.2016.01.062.Search in Google Scholar
10. Dharavath, M, Manna, P, Chakraborty, D. Computational study of transverse slot injection in supersonic flow. Defence Sci J 2018;68:121–8. https://doi.org/10.14429/dsj.68.11069.Search in Google Scholar
11. Kiani, M, Houshfar, E, Ashjaee, M. An experimental and numerical study on the combustion and flame characteristics of hydrogen in intersecting slot burners. Int J Hydrogen Energy 2018;43:3034–49. https://doi.org/10.1016/j.ijhydene.2017.12.126.Search in Google Scholar
12. Urzay, J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight. Annu Rev Fluid Mech 2018;50:593–627. https://doi.org/10.1146/annurev-fluid-122316-045217.Search in Google Scholar
13. Chakraborty, D, Anandhanarayanan, K, Raj, A, Shah, V, Krishnamurthy, R. Separation dynamics of air-to-air missile and validation with flight data. Defence Sci J 2018;68:5–11. https://doi.org/10.14429/dsj.68.11480.Search in Google Scholar
14. Thillaikumar, T, Bhale, P, Kaushik, M. Experimental investigations on the strut controlled thrust vectoring of a supersonic nozzle. J Appl Fluid Mech 2020;13:1223–32. https://doi.org/10.36884/JAFM.13.04.31069.Search in Google Scholar
15. Rabadan Santana, E, Weigand, B. Numerical investigations of inlet-combustor interactions for a scramjet hydrogen-fueled engine at a Mach flight number of 8. In: AIAA/3AF Int. Space Planes Hypersonic Syst. Technol. Conf. 2012. American Institute of Aeronautics and Astronautics, France; 2012. https://doi.org/10.2514/6.2012-5926.Search in Google Scholar
16. Riggins, DW, McClinton, CR. A computational investigation of flow losses in a supersonic combustor. In: AIAA/SAE/ASME/ASEE, 26th joint propulsion conference 1990: 1–20 pp. Orlando, FL, U.S.A, 1990. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1990-2093.Search in Google Scholar
17. Riggins, DW, McClinton, CR, Vitt, PH. Thrust losses in hypersonic engines part 1: methodology. J Propul Power 1997;13:281–7. https://doi.org/10.2514/2.5160.Search in Google Scholar
18. Pandey, KM, Roga, S, Choubey, G. Computational analysis of hypersonic combustor using strut injector at flight Mach 7. Combust Sci Technol 2015;187:1392–407. https://doi.org/10.1080/00102202.2015.1035371.Search in Google Scholar
19. Roga, S. CFD analysis of Scramjet engine combustion chamber with diamond-shaped strut injector at Flight Mach 4.5. J Phys Conf 2019;1276:012041. https://doi.org/10.1088/1742-6596/1276/1/012041.Search in Google Scholar
20. Roga, S, Pandey, KM. Computational analysis of hydrogen-fueled scramjet combustor using cavities in tandem flame holder. Appl Mech Mater 2015;772:130–5. https://doi.org/10.1088/1742-6596/1276/1/012041.Search in Google Scholar
21. Roga, S, Pandey, KM, Singh, AP. Computational analysis of supersonic combustion using wedge-shaped strut injector with turbulent non-premixed combustion model. Int J Soft Comput Eng 2012;2:344–53.Search in Google Scholar
22. Roga, S. CFD analysis of Scramjet engine combustion chamber with alternating wedge-shaped strut injector at Flight Mach 6.5. Appl Mech Mater 2015;1276:012038. https://doi.org/10.1088/1742-6596/1276/1/012038.Search in Google Scholar
23. Pandey, KM, Roga, S. CFD analysis of supersonic combustion using diamond-shaped strut injector with K-ω non-premixed combustion model. Trans Control Mech Systems 2012;1:114–24.Search in Google Scholar
