Recent Developments in the Research on Pulse Detonation Engines

Kailasanath, K.

doi:10.2514/2.1933

Cited by 400 publications

(123 citation statements)

References 3 publications

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“…Detonation waves have been studied for many years due to their potential applications in hypersonic propulsion systems, see Kailasanath (2003) and Roy et al (2004). Among the potential applications is the use of oblique detonation wave in continuous detonation wave engines and ram accelerators (Nettleton 2000).…”

Section: Introductionmentioning

confidence: 99%

Numerical study on unstable surfaces of oblique detonations

2014

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In this study, the onset of cellular structure on oblique detonation surfaces is investigated numerically using a one-step irreversible Arrhenius reaction kinetic model. Two types of oblique detonations are observed from the simulations. One is weakly unstable characterized by the existence of a planar surface, and the other is strongly unstable characterized by the immediate formation of the cellular structure. It is found that a high degree of overdrive suppresses the formation of cellular structures as confirmed by the results of many previous studies. However, the present investigation demonstrates that cellular structures also appear with degree of overdrive of 2.06 and 2.37, values much higher than ∼1.8 suggested previously in the literature for the critical value defining the instability boundary of oblique detonations. This contradiction could be explained by the use of differently shaped walls, a straight wall used in this study and a custom-designed curved wedge system so as to induce straight oblique detonations in previous studies. Another possible reason could be due to the low and possibly insufficient resolution used in previously published studies. Hence, simulations with different grid sizes are also performed to examine the effect of resolution on the numerical solutions. Using the present results, analysis also shows that although the characteristic lengths of unstable surfaces are different when the incident Mach number changes, these length scales are proportional to tangential velocities. Hence, the interior time determined by the overdrive degree is identified, and its limitation as the instability parameter is discussed.

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Section: Introductionmentioning

confidence: 99%

Numerical study on unstable surfaces of oblique detonations

2014

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“…One of the propulsion concepts is based on the oblique detonation wave, which derives into the Oblique Detonation Wave Engines (ODWE) and the Ram Accelerators [1]. This kind of propulsion system not only has the advantages of the Scramjet (Supersonic combustion ramjet), but also achieves high thermal cycle efficiency through the detonation [2,3].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the induction zone structure of the oblique detonation waves

2014

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a b s t r a c tOblique detonation waves are simulated to study the induction zone structures with different incident Ma numbers. Three kinds of shock configurations are observed at the end of the induction zone, which are the k-shaped shock, the X-shaped shock and the Y-shaped shock. The X-shaped and Y-shaped shocks appear when the incident Ma is low, and the Y-shaped shock associated with the complicated unstationary process. The induction zone length reaches the maximum value when the X-shaped shock changes into the Y-shaped shock, which indicates different mechanisms deciding the induction zone. The oblique shock wave dominates the induction zone when the incident Ma is high, while the oblique detonation wave dominates the induction zone when the incident Ma is low.

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“…In recent years, the potential application of detonation waves in hypersonic propulsion systems has been widely explored, see Kailasanath (2003) and Roy et al (2004). One kind of detonation propulsion utilizes the oblique detonation wave, which is the basis of oblique detonation wave engines (ODWE) and Ram Accelerators (Nettleton 2000).…”

Section: Introductionmentioning

confidence: 99%

On the transition pattern of the oblique detonation structure

2012

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Oblique detonation waves are simulated to study the evolution of their morphology as gasdynamic and chemical parameters are varied. Although two kinds of transition pattern have previously been observed, specifically an abrupt transition and a smooth one, the determining factors for the transition pattern are still unclear. Numerical results show that the transition pattern is influenced by the inflow Mach number, chemical activation energy and heat release. Despite the fact that these parameters were known to influence the detonation instability, the transition pattern variation cannot be predicted according to the instability criterion. In this study, the difference in the oblique shock and detonation angles is proposed as the criterion to determine the transition pattern with the aid of shock-polar analysis. It is found that the smooth transition will appear when the angle difference is small, while the abrupt transition will occur when the difference is large. The shift from the smooth transition to the abrupt transition occurs when the angle difference is about 15 • -18 • . The previously proposed criterion using the characteristic time ratio is also examined and compared with the present angle difference criterion, and the latter is proved to provide better results.

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Recent Developments in the Research on Pulse Detonation Engines

Cited by 400 publications

References 3 publications

Numerical study on unstable surfaces of oblique detonations

Numerical study on unstable surfaces of oblique detonations

Numerical investigation on the induction zone structure of the oblique detonation waves

On the transition pattern of the oblique detonation structure

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