Review of Propulsion Applications of Detonation Waves

Kailasanath, K.

doi:10.2514/2.1156

Cited by 572 publications

(95 citation statements)

References 74 publications

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“…Many fundamental studies of detonation waves [1][2][3] and of heat engines using detonation waves [4] have been carried out. A pulse detonation engine (PDE) is such a typical heat engine.…”

Section: Introductionmentioning

confidence: 99%

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Matsuoka

Esumi

Ikeguchi

et al. 2012

Combustion and Flame

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We developed a rotary valve for a pulse detonation engine (PDE), and confirmed its basic characteristics and performance. In a square cross-section combustor, we visualized a multi-shot of a pulse detonation rocket engine (PDRE) cycle at an operation frequency of 160 Hz by using a high-speed camera (time resolution: 3.33 μsec, space resolution: 0.4 mm) and a Schlieren method.The propellant filling process and the purge process were confirmed, and each process was modeled.Moreover, we confirmed the processes of detonation wave generation and burned gas blowdown. In addition, we investigated the impact of shortening the passage width of a combustor and negative-time ignition (ignition time is earlier than the end-time of the propellant filling process) on the deflagration-to-detonation transition (DDT) distance and time. The DDT distance did not depend on the passage width of a combustor and decreased under the negative-time ignition condition. With a passage width of 20 mm, the DDT distance decreased by 22% under the negative-time ignition condition to a minimum value (76 ± 8 mm). The DDT time from spark time reached a minimum value (69 ± 14 μsec) under the condition of a passage width of 10 mm and negative-time ignition.The detonation initiation time and the DDT distance were represented by the time until the flame expanded toward the tube-axis one-dimensionally from ignition (characteristic time). We also carried out thrust measurement using a PDRE system composed of a circular cross-section combustor and the newly developed valve. We obtained a stable time-averaged thrust in a wide range of operation frequency (40 Hz -160 Hz) and confirmed the increase of specific impulse due to a partial-fill effect.

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“…Many fundamental studies of detonation waves [1][2][3] and of heat engines using detonation waves [4] have been carried out. A pulse detonation engine (PDE) is such a typical heat engine.…”

Section: Introductionmentioning

confidence: 99%

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Matsuoka

Esumi

Ikeguchi

et al. 2012

Combustion and Flame

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“…Detonation research has attracted much attention in recent years owing to its potential applications in hypersonic propulsion [1,2]. Aluminum (Al) particle detonation is a type of dust detonation, and its research is important in the prevention of industrial explosions [3].…”

Section: Introductionmentioning

confidence: 99%

Effects of different product phases in aluminum dust detonation modeling

Teng

Jiang

2013

Sci. China Phys. Mech. Astron.

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Modeling aluminum (Al) dust detonation is difficult due to uncertainties in the product species and fractions. Recent experiments indicate both gaseous and solid alumina may appear in the detonation product, but only the gaseous one was considered before. To resolve this drawback, we study the effects of different product phases on the detonation parameters with the hybrid combustion model proposed recently. Numerical results demonstrate that the assumption of gaseous product induces high velocity and pressure, while the assumption of solid product induces low velocity and pressure. To clarify how close-to-experiment results have been obtained with one phase assumption, we revisit previous studies and analyze the models. The inconsistency between the product phase and heat release is found, and then one model with variable heat release dependent on the product phase is proposed. Then simulations with both the gaseous and solid products are carried out, and results reveal the necessity of establishing a relationship between the heat release and reaction products. Re s = two-phase Reynolds number t= time, s T= gas temperature, K T p =particle temperature, K u= gas velocity, m/s u p = particle velocity, m/s W i =molecular weight, g/mol x= distance, m = thermal conductivity of gas, W/(m·K) = bulk density of particle, kg/m 3  = dynamic viscosity coefficient, kg/(m·s) Teng H H, et al. Sci China-Phys Mech Astron November (2013) Vol. 56 No. 11 2179 v i = stoichiometric coefficient  = gas or particle density, kg/m 3

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“…The Humphrey cycle is much more efficient than the Brayton cycle, in which a very rapid burning takes place. Due to the rapidity of the process, there is not enough time for pressure equilibration, and the overall process is thermodynamically closer to a constant volume process than to the constant pressure process typical of conventional propulsion systems [39]. The thermodynamic efficiency of Chapmen-Jouget detonation has minimum entropy generation along the Hugoniot curve as compared to other combustion modes, which appear to have a potential thermodynamic advantage [13,40].…”

Section: Theory Process and Previous Work On Pdementioning

confidence: 99%

Pulse Detonation Assessment for Alternative Fuels

Azami

Savill

2017

Energies

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Abstract:The higher thermodynamic efficiency inherent in a detonation combustion based engine has already led to considerable interest in the development of wave rotor, pulse detonation, and rotating detonation engine configurations as alternative technologies offering improved performance for the next generation of aerospace propulsion systems, but it is now important to consider their emissions also. To assess both performance and emissions, this paper focuses on the feasibility of using alternative fuels in detonation combustion. Thus, the standard aviation fuels Jet-A, Acetylene, Jatropha Bio-synthetic Paraffinic Kerosene, Camelina Bio-synthetic Paraffinic Kerosene, Algal Biofuel, and Microalgae Biofuel are all asessed under detonation combustion conditions. An analytical model accounting for the Rankine-Hugoniot Equation, Rayleigh Line Equation, and Zel'dovich-von Neumann-Doering model, and taking into account single step chemistry and thermophysical properties for a stoichiometric mixture, is applied to a simple detonation tube test case configuration. The computed pressure rise and detonation velocity are shown to be in good agreement with published literature. Additional computations examine the effects of initial pressure, temperature, and mass flux on the physical properties of the flow. The results indicate that alternative fuels require higher initial mass flux and temperature to detonate. The benefits of alternative fuels appear significant.

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Review of Propulsion Applications of Detonation Waves

Cited by 572 publications

References 74 publications

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Effects of different product phases in aluminum dust detonation modeling

Pulse Detonation Assessment for Alternative Fuels

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