Experimental Analogue of a Pre-Mixed Rotating Detonation Engine In Plane Flow

Andrus, Ionio Q.; King, Paul I.; Fotia, Matthew; Schauer, Frederick; Hoke, John

doi:10.2514/6.2015-1105

Cited by 11 publications

(3 citation statements)

References 11 publications

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“…Detonation is likely to propagate back into the feeding system through the injection holes if their diameter is not inferior to a critical tube diameter dependent on the initial pressure of the fresh mixture [7]. Some experimental attempts have been made by Andrus et al [8] to propagate two consecutive detonations in a premixed layer re¦lled as if it were in a RDE. The appearance of §ashbacks and blowo¨s con¦rms that it is not a safe operation to use a premix.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of an unsteady injection adapted to the continuous detonation wave rocket engine operation

Gaillard¹,

Davidenko²,

Dupoirieux³

2019

Progress in Propulsion Physics – Volume 11

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Detonation applied to propulsion could result in a promising increase of the thermodynamic efficiency of the engine cycle. Numerical simulations of the detonation propagating in the Continuous Detonation Wave Rocket Engine (CDWRE) are currently performed but still do not account for realistic injection process. The assumption of an ideal injected premix is generally chosen for convenience to obtain theoretical results. Comparison of the numerical results with experiments is difficult because of the clear difference of the injection configurations. Some physical aspects of the separate injection of the components used in experiments are not clearly assessed. This study is included in a wider numerical project aimed at designing and optimizing a realistic CDWRE. The optimization process is presently focused on the injector. One element of the injection hole pattern is considered assuming that this element is periodically repeated over the injector head. The aim of the work presented here is to model and analyze the refill process of the components in the combustion chamber behind the rotating detonation. The simulation starts just after the passage of the detonation over the considered injection element. This simulation gives information on the way the injected propellants recreate the reactive mixture for the next detonation. In the first step, two-dimensional (2D) computations helped us to set up the methodology and to study the dynamic response of the fresh components injected. A comparison between 2D homogeneous and separate injections is provided. In the second step, three-dimensional (3D) computations have been performed with a separate injection suitable for the CDWRE operation. Some performance parameters are evaluated such as mixing efficiency or filling of the domain.

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Section: Introductionmentioning

confidence: 99%

Numerical investigation of an unsteady injection adapted to the continuous detonation wave rocket engine operation

Gaillard¹,

Davidenko²,

Dupoirieux³

2019

Progress in Propulsion Physics – Volume 11

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“…This would result in a high loss of injection pressure but also technological problems due to a large number of tiny openings. Despite all these challenges, some experimental investigations were conducted by Andrus et al (2015) to explore the possibility of direct injection of premixed propellants in an RDC. These experiments first focused on a sonic flame to simulate the effect of detonation propagation through a series of injection nozzles.…”

Section: Figurementioning

confidence: 99%

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Naour¹,

Davidenko

Gaillard

et al. 2023

Front. Aerosp. Eng.

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Propulsion systems based on the constant-pressure combustion process have reached maturity in terms of performance, which is close to its theoretical limit. Technological breakthroughs are needed to develop more efficient transportation systems that meet today’s demands for reduced environmental impact and increased performance. The Rotating Detonation Engine (RDE), a specific implementation of the detonation process, appears today as a promising candidate due to its high thermal efficiency, wide operating Mach range, short combustion time and, thus, high compactness. Following the first proofs of concept presented in the 1960s, the last decade has seen a significant increase in laboratory demonstrators with different fuels, injection techniques, operating conditions, dimensions and geometric configurations. Recently, two flight tests of rocket-type RDEs have been reported in Japan and Poland, supervized by Professors Kasahara (Nagoya University) and Wolanski (Warsaw University), respectively. Engineering approaches are now required to design industrial systems whose missions impose efficiency and reliability constraints. The latter may render ineffective the simplified solutions and configurations developed under laboratory conditions. This requires understanding the fundamentals of detonation dynamics relevant to the RDE and the interrelated optimizations of the device components. This article summarizes some of the authors’ experimental and numerical work on fundamental and applied issues now considered to affect, individually or in combination, the efficiency and reliability of the RDE. These are the structure of the detonation reaction zone, the detonation dynamics for rotating regimes, the injection configurations, the chamber geometry, and the integration constraints.

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“…Andrus et al [40] designed a small test setup to simulate RDE behavior in which premixing was done for the feed flow. The key lessons taken from this study was the impact that pre-mixing the inlet flow has on flashback tendency, shock propagations and flow velocities.…”

Section: Objectivesmentioning

confidence: 99%

Experimental investigation for characterizing and improving inlet designs in rotating detonation engines

Sisler¹

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Rotating detonation engines (RDEs) present great potential for significant improvement in efficiency for land based power generation systems, in addition to aircraft propulsion devices. They offer the advantage of a net pressure gain across the combustor, as well as high exhaust temperatures and less entropy production due to detonative combustion. These improvements provide direct correlation to improved overall efficiency and thermal efficiency of gas turbine engines. RDEs surpass their conventional combustor counterparts in terms of their geometric size and simpler mechanical design. Among many areas of much needed research to further the technology readiness level (TRL) of RDEs, the inlet design is paramount to the successful operation of a rotating detonation engine. The inlet is one of the central impetuses behind current RDE research.

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Experimental Analogue of a Pre-Mixed Rotating Detonation Engine In Plane Flow

Cited by 11 publications

References 11 publications

Numerical investigation of an unsteady injection adapted to the continuous detonation wave rocket engine operation

Numerical investigation of an unsteady injection adapted to the continuous detonation wave rocket engine operation

Rotating detonation combustors for propulsion: Some fundamental, numerical and experimental aspects

Experimental investigation for characterizing and improving inlet designs in rotating detonation engines

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