Effect of variation of hydrogen injection pressure and inlet air temperature on the flow-field of a typical double cavity scramjet combustor

Abstract In the present research work, computational simulation of the double cavity scramjet combustor have been performed by using the two-dimensional compressible Reynolds-Averaged Navier–Stokes (RANS) equations coupled with two equation standard k–ɛ turbulence model as well as the finite-rate/eddy-dissipation reaction model. All the simulations are carried out using ANSYS 14-FLUENT code. Additionally, the computational results of the present double cavity scramjet combustor have been compared with experimental results for validation purpose which is taken from the literature. The computational outcomes are in satisfactory agreement with the experimentally obtained shadowgraph image and pressure variation curve. However, due to numerical calculation, the pressure variation curve obtained computationally is under-predicted in 5 locations. Further, analyses have been carried out to investigate the effect of variation of hydrogen injection pressure as well as the variation of air inlet temperature on the flow-field characteristics of scramjet engine keeping the Mach number constant. The obtained results show that the increase in hydrogen injection pressure is followed by the generation of larger vortex structure near the cavity regions which in turn helps to carry the injectant and also enhance the air/fuel mixing whereas the increase in the inlet temperature of air is characterised by the shifting of incident oblique shock in the downstream of the H2 injection location. Again for T0 = 1500 K, the combustion phenomena remains limited to the cavity region and spreads very little towards the downstream of the combustor.

[1]  Wen Bao,et al.  Numerical and experimental investigation of improving combustion performance of variable geometry dual-mode combustor , 2017 .

[2]  Xianggeng Wei,et al.  Large eddy simulation of flame structure and combustion mode in a hydrogen fueled supersonic combustor , 2015 .

[3]  Li Yan,et al.  Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor , 2012 .

[4]  Li Yan,et al.  Numerical investigation on the ram–scram transition mechanism in a strut-based dual-mode scramjet combustor , 2016 .

[5]  Shigeru Aso,et al.  A study on supersonic mixing by circular nozzle with various injection angles for air breathing engine , 2006 .

[6]  Nickolay Smirnov,et al.  Modeling and simulation of hydrogen combustion in engines , 2014 .

[7]  Jianhan Liang,et al.  Flame Characteristics in Supersonic Combustor with Hydrogen Injection Upstream of Cavity Flameholder , 2008 .

[8]  Wei Huang,et al.  Research status of key techniques for shock-induced combustion ramjet (shcramjet) engine , 2010 .

[9]  Michael Oevermann,et al.  Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling , 2000 .

[10]  Krishna Murari Pandey,et al.  Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor , 2016 .

[11]  Wen Bao,et al.  Flame Transition in Dual-Mode Scramjet Combustor with Oxygen Piloted Ignition , 2014 .

[12]  Yung-Hwan Byun,et al.  A Study of the Mixing Characteristics for Cavity Sizes in SCRamjet Engine Combustor , 2009 .

[13]  Wen Bao,et al.  Flow field characteristics analysis and combustion modes classification for a strut/cavity dual-mode combustor , 2017 .

[14]  V. Babu,et al.  Investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of hydrogen , 2009 .

[15]  W. Jones,et al.  The prediction of laminarization with a two-equation model of turbulence , 1972 .

[16]  E. T. Curran,et al.  Scramjet Engines: The First Forty Years , 2001 .

[17]  L. T. Nguyen,et al.  NASA hypersonic flight demonstrators—overview, status, and future plans , 2004 .

[18]  Jiyuan Tu,et al.  Computational Fluid Dynamics: A Practical Approach , 2007 .

[19]  B. Launder,et al.  The numerical computation of turbulent flows , 1990 .

[20]  Krishna Murari Pandey,et al.  Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector , 2015 .

[21]  Gautam Choubey,et al.  Effect of variation of angle of attack on the performance of two-strut scramjet combustor , 2016 .

[22]  Wang Zhenguo,et al.  Cavities installation schemes affect on the scramjet ignition , 2007 .

