Journal Menu
Archive
Last Edition
Journal information

Vol.3, No.1, 2024: pp.1-12

Numerical investigation on pulse detonation engine performance under different equivalence ratio

Authors:

Osman Kocaaslan1

1Selçuk University, Huğlu Vocational School, Department of Machinery and Metal Technologies, Konya City, Türkiye

Received: 11 January 2024
Revised: 9 March 2024
Accepted: 22 March 2024
Published: 31 March 2024

Abstract:

Detonation-based engines have a higher thermal efficiency than deflagration-based engines and are therefore widely studied. In this study, the effect of initiation conditions on the detonation wave propagation and the performance of a pulse detonation engine, one type of detonation-based engine, was numerically investigated. Hydrogen-oxygen mixtures with equivalence ratios of φ=0.8, 1.0, and 1.2 were defined as initiation conditions with constant pressure and temperature. The numerical simulations were conducted using the transient explicit density-based solver in the ANSYS Fluent commercial software. The adaptability of the adaptive mesh refinement method in detonation-based engines was explored in the numerical studies, reducing the average total cell count by a factor of 2.617, and obtaining consistent results according to validation studies. The adaptive mesh refinement method was also used in numerical simulations where different equivalence ratios were defined. It was determined that an increase in the equivalence ratio resulted in an increase in the detonation wave velocity. Also, an increase in thrust distribution at the nozzle exit was observed before the blowdown stage, and the calculated thrust values for φ=0.8, φ=1.0, and φ=1.2 were 248.28 N, 264.5 N, and 270.83 N, respectively.

Keywords:

Detonation wave, combustion, pulse detonation engine, computational fluid dynamics, adaptive mesh refinement, equivalence ratio

References:

