Thermal auto-ignition in high-speed droplet-laden mixing layers

Ren, Zhaoxin; Wang, Bing; Xie, Qiaofeng; Wang, Daolian

doi:10.1016/j.fuel.2016.11.073

Cited by 33 publications

(7 citation statements)

References 38 publications

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“…The drag force due to the interphase slip velocity acting on the droplet is modeled, and the heat convection is calculated. Under the assumption made as such, the position (x d,i ), velocity (u d,i ), temperature (T d ), and mass (m d ) of a single droplet are controlled by the following equations [18]:…”

Section: Governingmentioning

confidence: 99%

Effects of Flow Compressibility on Two-Phase Mixing in Supersonic Droplet-Laden Flows

Ren

Wang

Zhang

2020

International Journal of Aerospace Engineering

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This research addresses a numerical analysis on the effects of flow compressibility on the characteristics of droplet dispersion, evaporation, and mixing of fuel and air according to the simulation of the spatially developing supersonic shear flows laden with evaporating n-decane droplets. A sixth-order hybrid WENO numerical scheme is employed for capturing the unsteady wave structures. The influence of inflow convective Mach number ( M c ), representing the high-speed flow compressibility, on the two-phase mixing is analyzed, in which M c is specified from 0.4 to 1.0. It is found that the shearing vortex is compressed spatially as M c increases, associated with the alternate distributions of compression and expansion regimes in the flow field. The flow compressibility changes not only the vortex structures but also the aerothermal parameters of the shear flows, and further influences the dispersion and evaporation of droplets. The two-phase mixing efficiency is observed to decrease as M c increases.

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Section: Governingmentioning

confidence: 99%

Effects of Flow Compressibility on Two-Phase Mixing in Supersonic Droplet-Laden Flows

Ren

Wang

Zhang

2020

International Journal of Aerospace Engineering

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“…Meanwhile, a lower combustor inlet Mach number M 3 improves the ignition and combustion characteristics of the supersonic combustion process as well as promotes flame stability. 9 Hence, a thrust control strategy is devised in this study, where the combustor inlet Mach number M 3 is used as the control variable. In order to determine the minimum combustor inlet Mach number M3s subject to the operation constraints and desired thrust output of the scramjet engine, the operating parameters of the compression and combustion processes are varied based on the operating conditions of the scramjet engine.…”

Section: Thrust Control Strategy: the Minimum Combustor Inlet Mach Numentioning

confidence: 99%

“…The value of b is assumed to be kept constant at 0.90. The Rayleigh loss in the supersonic combustion process is significant and the total pressure recovery b is a figure of merit of the combustion process even though it is an implicit parameter in equations (7) to (9).…”

Section: Supersonic Combustion Processmentioning

confidence: 99%

“…Ignition and flame stabilization are challenging problems. [6][7][8][9] The flowfield and combustion characteristics in the combustor of a scramjet are strongly influenced by the combustor inlet Mach number M 3 . On the one hand, a higher combustor inlet Mach number M 3 may reduce the combustor inlet pressure p 3 to a level below the minimum permissible limit, which occurs unexpectedly in hypersonic flights to avoid an excessive length required to complete the reaction.…”

Section: Introductionmentioning

confidence: 99%

“…Numerical simulations have been performed to investigate the flow structure and flowfield characteristics inside the scramjet. [8][9][10][11] Ground and flight tests have been conducted to determine the performance metrics of the scramjet engine at various operating conditions. However, it is not possible to investigate the overall performance of the scramjet engine over a wide range of flight and operating conditions due to limitations in the measurement techniques.…”

Section: Introductionmentioning

confidence: 99%

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Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine

Zhang

Wang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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A lower combustor inlet Mach number is desirable in order to design a compact, lightweight combustor and boost the overall performance of the scramjet engine. In this study, a thrust control strategy is proposed for a hydrogen-fueled scramjet taking into account the operating limitations, which is called the minimum combustor inlet Mach number rule since the combustor inlet Mach number is used as the control variable. By scheduling the fuel supply and modifying the intake geometry, the combustor inlet Mach number can be minimized while ensuring a certain thrust output within the operation constraints. In this manner, the scramjet engine can be operated with high specific thrust and low fuel consumption throughout the flight envelope. The thrust control strategy is further applied to a hydrogen-fueled scramjet in the hypersonic flight regime. Because the combustor inlet Mach number varies with flight conditions, the thrust strategy can be applied in practice by monitoring the following aerothermodynamic parameters in different flight regimes instead: (1) combustor outlet Mach number, (2) combustor inlet static temperature, and (3) combustor outlet static temperature. Furthermore, the effects of the thrust output on the division of flight regime are investigated, and the overall performance of the hydrogen-fueled scramjet engine obtained from applying the thrust control strategy is discussed in detail.

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Stabilization of wedge-induced oblique detonation waves in pre-evaporated kerosene–air mixtures with fluctuating equivalence ratios

et al. 2021

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Thermal auto-ignition in high-speed droplet-laden mixing layers

Cited by 33 publications

References 38 publications

Effects of Flow Compressibility on Two-Phase Mixing in Supersonic Droplet-Laden Flows

Effects of Flow Compressibility on Two-Phase Mixing in Supersonic Droplet-Laden Flows

Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine

Stabilization of wedge-induced oblique detonation waves in pre-evaporated kerosene–air mixtures with fluctuating equivalence ratios

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