Numerical and experimental validation for effective cross-sections in pulse detonation engine design
1
조회
0
다운로드
0
인용
0
참고문헌
키워드
초록
Industrial revolution and economic growth in any country is aided and abetted by effective defense research and developmenthand in hand with medical supremacy across the globe. Advent avionics system and advanced defense technology have sprungup from various nations further driving the need for hypersonic speed propulsion systems in transport or military applications. Pulse detonation systems may be an effective cure for such insolvency and may be used as an advanced highspeed propulsionsystem for various applications. The research work discusses the effect of cross-sections like cylinder, square and rectangle inachieving controlled detonation with supersonic velocity at exit and effective pressure for further expansion. The analysisresulted that the cylindrical cross-section with an orifice type blockage at three locations evenly spread throughout the lengthof the tube with 60 percent blockage ratio to be the most effective with maximum exit velocity of 2995.6 m/s and effectivepressure of 10.5 bar for an injection pressure of 100 bar and velocity 0.15 m/s. An experimental model using cold flow wasconducted to ratify the results from the numerical simulation and found to be similar with a differentiation of 14% due to thevariation of the working fluid.
Abstract
Industrial revolution and economic growth in any country is aided and abetted by effective defense research and developmenthand in hand with medical supremacy across the globe. Advent avionics system and advanced defense technology have sprungup from various nations further driving the need for hypersonic speed propulsion systems in transport or military applications. Pulse detonation systems may be an effective cure for such insolvency and may be used as an advanced highspeed propulsionsystem for various applications. The research work discusses the effect of cross-sections like cylinder, square and rectangle inachieving controlled detonation with supersonic velocity at exit and effective pressure for further expansion. The analysisresulted that the cylindrical cross-section with an orifice type blockage at three locations evenly spread throughout the lengthof the tube with 60 percent blockage ratio to be the most effective with maximum exit velocity of 2995.6 m/s and effectivepressure of 10.5 bar for an injection pressure of 100 bar and velocity 0.15 m/s. An experimental model using cold flow wasconducted to ratify the results from the numerical simulation and found to be similar with a differentiation of 14% due to thevariation of the working fluid.
참고문헌 (40)
- T. Endo, , T. of Japan Soc. Aero. Space Sci, 44(146), pp.217~222 (2002)
- S. Yungster, , Comb. Thy and Mod, 10(6), pp.981~1002 (2013)
- P. Srihari, , Def. Sci. J, 65(4), pp.265~271 (2015)
- F. Ma, , J. Prop. Power, 21(4), pp.681~691 (2005)
- S. Yungster, , 41st Aerosp. Sci. Meet. Exhi (2003)
- D. Allgood, , J. of Prop. and Power, 24(6), pp.1317~1323 (2008)
- A. Thattai, "Thes. Diss", ~ (2010)
- M. R. Nalim, , Shoc. Wav, 22(1), pp.23~38 (2012)
- Vizcaino, Jeff, "ERAU Dissert. Thes", ~ (2013)
- D. M. Valli, , Int. J. Inno. Res. Techn. Sci. Eng, 3(4), pp.11229~11237 (2014)
- Y. Wu, , Comb. Flame, 162(6), pp.2660~2669 (2015)
- N. Gopalakrishnan, , AIAA Join. Prop. Conf (2018)
- G. B. Goodwin, , Comb. Flame, 197, pp.145~160 (2018)
- Y. A. Poludnenko, , Sci, 366(6465) (2019)
- S. K. Soni, , Int. J. Emerg. Technol. Adv. Eng, 3(3), pp.458~464 (2013)
- M. R. Amin, , J. Mech. Eng, 51(7-8), pp.484~490 (2005)
- V. N. Tangirala, , Aerosp. Sci. Meet. Exh (2007)
- Y. Shao, , Chinese J. Aero, 23(6), pp.647~652 (2010)
- E. Wintenberger, , Power, 22(3), pp.593~603 (2006)
- K. Kailasanath, , Proc. Combust. Inst, 28(1), pp.595~601 (2000)
- S. M. Frolov, , Dokl. Phys. Chem, 416(1), pp.261~264 (2007)
- C. Johansen, , J. Loss Prev. Process Ind, 26(4), pp.571~585 (2013)
- S. M. Frolov, , Russ. J. Phys. Chem, 2(5), pp.759~774 (2008)
- S. Otsuka, , J. Therm. Sci, 19(6), pp.540~544 (2010)
- F. Zheng, , Jt. Prop. Conf. Exh (2009)
- H. H. Zhang, , Comb. Sci. Technol, 183(10), pp.1069~1082 (2011)
- L. Bachman, , Prop. Eng. For. (AIAA) (2019)
- C. L. Bachman, , Comb, 223, pp.271~283 (2021)
- R. Kaplan, , Comb. Thy. Mod, 23(1), pp.67~86 (2019)
- T. A. Kaemming, , AIAA Sci. Tech. For (2020)
- T. H. Yi, , Aerosp. Sci. Meet. Exh (2006)
- W. A. Stoddard, , Jt. Prop. Conf. Exh (2010)
- T. Xiao-ming, , Eng. Appl. Comput. Fluid Mech, 5(4), pp.499~505 (2011)
- X. He, , J. Sci. Comput, 19(1-3), pp.201~224 (2003)
- F. Ma, , J. Propuls. Power, 24(3), pp.479~490 (2008)
- S. Srikrishnan, , Adv. Stru. Sys. Mat (2020)
- S. Srikrishnan, , IOP Conf. Ser.:Mater. Sci. Eng, pp.992~ (2020)
- S. Srikrishnan, , MATEC Web Conf, 172(02006), pp.1~8 (2018)
- T. Ganesan, , Process. Res, 23(5), pp.625~628 (2022)
- Can Ozturk, "Effects of alloy ratio and coating thickness on temperature distribution of thermal barrier coatings", Journal of Ceramic Processing Research, 21(4), pp.433~441 (2020), 청정에너지연구소[DOI]