Optimization of the Thrust Performance of a Pulsed Detonation Engine

Левин, В. А.; Мануйлович, И. С.; Марков, В. В.

doi:10.1007/s10573-010-0056-y

Cited by 5 publications

(2 citation statements)

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“…Levin and Manulovich 8 performed a nozzle-shape optimization of conical and parabolic nozzle shapes using analytical expressions based on infinitely thin detonation waves. Billings 9 parameterized a twodimensional (2D) nozzle using cubic functions and performed the optimization using a genetic algorithm and inviscid evaluations, concluding that supersonic diverging nozzles are the best to maximize the thrust.…”

Section: Introductionmentioning

confidence: 99%

Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor

Ornano

Braun

Saracoglu

et al. 2017

Advances in Mechanical Engineering

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Thermal engines based on pressure gain combustion offer new opportunities to generate thrust with enhanced efficiency and relatively simple machinery. The sudden expansion of detonation products from a single-opening tube yields thrust, although this is suboptimal. In this article, we present the complete design optimization strategy for nozzles exposed to detonation pulses, combining unsteady Reynolds-averaged Navier-Stokes solvers with the accurate modeling of the combustion process. The parameterized shape of the nozzle is optimized using a differential evolution algorithm to maximize the force at the nozzle exhaust. The design of experiments begins with a first optimization considering steady-flow conditions, subsequently followed by a refined optimization for transient supersonic flow pulse. Finally, the optimized nozzle performance is assessed in three dimensions with unsteady Reynolds-averaged Navier-Stokes capturing the deflagration-to-detonation transition of a stoichiometric, premixed hydrogen-air mixture. The optimized nozzle can deliver 80% more thrust than a standard detonation tube and about 2% more than the optimized results assuming steady-flow operation. This study proposes a new multi-fidelity approach to optimize the design of nozzles exposed to transient operation, instead of the traditional methods proposed for steady-flow operation.

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Section: Introductionmentioning

confidence: 99%

Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor

Ornano

Braun

Saracoglu

et al. 2017

Advances in Mechanical Engineering

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“…The use of high-performance computers made it possible to study multi-dimensional flows related to the detonation due to the energy of the combustible mixture motion and its interaction with moving boundaries (see [36][37][38][39][40][41][42][43][44][45][46]). New regimes of the propagation of chemical reaction waves, including the galloping layered detonation, were discovered.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of spinning detonation in circular section channels

Левин

Manuylovich

Марков

2016

Comput. Math. and Math. Phys.

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Numerical simulation of three-dimensional structures of gas detonation in circular section channels that emerge due to the instability when the one-dimensional flow is initiated by energy supply at the closed end of the channel is performed. It is found that in channels with a large diameter, an irregular three-dimensional cellular detonation structure is formed. Furthermore, it is found that in channels with a small diameter circular section, the initially plane detonation wave is spontaneously transformed into a spinning detonation wave, while passing through four phases. A critical value of the channel diameter that divides the regimes with the three-dimensional cellular detonation and spinning detonation is determined. The stability of the spinning detonation wave under perturbations occurring when the wave passes into a channel with a greater (a smaller) diameter is investigated. It is found that the spin is preserved if the diameter of the next channel (into which the wave passes) is smaller (respectively, greater) than a certain critical value. The computations were performed on the Lomonosov supercomputer using from 0.1 to 10 billions of computational cells. All the computations of the cellular and spinning detonation were performed in the whole long three-dimensional channel (up to 1 m long) rather than only in its part containing the detonation wave; this made it possible to adequately simulate and investigate the features of the transformation of the detonation structure in the process of its propagation. INTRODUCTIONThe study of detonation waves in gases is mainly stimulated by the desire to use them for practical purposes in impulse facilities and special energy systems designed for rockets and other flying vehicles. Large magnitudes of the gas dynamics parameters and the complex flow pattern behind the detonation wave front significantly complicate both the experimental and theoretical study of detonation. The main source of information about detonation waves is the experimental study. Among the experimenters, a special place is held by Soloukhin (see [1][2][3][4][5][6]). His works became handbooks for generations of researchers. A significant contribution to the study of detonation was made by his colleagues, disciples, and students. As experimental data were accumulated, theoretical detonation models were improved as well. For example, the two-stage model, which takes into account the ignition delay and a finite time of the subsequent heat emission, makes it possible to describe the nonstationary nonlinear wave structure of detonation (see [7]). In the framework of the infinitely thin detonation wave, the asymptotic nature of the transition of the plane wave to the Chapman-Jouguet regime was established; in the framework of the cylindrical and spherical model, it was found that this transition occurs at a finite distance from the point of the detonation wave formation (see [8,9]). Within the two-stage model, the initial phase of the flow initiated by a point explosion was analytically investigated...

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Control of detonation combustion of rarefied hydrogen-air mixture in a laval nozzle

Tunik

2018

International Journal of Hydrogen Energy

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Optimization of the Thrust Performance of a Pulsed Detonation Engine

Cited by 5 publications

References 3 publications

Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor

Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor

Numerical simulation of spinning detonation in circular section channels

Control of detonation combustion of rarefied hydrogen-air mixture in a laval nozzle

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