The present work deals with the implication of injection angle and jet-to-cross flow ratio on the combustor performance of a cavity-based scramjet combustor. Unsteady, two-dimensional compressible flow through the scramjet combustor is considered to comprehend the effects of Mach number (Ma), jet-to-cross flow ratio () and injection angle (α) on the combustion characteristics. Results are presented for the following range of parameters: 2.0 ≤ Ma ≤ 2.7; 15° ≤ α ≤ 60° and 0.5 ≤ ≤ 1.2. Intense recirculation zone is observed at θ = 45° irrespective of inlet Mach number which are quintessential for proper mixing. Further, the size of the recirculation zone is the largest when jet-to-cross flow ratio is equal to 0.8 acting as a precursor for enhanced mixing performance. Moreover, static pressure reaches an optimum value at injection angle of 45° beyond which further increase would result in thermal choking. Our study reveals that mixing is improved with an increase in Mach number (Ma). It is observed that the size of the recirculation zone is strongly dependent on the jet-to-cross flow pressure ratio along with the injection angle. To put it in a nutshell, the injection angle of 45° along with a jet-to-cross flow pressure ratio of 0.8 is conducive the optimal performance in scramjet combustor.
ChangJZhangJBaoW,et al.Research progress on strut-equipped supersonic combustors for scramjet application. Prog Aerosp Sci2018; 103: 1–30.
2.
ChangJLiNXuK, et al.Recent research progress on unstart mechanism, detection and control of hypersonic inlet. Prog Aerosp Sci2017; 89: 1–22.
3.
QinFHuangZWHeGQ, et al.Flame stabilization mechanism study in a hydrogen-fueled model supersonic combustor under different air inflow conditions. Int J Hydrogen Energy2017; 42: 21360–21370.
4.
WangZCaiZSunM, et al.Large eddy simulation of the flame stabilization process in a scramjet combustor with rearwall-expansion cavity. Int J Hydrogen Energy2016; 41: 19278–19288.
5.
CaiZZhuXSunM, et al.Experiments on flame stabilization in a scramjet combustor with a rear-wall-expansion cavity. Int J Hydrogen Energy2017; 42: 26752–26761.
6.
GerdroodbaryMBMokhtariMFallahK,et al.The influence of micro air jets on mixing augmentation of transverse hydrogen jet in supersonic flow. Int J Hydrogen Energy2016; 41: 22497–22508.
7.
GerdroodbaryMBJahanianOMokhtariM. Influence of the angle of incident shock wave on mixing of transverse hydrogen micro-jets in supersonic crossflow. Int J Hydrogen Energy2015; 40: 9590–9601.
8.
SmirnovNNBetelinVBNikitinVF, et al.Detonation engine fed by acetylene–oxygen mixture. Acta Astronaut2014; 104: 134–146.
Ben-YakarAHansonRK. Cavity flame-holders for ignition and flame stabilization in scramjets: an overview. J Propul Power2001; 17: 869–877.
11.
RasmussenCCDriscollJFCarterCD,et al.Characteristics of cavity-stabilized flames in a supersonic flow. J Propul Power2005; 21: 765–768.
12.
ChoubeyGPandeyKM. Effect of parametric variation of strut layout and position on the performance of a typical two-strut based scramjet combustor. Int J Hydrogen Energy2017; 42: 10485–10500.
13.
JeongEO’ByrneSJeungIS,et al.Investigation of supersonic combustion with angled injection in a cavity-based combustor. J Propul Power2008; 24: 1258–1268.
14.
XianyuWXiaoshanLMengD, et al.Experimental study on effects of fuel injection on scramjet combustor performance. Chin J Aeronaut2007; 20: 488–494.
15.
Abu-FarahLHaidnOJKauHP. Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor. Propulsion and Power Research2014; 3: 175–186.
16.
BaurleRAEklundDR. Analysis of dual-mode hydrocarbon scramjet operation at Mach 4-6.5. J Propul Power2002; 18: 990–1002.
17.
MahtoNKChoubeyGSuneethaL,et al.Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor. Acta Astronaut2016; 128: 540–550.
18.
MickaDDriscollJ. Dual-mode combustion of a jet in cross-flow with cavity flameholder. In46th AIAA Aerospace Sciences Meeting and Exhibit 2008 (p. 1062).
19.
HuangWJinLYanL,et al.Influence of jet-to-crossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps. Int J Hydrogen Energy2014; 39: 21242–21250.
20.
GerdroodbaryMBAminiYGanjiDD,et al.The flow feature of transverse hydrogen jet in presence of micro air jets in supersonic flow. Adv Space Res2017; 59: 1330–1340.
21.
HuangWTanJGLiuJ,et al.Mixing augmentation induced by the interaction between the oblique shock wave and a sonic hydrogen jet in supersonic flows. Acta Astronaut2015; 117: 142–152.
22.
LiLQHuangWYanL, et al.Mixing enhancement and penetration improvement induced by pulsed gaseous jet and a vortex generator in supersonic flows. Int J Hydrogen Energy2017; 42: 19318–19330.
23.
LandsbergWOCurranDVeeraragavanA. Experimental flameholding performance of a scramjet cavity with an inclined front wall. Aerosp Sci Technol2022; 126: 107622.
24.
NairPPSuryanANarayananV. Modal analysis of mixing characteristics in scramjet combustor with passive struts. Int J Hydrogen Energy2022; 47: 34656–34675.
25.
RostamianMMaddahSRostamiyanY. Computational study of hydrogen and air co-flow jets mixing in dual-combustor ramjet in presence of ramp shock generator. Proc Inst Mech Eng G: J Aerosp Eng2023; 237: 1511–1519.
26.
