Dynamic evolution of a transient supersonic trailing jet induced by a strong incident shock wave

Haghdoost, Mohammad Rezay; Edgington-Mitchell, Daniel; Nadolski, Maikel; Klein, Rupert; Oberleithner, Kilian

doi:10.1103/physrevfluids.5.073401

Cited by 17 publications

(5 citation statements)

References 29 publications

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“…Artificial oscillations at discontinuities in the numerical scheme (such as the shock) are prevented by limiting the slopes of the reconstruction step using the van-Leer limiter (see Toro (2013) for further details). This numerical scheme has been presented in a number of previous works (Nadolski et al 2019;Rezay Haghdoost et al 2020a and is well validated.…”

Section: Descriptionmentioning

confidence: 99%

“…This mechanism is assessed using an Euler scheme with a quiescent medium. Despite the inherent inviscid assumption, Euler schemes have been demonstrated to be reasonable models for shock diffraction from large angle, sharp-edged geometries such as a 90 • corner (Hillier 1991;Rezay Haghdoost et al 2020a).…”

Section: Isolating the Dominant Mechanisms Of Shock Distortionmentioning

confidence: 99%

“…2019; Rezay Haghdoost et al. 2020 a , b ). Inside the nozzle, the reflected shock (I) has propagated back and forth between the inner surfaces and the centreline of the nozzle.…”

Section: Isolating the Dominant Mechanisms Of Shock Distortionmentioning

confidence: 99%

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Diffraction of shock waves through a non-quiescent medium

et al. 2022

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An investigation of shock diffraction through a non-quiescent background medium is presented using both experimental and numerical techniques. Unlike diffracting shocks in quiescent media, a spatial distortion of the shock front occurs, producing a region of constant shock angle. An example of this process arises in the exhaust from a pulse-detonation combustor. As the background velocity is increased, such as through the inclusion of a converging nozzle at the exhaust, the spatial distortion becomes more apparent. Numerical simulations using a compressible Euler solver demonstrate that the distortion is not due to the geometrical influence of the nozzle, but rather is a function of the magnitude of the background flow velocity. The distortion is studied using a modified geometrical shock dynamics formulation which includes the background flow and is validated against experiments. A simple model is presented to predict the shock distortion angle in the weak-shock limit. Finally, the axial decay behaviour of the shock is investigated and it is shown that the advection of the shock by the background flow delays the arrival of the head and tail of the expansion characteristic at the centreline. This leads to an increase in the rate of decay of the shock Mach number as the background flow velocity is increased.

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Section: Descriptionmentioning

confidence: 99%

Section: Isolating the Dominant Mechanisms Of Shock Distortionmentioning

confidence: 99%

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Diffraction of shock waves through a non-quiescent medium

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“…Time resolved measurement of total pressure behind transient shock waves is very challenging [28][29][30]. In this work, an in-house-made high-frequency total pressure probe is used to measure the total pressure at the exit of the divider.…”

Section: High-frequency Total Pressure Probementioning

confidence: 99%

Numerical and experimental evaluation of shock dividers

et al. 2022

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Mitigation of pressure pulsations in the exhaust of a pulse detonation combustor is crucial for operation with a downstream turbine. For this purpose, a device termed the shock divider is designed and investigated. The intention of the divider is to split the leading shock wave into two weaker waves that propagate along separated ducts with different cross sections, allowing the shock waves to travel with different velocities along different paths. The separated shock waves redistribute the energy of the incident shock wave. The shock dynamics inside the divider are investigated using numerical simulations. A second-order dimensional split finite volume MUSCL-scheme is used to solve the compressible Euler equations. Furthermore, low-cost simulations are performed using geometrical shock dynamics to predict the shock wave propagation inside the divider. The numerical simulations are compared to high-speed schlieren images and time-resolved total pressure recording. For the latter, a high-frequency pressure probe is placed at the divider outlet, which is shown to resolve the transient total pressure during the shock passage. Moreover, the separation of the shock waves is investigated and found to grow as the divider duct width ratio increases. The numerical and experimental results allow for a better understanding of the dynamic evolution of the flow inside the divider and inform its capability to reduce the pressure pulsations at the exhaust of the pulse detonation combustor.

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“…All concepts are based on a periodic combustion process that results in pulsating flow conditions at the combustor outlet. These fluctuations are especially pronounced downstream of a PDC, where propagating detonations ultimately result in shock waves exiting the combustor [3]. However, at the inlet of conventional turbines, steady flow conditions are favorable to ensure good performance and reduced mechanical stress.…”

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confidence: 99%