Detonation-to-shock wave transmission at a contact discontinuity

Peace, James T.; Lu, Frank K.

doi:10.1007/s00193-018-0804-6

Cited by 13 publications

(6 citation statements)

References 18 publications

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“…Eventually, a constant velocity shock will be obtained. The analytic solution for this final transmitted shock has been obtained by previous researchers [24][25][26].…”

Section: Transmission Into An Infinitely Long Inert Layermentioning

confidence: 99%

Transmission of a detonation wave across an inert layer

Tang-Yuk

Lee

et al. 2022

Combustion and Flame

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“…Eventually, a constant velocity shock will be obtained. The analytic solution for this final transmitted shock has been obtained by previous researchers [24][25][26].…”

Section: Transmission Into An Infinitely Long Inert Layermentioning

confidence: 99%

Transmission of a detonation wave across an inert layer

Tang-Yuk

Lee

et al. 2022

Combustion and Flame

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“…In the PDC, the detonation wave propagates until the interface between the air and detonatable mixture, which is determined from the fill fraction of the tube. At this point, the shock wave decouples from the combustion front and the strength of the shock rapidly decays as it propagates, due to viscous effects as well as the Taylor expansion waves behind the detonation (Peace & Lu 2018). The inclusion of a converging nozzle also introduces a significant blockage ratio (75 %) and results in a lower fill fraction from the increased back pressure.…”

Section: Example Of Shock Diffraction Through a Non-quiescent Mediummentioning

confidence: 99%

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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“…Once the detonation wave is transmitted as a shock wave at the contact surface, the Taylor waves overtake the transmitted shock wave. This results in an considerable attenuation of the shock wave as it propagates through the air [35]. Similar to a shock tube also viscous effects contributes to the deceleration of the leading shock wave [36,37].…”

Section: Pdc Operating Conditionsmentioning

confidence: 99%

Investigation of the Exhaust Flow of a Pulse Detonation Combustor at different Operating Conditions based on High-Speed Schlieren and PIV

Haghdoost

Edgington-Mitchell²,

Paschereit

et al. 2019

AIAA Scitech 2019 Forum

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The exhaust flow of a Pulse Detonation Combustor (PDC) is investigated for different operating conditions. The PDC consists of two units, the deflagration to detonation transition section and the exhaust tube with a straight nozzle. High-speed high-resolution schlieren images visualize the shock dynamics downstream of the nozzle. The flow dynamics during one full PDC cycle is examined via high-speed Particle Image Velocimetry. A well-suited solid tracer particle for supersonic reactive flow is determined in a preliminary study to minimize the PIV measurement error. The investigated operating conditions of the PDC differ in fillfraction, which is the percentage of the tube filled with a reactive mixture. With increasing fill-fraction, the flow features grow in size and strength, as the propagation velocity of the leading shock increases. The blow down process of the PDC is characterized by several exhaust and suction phases. An increase in fill-fraction results in a stronger first exhaust phase, while the subsequent suction and exhaust phases remain almost unaffected.

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Detonation-to-shock wave transmission at a contact discontinuity

Cited by 13 publications

References 18 publications

Transmission of a detonation wave across an inert layer

Transmission of a detonation wave across an inert layer

Diffraction of shock waves through a non-quiescent medium

Investigation of the Exhaust Flow of a Pulse Detonation Combustor at different Operating Conditions based on High-Speed Schlieren and PIV

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