Experimental investigation on combustion performance of cavity-strut injection of supercritical kerosene in supersonic model combustor

Sun, Mingbo; Zhong, Zhan; Liang, Jianhan; Wang, Hongbo

doi:10.1016/j.actaastro.2016.05.035

Cited by 92 publications

(12 citation statements)

References 9 publications

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“…11,12 Hsu et al 13 found that placing a strut in front of the cavity is helpful in achieving better flame stabilization with methods of OH-planar laserinduced fluorescence and shadowgraphy. Gu et al 14 reported that the ignition success probability in a cavity is related to the space between the strut and the cavity, whereas Sun et al 15 found that under the strut-injection mode, the coupling effect between the mixing field and the cavity separation zone is crucial for flame stabilization. Based on the above-mentioned advantages, the cavity-strut flame holder is a promising candidate for TBCC combustors with wider flight envelopes.…”

Section: Introductionmentioning

confidence: 99%

Influence of strut on cavity at subsonic speeds: Ignition characteristics

Miao

Fan

Liu

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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In high-speed airflow, the use of cavity and struts in combination can improve fuel distribution and flame-stabilization, but may weaken the ignition performance. Herein, the lean ignition characteristics of several cavity–strut flame holders in a tandem turbine-based combined cycles combustor are experimentally investigated with the flow fields by using particle image velocimetry and high-speed chemiluminescence imaging techniques. Additionally, the effects of the strut structure parameters on the lean ignition performance in the cavity are studied. Experimental results indicate that changes in structural parameters have the opposite effects on the ignition performance and the flame-propagation performance. Reducing the strut inclination angle has a contrary function with the decrease in the cavity–strut space, which also transforms the flame-stabilizing mechanism between strut-stabilizing and cavity-stabilizing, accompanied by the flame morphology behind strut changes from no-flame to intermittent-flame, and finally continuous-flame. The lean ignition limit changes with the structure parameters, mainly due to the inverse change in the mass exchange rate and cavity residence time. Compared with the single cavity, the proper cavity–strut combined structure has a wider lean ignition limit at high subsonic speeds due to the advantage of simultaneously increasing the mass exchange rate and cavity residence time.

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Section: Introductionmentioning

confidence: 99%

Influence of strut on cavity at subsonic speeds: Ignition characteristics

Miao

Fan

Liu

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Currently, the research process of scramjets is mainly focused on liquid fuel, such as kerosene and liquid hydrogen [8,11,[14][15][16][17][18]. However, compared with the liquid fuel scramjets, solid fuel scramjets have the same advantages as traditional solid fuel engines, such as simple structure, high energy density, good maneuverability, and long storage time, etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Xia

et al. 2019

Energies

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.

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“…Sun et al. 15 experimentally investigated the kerosene combustion in supersonic model combustion chamber with different injection schemes. Wang et al.…”

Section: Introductionmentioning

confidence: 99%

“…Sun et al 14 experimentally and numerically studied the flame characteristics of the hydrogen fuel supersonic combustor and showed that the cavity shear layer plays a very important role in the flameholding process. Sun et al 15 experimentally investigated the kerosene combustion in supersonic model combustion chamber with different injection schemes. Wang et al 16 experimentally studied different combustion modes of the hydrogen jet combustion in cavity based scramjet and reported that three combustion modes were observed: cavity assisted jet-wake stabilized combustion, cavity shear-layer stabilized combustion, and combined cavity shear-layer/recirculation stabilized combustion.…”

Section: Introductionmentioning

confidence: 99%

Combustion efficiency and pressure loss balance for the supersonic combustor

Tahsini

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The purpose of this paper is to investigate the effects of intake’s compression process of the scramjet on its flight performance. The hydrogen injection to the supersonic cross-flow is considered as the problem configuration. The finite volume solver is developed to simulate the compressible reacting turbulent flow using the proper reaction mechanism as the finite rate chemistry. The combustion efficiency and the drag force are the most important parameters on the scramjet flight performance, and finding the design point to balance the higher combustion efficiency and the lower minimum drag, which depends on the total pressure loss, can be used to optimize the supersonic combustors. The performance of the supersonic intake is considered here using some oblique shock waves with equal flow-deflection angles to compute the combustor’s inlet condition. The variation of combustion efficiency and total pressure loss is presented for different combustor’s inlet conditions. The results are presented for the constant jet to inlet pressure ratios and also for the constant equivalence ratios, in which the last one is much appropriate and utilized to find the optimum design point of the intake and the combustor, for assumed flight condition.

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Experimental investigation on combustion performance of cavity-strut injection of supercritical kerosene in supersonic model combustor

Cited by 92 publications

References 9 publications

Influence of strut on cavity at subsonic speeds: Ignition characteristics

Influence of strut on cavity at subsonic speeds: Ignition characteristics

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Combustion efficiency and pressure loss balance for the supersonic combustor

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