LiXLiuWPanY,et al.Experimental investigation on the ignition limits of a kerosene-fueled cavity in model scramjet combustor. Proc Inst Mech Eng G: J Aerosp Eng2023; 237: 2442–2450.
27.
LiXLiuWPanY,et al.Experimental investigation on the flame stabilization modes of liquid kerosene in a cavity-based scramjet combustor. Proc Inst Mech Eng G: J Aerosp Eng2023; 237: 1464–1474.
28.
LiLRongCHuS, et al.Intelligent variable strut for combustion performance optimization of a wide-range scramjet engine. Int J Hydrogen Energy2024; 49: –3.
29.
SunYZhengSJiangL,et al.Effect of thermal boundary condition and turbulent models on the combustion simulation of ethylene-fueled scramjet combustor. Phys Fluids2023; 35: 9.
30.
YaoWLiuHZhangZ, et al.Effects of thermal/chemical nonequilibrium on a high-mach ethylene-fueled scramjet. J Propul Power2023: 1–8. doi:https://doi.org/10.2514/1.B39007.
31.
RajaTSivanandiPDhandabaniS,et al.Exploratory of novel thermal barrier coating on diesel engine performance. Proc Inst Mech Eng E: J Process Mech Eng2023; 237: 2083–2092.
32.
AltunŞAdinMŞİlçinK. Monohydric aliphatic alcohols as liquid fuels for using in internal combustion engines: a review. Proc Inst Mech Eng E: J Process Mech Eng2023; 09544089231160472. doi:https://doi.org/10.1177/09544089231160.
33.
WangHWangZSunM,et al.Combustion characteristics in a supersonic combustor with hydrogen injection upstream of cavity flameholder. Proc Combust Inst2013; 34: 2073–2082.
34.
AnsysAF, 14.0 Theory Guide, ANSYS inc. 2011.
35.
MickaDJ. Combustion stabilization, structure, and spreading in a laboratory dual-mode scramjet combustor. Doctoral dissertation, University of Michigan, 2010.
36.
MickaDJDriscollJF. Combustion characteristics of a dual-mode scramjet combustor with cavity flameholder. Proc Combust Inst2009; 32: 2397–2404.
37.
MickaDDriscollJ. Reaction zone imaging in a dual-mode scramjet combustor using CH-PLIF. In44th AIAA/ASME/SAE/ASEE joint propulsion conference & exhibit 2008 (p. 5071).
38.
HuangWLuoSLiuJ,et al.Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle. Sci China Technol Sci2010; 53: 2725–2733.
39.
TuJYeohGHLiuC. Computational fluid dynamics: a practical approach. Butterworth: Heinemann, 2018.
40.
HuangWWangZLuoS,et al.Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chin Sci Bull2011; 56: 3871–3877.
41.
JonesWWhitelawJH. Calculation methods for reacting turbulent flows: a review. Combust Flame1982; 48: 1–26.
42.
LiuCWangZSunM, et al.Characteristics of the hydrogen jet combustion through multiport injector arrays in a scramjet combustor. Int J Hydrogen Energy2018; 43: 23511–23522.
43.
WangHSunMYangY,et al.A passive scalar-based method for numerical combustion. Int J Hydrogen Energy2015; 40: 10658–10661.
44.
FraserAWMartinEBMorrisAJ. Neural network modelling and prediction in multipass steel processing. Proc Inst Mech Eng E: J Process Mech Eng2004; 218: 121–132.
45.
ÖzgörenYÖÇetinkayaSSarıdemirS, et al.Artificial neural network based modelling of performance of a beta-type stirling engine. Proc Inst Mech Eng E: J Process Mech Eng2013; 227: 166–177.
46.
GommJBWeerasingheMWilliamsD. Diagnosis of process faults with neural networks and principal component analysis. Proc Inst Mech Eng E: J Process Mech Eng2000; 214: 131–143.
47.
SinaeiPTabejamaatS. Large eddy simulation of methane diffusion jet flame with representation of chemical kinetics using artificial neural network. Proc Inst Mech Eng E: J Process Mech Eng2017; 231: 147–163.
48.
KumaranKBabuV. Investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of hydrogen. Combust Flame2009; 156: 826–841.
49.
WaidmannWAlffFBrummundU, et al.Experimental investigation of the combustion process in a supersonic combustion ramjet (SCRAMJET). DGLR Jahrbuch1994: 629–638.
50.
WaidmannWAlffFBöhmM, et al.Supersonic combustion of hydrogen/air in a scramjet combustion chamber. Space Technol1995; 15: 421–429.
51.
GuerraRWaidmannWLaibleC. An experimental investigation of the combustion of a hydrogen jet injected parallel in a supersonic air stream. In3rd International Aerospace Planes Conference 1991 Dec (p. 5102).
52.
SmirnovNNBetelinVBNikitinVF, et al.Accumulation of errors in numerical simulations of chemically reacting gas dynamics. Acta Astronaut2015; 117: 338–355.
53.
SmirnovNNBetelinVBShagalievRM, et al.Hydrogen fuel rocket engines simulation using LOGOS code. Int J Hydrogen Energy2014; 39: 10748–10756.
54.
HuangWWangZGLiSB,et al.Influences of H2O mass fraction and chemical kinetics mechanism on the turbulent diffusion combustion of H2–O2 in supersonic flows. Acta Astronaut2012; 76: 51–59.
55.
HuangWYanL. Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows. J Zhejiang Univ Sci2013; 14: 554–564.
56.
GaoZLeeC. Numerical research on mixing characteristics of different injection schemes for supersonic transverse jet. Sci China Technol Sci2011; 54: 883–893.
57.
HuangWMaLPourkashanianM, et al.Parametric effects in a scramjet engine on the interaction between the air stream and the injection. Proc Inst Mech Eng G: J Aerosp Eng2012; 226: 294–309.
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