[1] L.-F. Zhang, S.-J. Zhang, Z. Ma, M.-Y. Luan, J.-P. Wang, Three-dimensional numerical study on rotating detonation engines using reactive Navier-Stokes equations. Aerospace Science and Technology, 93, 2019: 1–10.
https://doi.org/10.1016/j.ast.2019.07.004
[2] E.M. Braun, F.K. Lu, D.R. Wilson, J A. Camberos, Airbreathing rotating detonation wave engine cycle analysis. Aerospace Science and Technology, 27(1), 2013: 201–208. https://doi.org/10.1016/j.ast.2012.08.010
[3] P. Wolański, Detonative propulsion. Proceedings of the Combustion Institute, 34(1), 2013: 125–158.
https://doi.org/10.1016/j.proci.2012.10.005
[4] S. Prakash, V. Raman, C. Lietz, W.A. Hargus, S.A. Schumaker, High Fidelity Simulations of a Methane-Oxygen Rotating Detonation Rocket Engine. AIAA Scitech 2020 Forum, 6-10 January 2020, Orlando, Florida. https://doi.org/10.2514/6.2020-0689
[5] A.C. St. George, R. Driscoll, V. Anand, D.E. Munday, E.J. Gutmark, Fuel Blending as a Means to Achieve Initiation in a Rotating Detonation Engine. 53rd AIAA Aerospace Sciences Meeting, 5-9 January 2015, Kissimmee, Florida.
https://doi.org/10.2514/6.2015-0633
[6] B.R. Bigler, E.J. Paulson, W.A. Hargus, Idealized Efficiency Calculations for Rotating Detonation Engine Rocket Applications. 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 10-12 July 2017, Atlanta, USA.
https://doi.org/10.2514/6.2017-5011
[7] J. Sousa, G. Paniagua, E. Collado Morata, Thermodynamic analysis of a gas turbine engine with a rotating detonation combustor. Applied Energy, 195, 2017: 247–256. https://doi.org/10.1016/j.apenergy.2017.03.045
[8] T. Suzuki, A. Matsuo, Y. Daimon, H. Kawashima, A. Kawasaki, K. Matsuoka, J. Kasahara, Prediction of Pressure Loss in Injector for Rotating Detonation Engines Using Single-element Simulations. AIAA Propulsion and Energy 2020 Forum, 24-28 August 2020. https://doi.org/10.2514/6.2020-3879
[9] R. Driscoll, W. Stoddard, A.S. George, E. Gutmark, Shock Transfer and Shock-Initiated Detonation in a Dual Pulse Detonation Engine/Crossover System. AIAA Journal, 53(1), 2015: 132–139. https://doi.org/10.2514/1.j053027
[10] T. Bussing, G. Pappas, An introduction to pulse detonation engines. 32nd Aerospace Sciences Meeting and Exhibit, 10-13 January 1994, Reno, USA. https://doi.org/10.2514/6.1994-263
[11] K. Kailasanath, Review of Propulsion Applications of Detonation Waves. AIAA Journal, 38(9), 2020: 1698–1708. https://doi.org/10.2514/2.1156
[12] O. Kocaaslan, T. Yasa, K. M. Güleren, A parametric study on the swirler for turbulent combustion. Journal of Thermal Science and Technology, 41(2), 2021: 205-226. https://doi.org/10.47480/isibted.1025923
[13] M.N. Kaya, A.R. Kok, H. Kurt, Comparison of aerodynamic performances of various airfoils from different airfoil families using CFD. Wind and Structures, 32(3), 2021: 239-248. https://doi.org/10.12989/was.2021.32.3.239
[14] N. Alam, K.K. Sharma, K.M. Pandey, Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air. Journal of the Brazilian Society of Mechanical Sciences and Engineering, 41(11), 2019: 502. https://doi.org/10.1007/s40430-019-2024-0
[15] N. Alam, K.K. Sharma, K.M. Pandey, Effects of Various Compositions of the Fuel-Air Mixture on the Pulse Detonation Engine Performance. Combustion, Explosion, and Shock Waves, 55(6), 2019: 708–717.
https://doi.org/10.1134/s0010508219060121
[16] N. Alam, K.K. Sharma, K.M. Pandey, Numerical investigation of flame propagation in pulse detonation engine with variation of obstacle clearance. Journal of Thermal Analysis and Calorimetry, 140, 2019: 2485-2495.
https://doi.org/10.1007/s10973-019-08948-5
[17] V.E. Tangirala, A.J. Dean, P.F. Pinard, B. Varatharajan, Investigations of cycle processes in a pulsed detonation engine operating on fuel–air mixtures. Proceedings of the Combustion Institute, 30(2), 2005: 2817–2824.
https://doi.org/10.1016/j.proci.2004.08.208
[18] A.J. Dean, A. Rasheed, V. Tangirala, P.F. Pinard, Operation and Noise Transmission of an Axial Turbine Driven by a Pulse Detonation Combustor. Turbo Expo 2005, Parts A and B , Vol.6, 6-9 June 2005, Reno, USA. https://doi.org/10.1115/gt2005-69141
[19] D. Valiev, V. Bychkov, V. Akkerman, C.K. Law, L.-E. Eriksson, Flame acceleration in channels with obstacles in the deflagration-to-detonation transition. Combustion and Flame, 157(5), 2010: 1012–1021.
https://doi.org/10.1016/j.combustflame.2009.12.021
[20] A.V. Gaathaug, K. Vaagsaether, D. Bjerketvedt, Experimental and numerical investigation of DDT in hydrogen–Air behind a single obstacle. International Journal of Hydrogen Energy, 37(22), 2012: 17606–17615.
https://doi.org/10.1016/j.ijhydene.2012.03.168
[21] I.O. Moen, M. Donato, R. Knystautas, J.H. Lee, Flame acceleration due to turbulence produced by obstacles. Combustion and Flame, 39(1), 1980: 21–32. https://doi.org/10.1016/0010-2180(80)90003-6
[22] T. Ogawa, V.N. Gamezo, E.S. Oran, Flame acceleration and transition to detonation in an array of square obstacles. Journal of Loss Prevention in the Process Industries, 26(2), 2013: 355–362. https://doi.org/10.1016/j.jlp.2011.12.009
[23] P. Debnath, K.M. Pandey, Computational Study of Deflagration to Detonation Transition in Pulse Detonation Engine Using Shchelkin Spiral. Applied Mechanics and Materials, 772, 2015: 136–140.