[23]  Wei Huang,et al.  Mixing augmentation mechanism induced by the pseudo shock wave in transverse gaseous injection flow fields , 2016 .

[24]  Gautam Choubey,et al.  Investigation on the effects of operating variables on the performance of two-strut scramjet combustor , 2016 .

[25]  Kuo-Cheng Lin,et al.  Dual Cavity Scramjet Operability and Performance Study , 2009 .

[26]  Wang Lu,et al.  Numerical Study of the Combustion Field in Dual-cavity Scramjet Combustor , 2015 .

[27]  Zhenguo Wang,et al.  Numerical simulation on ignition transients of hydrogen flame in a supersonic combustor with dual-cavity , 2016 .

[28]  Wei Huang,et al.  Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle , 2010 .

[29]  Gautam Choubey,et al.  Effect of different strut + wall injection techniques on the performance of two-strut scramjet combustor , 2017 .

[30]  E. Erdem,et al.  Numerical and experimental investigation of transverse injection flows , 2010 .

[31]  Zhenguo Wang,et al.  Numerical and experimental study on flame structure characteristics in a supersonic combustor with dual-cavity , 2015 .

[32]  Antonella Ingenito,et al.  Hydrogen/air supersonic combustion for future hypersonic vehicles , 2011 .

[33]  Daren Yu,et al.  Analysis of combustion mode and operating route for hydrogen fueled scramjet engine , 2013 .

[34]  Gautam Choubey,et al.  Effect of parametric variation of strut layout and position on the performance of a typical two-strut based scramjet combustor , 2017 .

[35]  Wen Bao,et al.  Experimental study of a flush wall scramjet combustor equipped with strut/wall fuel injection , 2014 .

[36]  J. Driscoll,et al.  Combustion characteristics of a dual-mode scramjet combustor with cavity flameholder , 2009 .

[37]  Wang Zhen-guo.  Configuration Effect Analysis of Scramjet Combustor Based on the Integral Balanceable Method , 2009 .

[38]  Jun-tao Chang,et al.  Experimental and numerical investigation on hysteresis characteristics and formation mechanism for a variable geometry dual-mode combustor , 2017 .

[39]  Zhenguo Wang,et al.  Influences of H2O mass fraction and chemical kinetics mechanism on the turbulent diffusion combustion of H2–O2 in supersonic flows , 2012 .

[40]  S. Baek,et al.  Numerical study on supersonic combustion with cavity-based fuel injection , 2004 .

[41]  Nickolay Smirnov,et al.  Hydrogen fuel rocket engines simulation using LOGOS code , 2014 .

[42]  Ning Qin,et al.  Large eddy simulation of a hydrogen-fueled scramjet combustor with dual cavity , 2015 .

[43]  Juntao Chang,et al.  Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis , 2014 .

[44]  Gautam Choubey,et al.  Computational Analysis of Hypersonic Combustor Using Strut Injector at Flight Mach 7 , 2015 .

[45]  Jing Lei,et al.  A parametric study on the aerodynamic characteristics of a hypersonic waverider vehicle , 2011 .

[46]  Zhenguo Wang,et al.  Experimental and Numerical Study on Flame Stabilization in a Supersonic Combustor with Hydrogen Injection Upstream of Cavity Flameholders , 2009 .

[47]  David W. Zingg,et al.  A perspective on turbulence models for aerodynamic flows , 2009 .

[48]  Derek B. Ingham,et al.  Variation of inlet boundary conditions on the combustion characteristics of a typical cavity-based scramjet combustor , 2014 .

[49]  Chih-Jen Sung,et al.  Fuel Injection and Flame Stabilization in a Liquid-Kerosene-Fueled Supersonic Combustor , 2003 .

[50]  Jing Lei,et al.  Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator , 2011 .

[51]  Wen Bao,et al.  Dynamic Characteristics of Combustion Mode Transitions in a Strut-Based Scramjet Combustor Model , 2013 .