24. Tomioka, S, Kanda, T, Tani, K, Mitani, T, Shimura, T, Chinzei, N. Testing of a scramjet engine with a strut in M8 flight conditions. In: 34th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit; 1998: 1–8 pp. 13 - 15 July 1998, Cleveland, OH, U.S.A. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.1998-3134.Search in Google Scholar
25. Tomioka, S, Murakami, A, Kudo, K, Mitani, T. Combustion tests of a staged supersonic combustor with a strut. J Propul Power 2001;17:293–300. https://doi.org/10.2514/2.5741.Search in Google Scholar
26. Karimi, MS, Oboodi, MJ. Investigation and recent developments in aerodynamic heating and drag reduction for hypersonic flows. Heat Mass Tran 2019;55:547–69. https://doi.org/10.1007/s00231-018-2416-1.Search in Google Scholar
27. Gürtürk, M, Oztop, HF, Pambudi, NA. CFD analysis of a rotary kiln using for plaster production and discussion of the effects of flue gas recirculation application. Heat Mass Transfer 2018;54:2935–50. https://doi.org/10.1007/s00231-018-2336-0.Search in Google Scholar
28. Jeyakumar, SP, Patale, AS, Sharma, P. Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor. Int J Turbo Jet Eng 2024;41:449–62. https://doi.org/10.1515/tjj-2023-0067.Search in Google Scholar
29. Sanaka, SP, Kandula, R, Chalamalasetty, KS, Kappala, DR. Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity. Int J Turbo Jet Eng 2023.10.1515/tjeng-2023-0029Search in Google Scholar
30. Kireeti, SK, Gadepalli, RS, Gugulothu, SK. Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor. Int J Turbo Jet Engines 2024;16:15–30. https://doi.org/10.1515/tjj-2021-0071.Search in Google Scholar
31. Hwang, BJ, Min, S. Research progress on mixing enhancement using streamwise vortices in supersonic flows. Acta Astronaut 2022;200:11–32. https://doi.org/10.1016/j.actaastro.2022.07.055.Search in Google Scholar
32. Zhou, W, Xing, K, Dou, S, Yang, Q, Xu, X. Distribution characteristics of a supercritical hydrocarbon fuel jet injected into a high-speed crossflow. Fuel 2023;333:126497. https://doi.org/10.1016/j.fuel.2022.126497.Search in Google Scholar
33. Rajkumar, S, Vasanthakumar, P, Moorthi, AKS, Rathakrishnan, E. Supersonic jet mixing in the presence of two annular co-flow streams. Int J Turbo Jet Engines 2024;41:103–10. https://doi.org/10.1515/tjj-2022-0048.Search in Google Scholar
34. Kireeti, SK, Sastry, GR, Gugulothu, SK. Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor. Int J Turbo Jet Engines 2023;40:s43–57. https://doi.org/10.1515/tjj-2021-0055.Search in Google Scholar
35. Mo, Z, Zhou, D, Shen, X. Parametric analysis of thermal cycle of a short take-off and vertical landing engine. Int J Turbo Jet Eng 2024;41:731–9. https://doi.org/10.1515/tjj-2023-0054.Search in Google Scholar
36. Oevermann, M. Numerical investigation of turbulent hydrogen combustion in a scramjet using flamelet modeling. Aero Sci Technol 2000;4:463–80. https://doi.org/10.1016/S1270-9638(00)01070-1.Search in Google Scholar
37. Tu, J, Yeoh, GH, Liu, C. Computational fluid dynamics, a practical approach, 3rd ed. Oxford, UK: Butterwoth-Heinemann; 2018:1–467 pp.Search in Google Scholar
38. Gerlinger, P, Kasal, P, Boltz, J, Brüggemann, D. Numerical investigation of hydrogen strut injections into supersonic air flows. In: 34th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit; 2000: 22–8 pp. 13 - 15 July 1998, Cleveland, OH, U.S.A. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/2.5559.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
