Review of combustion stabilization for hypersonic airbreathing propulsion

Liu, Qili; Baccarella, Damiano; Lee, Tonghun

doi:10.1016/j.paerosci.2020.100636

Cited by 123 publications

(19 citation statements)

References 438 publications

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“…Significant research and development efforts are underway towards the development of hypersonic vehicles that rely on airbreathing supersonic-combustion RAMJET (SCRAMJET) engines (Choubey et al, 2019). The primary limiting phenomenon in these engines is combustion at supersonic conditions where the residence times are of the order 10 -4 -10 -3 s (Liu et al, 2020). Combustion in these systems is complex, analogous to lighting and holding a match in a hurricane.…”

Section: Hypersonic Air-breathing Propulsionmentioning

confidence: 99%

“…It can take place in a diffusive or premixed mode and involves extremely fast mixing processes and chemical reactions. Hence, the design of SCRAMJET and other highspeed propulsion systems is dependent on, and limited by, flame stabilization at extreme conditions (Huang et al, 2019;Liu et al, 2020). Given the limiting nature of combustion processes in high-speed propulsion systems, understanding the fundamental phenomena and developing innovative flame stabilization schemes represent important research challenges for the development of hypersonic air-breathing propulsion.…”

Section: Hypersonic Air-breathing Propulsionmentioning

confidence: 99%

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Grand challenges in aerospace propulsion

Oehlschlaeger

2022

Front. Aerosp. Eng.

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Section: Hypersonic Air-breathing Propulsionmentioning

confidence: 99%

Section: Hypersonic Air-breathing Propulsionmentioning

confidence: 99%

Grand challenges in aerospace propulsion

Oehlschlaeger

2022

Front. Aerosp. Eng.

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“…e specific heat capacity at constant volume of gasphase mixture is calculated as follows: (14) e molar mass of the gas-phase mixture is calculated as follows:…”

Section: Governing Equationmentioning

confidence: 99%

“…e cavity-based scramjet engine has been widely recognized since it was put forward [14,15], but the flame stabilization mechanism of the cavity has not been fully clarified so far. At present, the research on the flame stabilization of the cavity is mostly based on experimental research.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Flame Stabilization of Cavity-Based Scramjet Combustor Using Compressible Modified FGM Model

Zhang

Zhu

Yang

et al. 2022

International Journal of Chemical Engineering

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The technology of flame stabilization on cavity-based scramjet combustor has great significance in the field of future spacecraft. In this paper, a compressible modified FGM model was established based on the idea of the flamelet model, which was adopted to simulate the unsteady combustion process of the hydrogen transverse jet in the upper cavity of the scramjet. The results show that the compressible modified FGM model can accurately reflect the flow field and the propagation process of the flame in the supersonic cavity, and can capture the fine shock structure in the flow field. The coupling effect of shock waves and shear layer cause the shear layer to quickly destabilize, resulting in the turbulence effect, which promotes the mixing of air and fuel. The boundary layer separation at the upper wall of the combustion chamber will reduce the stability of the shear layer.

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“…The scramjet is an important part of future hypersonic air-breathing propulsion systems because of its excellent thrust performance. 1 However, the existing scramjet technologies are based on the isobaric combustion cycle, which hinders the significant improvement in the engine thrust performance. 2,3 In recent years, a major breakthrough in the near-isochoric combustion cycle of the detonation engine has been achieved.…”

Section: Introductionmentioning

confidence: 99%

Effects of velocity shear layer on detonation propagation in a supersonic expanding combustor

Cai

Mahmoudi

2021

Physics of Fluids

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This study investigates the mechanism of detonation propagation in a stoichiometric hydrogen-oxygen mixture with non-uniform flow velocity entering an expanding combustor. For simulation of the detonation propagation, the Navier-Stokes equations with a one-step two-species chemistry model are solved by employing the hybrid sixth-order weighted essentially non-oscillatory centre difference scheme. The self-sustaining mechanism of detonation propagation in an expanding combustor under the action of non-uniform supersonic flow with a velocity shear layer is revealed. The results show that under the influence of velocity shear layer, two different unburned jets are produced behind the detonation front. These jets are induced by the velocity shear layers and the Prandtl-Meyer expansion fan. The two jets interact and mix gradually. The interaction between the mixed unburned jets and highly unstable shear layers creates large-scale vortices that intensify the turbulent mixing of the unburned jets. Meanwhile, the baroclinic mechanism generates numerous vortices on the boundary of the unburned jet. These vortices promote the mixing of the burned and unburned gases, which eventually leads to the rapid consumption of the unburned pockets. The heat released due to the burning of the unreacted pockets behind the detonation wave, supports a self-sustaining propagation of the detonation wave. When the velocity difference among the shear layers increases, the surface fluctuation of the detonation wave increases.

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Review of combustion stabilization for hypersonic airbreathing propulsion

Cited by 123 publications

References 438 publications

Grand challenges in aerospace propulsion

Grand challenges in aerospace propulsion

Numerical Investigation on Flame Stabilization of Cavity-Based Scramjet Combustor Using Compressible Modified FGM Model

Effects of velocity shear layer on detonation propagation in a supersonic expanding combustor

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