https://doi.org/10.4028/www.scientific.net/amm.772.136
[24] S.M. Frolov, V.S. Aksenov, Deflagration-to-detonation transition in a kerosene-air mixture. Doklady Physical Chemistry, 416, 2007: 261–264. https://doi.org/10.1134/s0012501607090072
[25] K. Asato, T. Miyasaka, Y. Watanabe, K. Tanabashi, Combined effects of vortex flow and the Shchelkin spiral dimensions on characteristics of deflagration-to-detonation transition. Shock Waves, 23, 2013: 325–335.
https://doi.org/10.1007/s00193-012-0430-7
[26] T. New, P. Panicker, F. Lu, H. Tsai, Experimental Investigations on DDT Enhancements by Schelkin Spirals in a PDE. 44th AIAA Aerospace Sciences Meeting and Exhibit, 9-12 January 2006, Reno, USA. https://doi.org/10.2514/6.2006-552
[27] W. Wang, H. Qiu, W. Fan, C. Xiong, Experimental Study on DDT Characteristics in Spiral Configuration Pulse Detonation Engines. International Journal of Turbo & Jet-Engines, 30(3), 2013: 261-270. https://doi.org/10.1515/tjj-2013-0028
[28] F.K. Lu, E.M. Braun, Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts. Journal of Propulsion and Power, 30(5), 2014: 1125–1142. https://doi.org/10.2514/1.b34802
[29] J.T. Peace, F.K. Lu, Numerical Study of Pulse Detonation Engine Nozzle and Exhaust Flow Phenomena. 51st AIAA/SAE/ASEE Joint Propulsion Conference, 27-29 July 2015, Orlando, Florida. https://doi.org/10.2514/6.2015-4189
[30] S.-J. Liu, Z. -Y. Lin, W. -D. Liu, W. Lin, M. -B. Sun, Experimental and three-dimensional numerical investigations on H2/air continuous rotating detonation wave. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 227(2), 2012: 326–341. https://doi.org/10.1177/0954410011433542
[31] Z. Lei, X. Yang, J. Ding, P. Weng, X. Wang, Performance of rotating detonation engine with stratified injection. Journal of Zhejiang University-SCIENCE A, 21(9), 2020: 734–744. https://doi.org/10.1631/jzus.a1900383
[32] N. Tsuboi, Y. Watanabe, T. Kojima, A.K. Hayashi, Numerical estimation of the thrust performance on a rotating detonation engine for a hydrogen–oxygen mixture. Proceedings of the Combustion Institute, 35(2), 2015: 2005–2013.
https://doi.org/10.1016/j.proci.2014.09.010
[33] J. Fujii, Y. Kumazawa, A. Matsuo, S. Nakagami, K. Matsuoka, J. Kasahara, Numerical investigation on detonation velocity in rotating detonation engine chamber. Proceedings of the Combustion Institute, 36(2), 2017: 2665–2672.
https://doi.org/10.1016/j.proci.2016.06.155
[34] R. Zhou, J.-P Wang, Numerical investigation of shock wave reflections near the head ends of rotating detonation engines. Shock Waves, 23, 2013: 461–472.
https://doi.org/10.1007/s00193-013-0440-0
[35] S. Yao, X. Han, Y. Liu, J. Wang, Numerical study of rotating detonation engine with an array of injection holes. Shock Waves, 27, 2016: 467–476. https://doi.org/10.1007/s00193-016-0692-6
[36] T.-H. Yi, J. Lou, C. Turangan, J.-Y. Choi, P. Wolanski, Propulsive Performance of a Continuously Rotating Detonation Engine. Journal of Propulsion and Power, 27(1), 2011: 171–181. https://doi.org/10.2514/1.46686
[37] S. Escobar, S. R. Pakalapati, I. Celik, D. Ferguson, P. Strakey, Numerical Investigation of Rotating Detonation Combustion in Annular Chambers. Combustion, Fuels and Emissions, Vol.1A, 3-7 June 2013, San Antonio, USA.
https://doi.org/10.1115/gt2013-94918
[38] H. Zheng, Q. Meng, N. Zhao, Z. Li, F. Deng, Numerical investigation on H2/Air non-premixed rotating detonation engine under different equivalence ratios. International Journal of Hydrogen Energy, 45(3), 2020: 2289–2307.
https://doi.org/10.1016/j.ijhydene.2019.11.014
[39] J. Sun, J. Zhou, S. Liu, Z. Lin, W. Lin, Effects of air injection throat width on a non-premixed rotating detonation engine. Acta Astronautica, 159, 2019: 189–198. https://doi.org/10.1016/j.actaastro.2019.03.067
[40] M.Ó Conaire, H.J. Curran, J.M. Simmie, W.J. Pitz, C.K. Westbrook, A comprehensive modeling study of hydrogen oxidation. International Journal of Chemical Kinetics, 36, 2004: 603–622. https://doi.org/10.1002/kin.20036
[41] C. Lietz, M. Ross, Y. Desai, W. A. Hargus, Numerical investigation of operational performance in a methane-oxygen rotating detonation rocket engine, AIAA SciTech 2020 Forum, 6-10 January 2020, Orlando, Florida.
https://doi.org/10.2514/6.2020-0687
[42] T. Sato, V. Raman, Detonation Structure in Ethylene/Air-Based Non-Premixed Rotating Detonation Engine. Journal of Propulsion and Power, 36(15), 2020: 1-11. https://doi.org/10.2514/1.b37664
[43] NASA Glenn Research Centre, CEARUN rev4 (Chemical Equilibrium Applications) software, 2023.
https://cearun.grc.nasa.gov/ (Accessed: 10 Jan 2024).
[44] T.-H. Yi, C. Turangan, J. Lou, P. Wolanski, J. Kindracki, A Three-Dimensional Numerical Study of Rotational Detonation in an Annular Chamber. 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 5-8 January 2009, Orlando, Florida. https://doi.org/10.2514/6.2009-634

© 2024 by the author. This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License (CC BY-NC 4.0)

Volume 3
Number 1
March 2024.

 

Loading

How to Cite

O. Kocaaslan, Numerical Investigation on Pulse Detonation Engine Performance Under Different Equivalence Ratio. Advanced Engineering Letters, 3(1), 2024: 1-12.
https://doi.org/10.46793/adeletters.2024.3.1.1

More Citation Formats