Shock wave-Boundary Layer Interactions in Wedge-induced Oblique Detonations

Miao, Shikun; Xu, D. Q.; Song, Tao; Yu, Jinming

doi:10.1080/00102202.2019.1646256

Cited by 8 publications

(2 citation statements)

References 33 publications

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“…2017, 2018 a , b ) and shock/detonation-induced boundary layer separation (Ess, Sislian & Allen 2005; Miao et al. 2020), increase the flow complexity in a space-confined combustor and cannot be overlooked in the stabilization of ODWs. These fundamental differences in detonation stabilization between spatially confined and unconfined flow regimes were also pointed out by Higgins (1997) through experiments, where hypervelocity blunt projectiles were fired into detonation chambers with significantly different chamber diameters and various detonation propagation phenomena were observed.…”

Section: Introductionmentioning

confidence: 99%

“…However, the stabilization of an ODW induced by an isolated wedge or cone is only a typical external flow problem, whereas the stabilization of an ODW in an ODE combustor is an internal flow problem because of the geometric constraints of the combustor's internal walls. In particular, the additional factors involved in internal flows, such as the reflection of OSWs/ODWs (Wang et al 2020a,b;Wang, Yang & Teng 2021), shock/detonation-shock/detonation interactions (Xiang et al 2021a,b), shock/detonation-boundary layer interactions (Cai et al 2017(Cai et al , 2018a and shock/detonation-induced boundary layer separation (Ess, Sislian & Allen 2005;Miao et al 2020), increase the flow complexity in a space-confined combustor and cannot be overlooked in the stabilization of ODWs. These fundamental differences in detonation stabilization between spatially confined and unconfined flow regimes were also pointed out by Higgins (1997) through experiments, where hypervelocity blunt projectiles were fired into detonation chambers with significantly different chamber diameters and various detonation propagation phenomena were observed.…”

Section: Introductionmentioning

confidence: 99%

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Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

2022

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The stabilization of oblique detonation waves (ODWs) in an engine combustor is important for the successful applications of oblique detonation engines, and comprehensively understanding the effects of the inviscid reflection of ODWs on their stabilization and the relevant mechanisms is imperative to overall combustor design. In this study, the flow fields of ODW reflections in a space-confined combustor are numerically studied by solving the two-dimensional time-dependent multispecies Euler equations in combination with a detailed hydrogen combustion mechanism. The inviscid Mach reflections of ODWs before an expansion corner are emphasized with different flight Mach numbers, Ma, and different dimensionless reflection locations, ζ ≥ 0 (ζ = 0: the ODW reflects precisely at the expansion corner; ζ > 0: the ODW reflects off the wall before the expansion corner). Two kinds of destabilization phenomena of the inviscid Mach reflection of an ODW induced by different mechanisms are found, namely wave-induced destabilization at large ζ > 0 for moderate (not very low) Ma and inherent destabilization at any ζ > 0 for low Ma. Wave-induced destabilization is attributed to the incompatibility between the pressure ratio across the Mach stem and its relative propagation speed, which is triggered by the action of the secondary reflected shock wave or the transmitted Mach stem on the subsonic zone behind the Mach stem. Inherent destabilization is demonstrated through an in-depth theoretical analysis and is attributed to geometric choking of the flow behind the Mach stem.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

2022

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Oblique detonation wave triggered by a double wedge in hypersonic flow

Teng

Zhang

Yang

et al. 2022

Chinese Journal of Aeronautics

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Effects of wedge-angle change on the evolution of oblique detonation wave structure

et al. 2022

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Compared to pulse detonation engine and rotating detonation engine, oblique detonation engine has the advantage in higher flight Mach number. However, it is still challenging to achieve stabilized oblique detonation wave for a broad range of flight conditions. To control oblique detonation wave, this study focuses on the oblique detonation wave structure evolution induced by changing the wedge angle. Transient two-dimensional simulations are conducted for wedge-stabilized oblique detonation wave in stoichiometric hydrogen/air mixtures. The detailed chemistry of hydrogen combustion is considered and the thermal states of the reactants are determined by the specified flight altitude and Mach number. The angle change between inflow and wedge can be achieved in two ways: inflow-angle change with fixed wedge angle and wedge-angle change with fixed inflow direction. Results indicate that no new autoignition zone exists in the transient wave evolution caused by wedge-angle change, which is different from that of inflow-angle change observed in previous studies. For the wedge-angle change process, the effects of wedge-angle change rate on transient oblique detonation wave structure evolution are further assessed. It is found that the transient oblique detonation wave structure is more sensitive to the wedge-rotation angular velocity for increasing wedge angle (controlled by the thermodynamic properties of the mixture) than that for decreasing wedge angle (controlled by the shock wave dynamic). For the quasi-steady triple-wave structure during wedge-angle decreasing process, a normal detonation wave occurs and becomes dominant in the wave structure evolution, whose formation mechanism is analyzed by the polar curve theory.

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Shock wave-Boundary Layer Interactions in Wedge-induced Oblique Detonations

Cited by 8 publications

References 33 publications

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

Oblique detonation wave triggered by a double wedge in hypersonic flow

Effects of wedge-angle change on the evolution of oblique detonation wave structure

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