Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures
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In this paper, an experimental study on rotating detonation in a rocket engine is presented, where a model of a simple engine was designed, built, and tested, and the model of the engine was connected to the dump tank.Abstract:
An experimental study on rotating detonation is presented in this paper. The study was focused on the possibility of using rotating detonation in a rocket engine. The research was divided into two parts: the first part was devoted to obtaining the initiation of rotating detonation in fuel–oxygen mixture; the second was aimed at determination of the range of propagation stability as a function of chamber pressure, composition, and geometry. Additionally, thrust and specific impulse were determined in the latter stage. In the paper, only rich mixture is described, because using such a composition in rocket combustion chambers maximizes the specific impulse and thrust. In the experiments, two kinds of geometry were examined: cylindrical and cylindrical-conic, the latter can be simulated by a simple aerospike nozzle. Methane, ethane, and propane were used as fuel. The pressure–time courses in the manifolds and in the chamber are presented. The thrust–time profile and detonation velocity calculated from measured pressure peaks are shown. To confirm the performance of a rocket engine with rotating detonation as a high energy gas generator, a model of a simple engine was designed, built, and tested. In the tests, the model of the engine was connected to the dump tank. This solution enables different environmental conditions from a range of flight from 16 km altitude to sea level to be simulated. The obtained specific impulse for pressure in the chamber of max. 1.2 bar and a small nozzle expansion ratio of about 3.5 was close to 1,500 m/s.read more
Citations
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Rotating detonation in a ramjet engine three-dimensional modeling
TL;DR: In this paper, a rotating detonation engine (RDE) combustion chamber fed by hydrogen-air mixtures of different composition was modeled numerically using 3D geometry, and the timeconsuming parts of the numerical code were parallelized using the OpenMP technique.
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Numerical Investigation of Rotating Detonation Engine Propulsive Performance
TL;DR: In this article, a series of 3-and 2-dimensional numerical simulations of a rotating detonation engine (RDE) were carried out with a 1-step chemical reaction model to investigate the RDE's propulsive performance.
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Numerical investigation of shock wave reflections near the head ends of rotating detonation engines
R. Zhou,Jian-Ping Wang +1 more
TL;DR: The influence of various chamber geometries on shock wave reflections near the head end of rotating detonation engines was investigated in this article, where a hydrogen/air one-step chemical reaction model was used.
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Numerical estimation of the thrust performance on a rotating detonation engine for a hydrogen–oxygen mixture
TL;DR: In this article, numerical simulations of 2D and 3D rotating detonation engines for a hydrogen-oxygen mixture were performed using a detailed chemistry model, and the results indicated that the overall flow structures are in agreement for the two simulations and that both rotating velocities are approximately 96% of the CJ value.
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Experimental Realization of H2/Air Continuous Rotating Detonation in a Cylindrical Combustor
TL;DR: In this article, the results of experimental studies on a H2/air continuous rotating detonation engine (CRDE) in an annular combustor are presented, and the detonation propagation modes of all the tests can be divided into four kinds: two-wave, hybrid two/one wave, one-wave and transient one wave.
References
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Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications II. Users Manual and Program Description. 2; Users Manual and Program Description
Bonnie J. McBride,Sanford Gordon +1 more
Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications II. Users Manual and Program Description
Bonnie J. McBride,Sanford Gordon +1 more
TL;DR: The NASA Lewis CEA (Chemical Equilibrium with Applications) program as mentioned in this paper is a two-part report describing the second part of a twopart report described the NASA Lewis-CEA program.
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Review of Propulsion Applications of Detonation Waves
TL;DR: In this article, the advantages of the detonation cycle over the constant pressure combustion cycle, typical of conventional propulsion engines, are discussed, and the impact of the early work on these recent developments and some of the outstanding issues are also discussed.
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Fundamentals of rotating detonations
TL;DR: In this article, a rotating detonation propagating at nearly Chapman-Jouguet velocity is numerically stabilized on a two-dimensional simple chemistry flow model, giving an axial flow.