Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures
TL;DR: 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.
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TL;DR: In this paper, an assessment of the challenges of understanding basic physics through utilizing rotating detonations in aerospace platforms is provided, ranging from understanding the basic physics of the system to its feasibility.
Abstract: Rotating detonation engines (RDEs), also known as continuous detonation engines, have gained much worldwide interest lately. Such engines have huge potential benefits arising from their simplicity of design and manufacture, lack of moving parts, high thermodynamic efficiency and high rate of energy conversion that may be even more superior than pulse detonation engines, themselves the subject of great interest. However, due to the novelty of the concept, substantial work remains to demonstrate feasibility and bring the RDE to reality. An assessment of the challenges, ranging from understanding basic physics through utilizing rotating detonations in aerospace platforms, is provided.
451 citations
TL;DR: In this article, the detonations propagating through the annular channel of an optically accessible rotating detonation engine (RDE) operating on hydrogen-air are visualized using OH* chemiluminescence imaging.
274 citations
TL;DR: An overview of the research done worldwide to address some of the challenges and questions pertaining to the physics of rotating detonation combustors operation is provided in this paper, where notable parallels are drawn to the phenomena of low and high frequency instabilities in solid and liquid rockets that have been recognized as the most severe hindrance to their operation.
204 citations
TL;DR: In this article, a large-scale continuous detonation combustor (CDC) has been designed, fabricated and tested to study the effect of different design elements on the operation process and CDC propulsion performance.
198 citations
Cites background from "Experimental research on the rotati..."
...[8,9], French [10,11], Japanese [12,13], Polish [12,14], and Russian [3,15,16] scientists have appeared to mention just a few....
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...During the last decade, interest in the CDC concept increased significantly: the works of American [5e7], Chinese [8,9], French [10,11], Japanese [12,13], Polish [12,14], and Russian [3,15,16] scientists have appeared to mention just a few....
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TL;DR: In this article, a new model of the rotating detonation engine (RDE) combustor, which is called the hollow combustor has no inner wall and is hollow, was presented to solve the problem of engine heating that arises in RDEs with the coaxial annular combustor.
166 citations
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01 Jan 1996
1,984 citations
01 Jun 1996
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.
Abstract: This users manual is the second part of a two-part report describing the NASA Lewis CEA (Chemical Equilibrium with Applications) program. The program obtains chemical equilibrium compositions of complex mixtures with applications to several types of problems. The topics presented in this manual are: (1) details for preparing input data sets; (2) a description of output tables for various types of problems; (3) the overall modular organization of the program with information on how to make modifications; (4) a description of the function of each subroutine; (5) error messages and their significance; and (6) a number of examples that illustrate various types of problems handled by CEA and that cover many of the options available in both input and output. Seven appendixes give information on the thermodynamic and thermal transport data used in CEA; some information on common variables used in or generated by the equilibrium module; and output tables for 14 example problems. The CEA program was written in ANSI standard FORTRAN 77. CEA should work on any system with sufficient storage. There are about 6300 lines in the source code, which uses about 225 kilobytes of memory. The compiled program takes about 975 kilobytes.
621 citations
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.
Abstract: Applications of detonations to propulsion are reviewed. First, the advantages of the detonation cycle over the constant pressure combustion cycle, typical of conventional propulsion engines, are discussed. Then the early studies of standing normal detonations, intermittent (or pulsed) detonations, rotating detonations, and oblique shock-induced detonations are reviewed. This is followed by a brief discussion of detonation thrusters, lasersupported detonations and oblique detonation wave engines. Finally, a more detailed review of research during the past decade on ram accelerators and pulsed detonation engines is presented. The impact of the early work on these recent developments and some of the outstanding issues are also discussed.
600 citations
"Experimental research on the rotati..." refers background in this paper
...The first one is called the Standing Detonation Engine [9], where injection of the mixture is continuous, which ensures a constant thrust value....
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...The second group of detonation engines is called the Pulsed Detonation Engine (PDE) and its design is very simple [9,10]....
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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.
Abstract: A rotating detonation propagating at nearly Chapman–Jouguet velocity is numerically stabilized on a two-dimensional simple chemistry flow model. Under purely axial injection of a combustible mixture from the head end of a toroidal section of coaxial cylinders, the rotating detonation is proven to give no average angular momentum at any cross section, giving an axial flow. The detonation wavelet connected with an oblique shock wave ensuing to the downstream has a feature of unconfined detonation, causing a deficit in its propagation velocity. Due to Kelvin–Helmholtz instability existing on the interface of an injected combustible, unburnt gas pockets are formed to enter the junction between the detonation and oblique shock waves, generating strong explosions propagating to both directions. Calculated specific impulse is as high as 4,700 s.
265 citations
"Experimental research on the rotati..." refers background in this paper
...[13], the pressure peaks of various amplitudes were also reported....
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