Progress of continuously rotating detonation engines

Zhou, Rui; Wu, Dan; Wang, Jianping

doi:10.1016/j.cja.2015.12.006

Cited by 159 publications

(32 citation statements)

References 57 publications

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“…and thermal and frictional losses [31,44]. The result is quasi-continuous thrust that approximates a continuous thrust through high frequency rotations, suitable for both direct propulsion applications and in the combustor of a gas turbine [31,32,45]. Cross-section of a typical rotating detonation engine [38].…”

Section: Rotating Detonation Enginesmentioning

confidence: 99%

“…Despite this, it is used in most instances of numerical modelling as a guide as to whether the wave is performing as expected for the given parameters of the RDE [4,6,27,31,32,42,75,77]. Chapman and Jouguet's theory only applies to kinetic energy, disregarding the chemical energy of the reacting species, and hence, the Zel'Dovich-von Neumann-Doring (ZND) model is used as a more complete representation of the shock, taking into account the finite chemical reaction area directly upstream of the leading shock [3,21,45,75,[78][79][80].…”

Section: Shock Initiationmentioning

confidence: 99%

“…The attachment of turbines to RDEs has been proposed [8,9,31,32,45]. It has also been noted that there is a secondary shock propagating from the detonation, which exits the outlet of the chamber [32].…”

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confidence: 99%

See 2 more Smart Citations

A Theoretical Review of Rotating Detonation Engines

Shaw¹,

Kildare²,

Evans³

et al. 2021

Direct Numerical Simulations - An Introduction and Applications

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Rotating detonation engines are a novel device for generating thrust from combustion, in a highly efficient, yet mechanically simple form. This chapter presents a detailed literature review of rotating detonation engines. Particular focus is placed on the theoretical aspects and the fundamental operating principles of these engines. The review covers both experimental and computational studies, in order to identify gaps in current understanding. This will allow the identification of future work that is required to further develop rotating detonation engines.

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Section: Rotating Detonation Enginesmentioning

confidence: 99%

Section: Shock Initiationmentioning

confidence: 99%

See 1 more Smart Citation

A Theoretical Review of Rotating Detonation Engines

Shaw¹,

Kildare²,

Evans³

et al. 2021

Direct Numerical Simulations - An Introduction and Applications

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“…This so-called pressure gain combustion (PGC) can be accomplished by different means. The leading paths are pulse detonation (Roy et al, 2004;Pandey and Debnath, 2016), rotating detonation (Zhou et al, 2016;Kailasanath, 2017;Paxson and Naples, 2017), wave rotors (Akbari and Nalim, 2009;McClearn et al, 2016) and shockless explosion (Bobusch et al, 2014;Reichel et al, 2016) combustion. Some other concepts are the piston topping (Kaiser et al, 2015) and the nutating disk (Meitner et al, 2006).…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances

Almeida

Peitsch

2018

J. Glob. Power Propuls. Soc.

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A numerical aeroelastic assessment of a highly loaded high pressure compressor exposed to flow disturbances is presented in this paper. The disturbances originate from novel, inherently unsteady, pressure gain combustion processes, such as pulse detonation, shockless explosion, wave rotor or piston topping composite cycles. All these arrangements promise to reduce substantially the specific fuel consumption of present-day aeronautical engines and stationary gas turbines. However, their unsteady behavior must be further investigated to ensure the thermodynamic efficiency gain is not hindered by stage performance losses. Furthermore, blade excessive vibration (leading to high cycle fatigue) must be avoided, especially under the additional excitations frequencies from waves traveling upstream of the combustor. Two main numerical analyses are presented, contrasting undisturbed with disturbed operation of a typical industrial core compressor. The first part of the paper evaluates performance parameters for a representative blisk stage with high-accuracy 3D unsteady Reynolds-averaged Navier-Stokes computations. Isentropic efficiency as well as pressure and temperature unsteady damping are determined for a broad range of disturbances. The nonlinear harmonic balance method is used to determine the aerodynamic damping. The second part provides the aeroelastic harmonic forced response of the rotor blades, with aerodynamic damping and forcing obtained from the unsteady calculations in the first part. The influence of blade mode shapes, nodal diameters and forcing frequency matching is also examined.

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“…Как показали детальные численные расчеты детонационных процессов в камерах сгорания цилин-дрической формы [85][86][87][88][89][90][91], тяга RDE сравнительно слабо зависит от формы сопла. Наибольшая тяга дос-тигается, естественно, с соплом Лаваля.…”

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