Operation of a liquid-fueled and valveless pulse detonation rocket engine at high frequency

Lu, Wei; Fan, Wei; Wang, Ke; Zhang, Qibin; Chi, Yeqing

doi:10.1016/j.proci.2016.07.098

Cited by 24 publications

(5 citation statements)

References 17 publications

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“…Studies on such topics have been performed for decades in different fields, e.g. aerospace propulsion 1,2,3 , internal combustion engine 4,5,6 and shock tube 7,8,9 . Due to the simplicity in geometry and convenience for parametric study, shock-droplet or shock-particle interactions have been extensively investigated in shock tube facilities.…”

Section: Introductionmentioning

confidence: 99%

On the interactions between a propagating shock wave and evaporating water droplets

Huang

Zhang

2020

Physics of Fluids

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One-dimensional numerical simulations based on hybrid Eulerian-Lagrangian approach are performed to investigate the interactions between propagating shock waves and dispersed evaporating water droplets in two-phase gas-droplet flows. Two-way coupling for interphase exchanges of mass, momentum and energy is adopted. Parametric study on shock attenuation, droplet evaporation, motion and heating is conducted, through considering various initial droplet diameters (5-20 μm), number densities (2.5 × 10 11 -2 × 10 12 /m 3 ) and incident shock Mach numbers (1.17-1.9). It is found that the leading shock may be attenuated to sonic wave and even subsonic wave when droplet volume fraction is large and/or incident shock Mach number is low. Attenuation in both strength and propagation speed of the leading shock is mainly caused by momentum transfer to the droplets that interact at the shock front. Total pressure recovery is observed in the evaporation region, whereas pressure loss results from shock compression, droplet drag and pressure gradient force behind the shock front. Recompression of the region between the leading shock and two-phase contact surface is observed when the following compression wave is supersonic. After a critical point, this region gets stable in width and interphase exchanges in mass, momentum, and energy. However, the recompression phenomenon is sensitive to droplet volume fraction and may vanish with high droplet loading. For an incident shock Mach number of 1.6, recompression only occurs when the initial droplet volume fraction is below 3.28 × 10 -5 .

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Section: Introductionmentioning

confidence: 99%

On the interactions between a propagating shock wave and evaporating water droplets

Huang

Zhang

2020

Physics of Fluids

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“…However, the other propulsion system operates on deflagration mode at constant pressure process (Tangirala et al, 2005). The circular crosssection of PDE tube gives better propulsive performance over the rectangular cross-section tube (Jie et al, 2014;Lu et al, 2017;Kuznetsov et al, 2002;Kellenberger and Ciccarelli, 2015;Zheng et al, 2017). There are number of experimental and numerical models studied on the performance of PDE detonation tube at single cycle operation.…”

Section: C-jmentioning

confidence: 99%

“…They are also analyzed the Von-Neumann spike, detonation velocity and C-J Pressure with different grid size and found that one-step overall reaction model is predicted the flow properties with maximum accuracy. (Lu et al, 2017) investigated through one-dimensional simulation of interaction between pressure wave and flame front by using Arrhenius expression with chemical model of hydrogen oxidation. They are observed the propagation and reflection of pressure wave might trigger in cylinder, and lead to very highpressure oscillation.…”

Section: C-jmentioning

confidence: 99%

Numerical Investigation of Combustion Wave Propagation in Obstructed Channel of Pulse Detonation Engine using Kerosene and Butane Fuels

Alam

Pandey

Sharma

2019

JAFM

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The present computational analysis reports the results of combustion phenomenon in 1200 mm long and 60 mm internal circular diameter (D) of three dimensional obstructed combustion chamber (combustor) of the pulse detonation engine (PDE). The simulation is carried out for stoichiometric mixture of two fuels Kerosene-air and Butane-air mixture at atmospheric pressure and temperature of 1 atm and 300 K respectively along with preheated air. The chemical species of Kerosene and Butane (C12H26 and C4H10) fuel are solved by species transport equation and irreversible one-step chemical kinetics model. The propagation speed of flame, detonation wave pressure and deflagration-to-detonation transition (DDT) run-up length are analyzed by three dimensional reactive Navier-Stokes algorithm along with realizable k-ɛ turbulence equation model. The obstacles are placed inside the combustor tube at spacing (s) of 60 mm (1D) and obstacles having blockage ratio (BR) 0.5 for creating perturbation in propagating combustion flame. This resulted in increase of the surface area of propagating flame and reduces deflagration-to-detonation transition (DDT) run-up length.

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“…A PDE utilizing a rotary valve for rapid actuation has been studied [4][5][6]. Furthermore, a valveless detonation system has been devised for PDE operation, eliminating the need for opening and closing valves [7,8]. Without the need for valve actuation, while being continuously supplied, this process requires that both the fuel and the oxidizer undergo combustion and quenching within a single cycle.…”

Section: Introduction 1detonation Enginementioning

confidence: 99%

Investigation of Spray Characteristics for Detonability: A Study on Liquid Fuel Injector and Nozzle Design

Choi,

Oh,

Park

2024

Aerospace

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Detonation engines are gaining prominence as next-generation propulsion systems that can significantly enhance the efficiency of existing engines. This study focuses on developing an injector utilizing liquid fuel and a gas oxidizer for application in detonation engines. In order to better understand the spray characteristics suitable for the pulse detonation engine (PDE) system, an injector was fabricated by varying the Venturi nozzle exit diameter ratio and the geometric features of the fuel injection hole. Analysis of high-speed camera images revealed that the Venturi nozzle exit diameter ratio plays a crucial role in determining the characteristics of air-assist or air-blast atomization. Under the conditions of an exit diameter ratio of Re/Ri = 1.0, the formation of a liquid film at the exit was observed, and it was identified that the film’s length is influenced by the geometric characteristics of the fuel injection hole. The effect of the fuel injection hole and Venturi nozzle exit diameter ratio on SMD was analyzed by using droplet diameter measurement. The derived empirical correlation indicates that the atomization mechanism varies depending on the Venturi nozzle exit diameter ratio, and it also affects the distribution of SMD. The characteristics of the proposed injector, its influence on SMD, and its velocity, provide essential groundwork and data for the design of detonation engines employing liquid fuel.

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Operation of a liquid-fueled and valveless pulse detonation rocket engine at high frequency

Cited by 24 publications

References 17 publications

On the interactions between a propagating shock wave and evaporating water droplets

On the interactions between a propagating shock wave and evaporating water droplets

Numerical Investigation of Combustion Wave Propagation in Obstructed Channel of Pulse Detonation Engine using Kerosene and Butane Fuels

Investigation of Spray Characteristics for Detonability: A Study on Liquid Fuel Injector and Nozzle Design

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