The influence of a compressible boundary on the propagation of gaseous detonations

Dabora, Eliahou K.; Nicholls, J. A.; Morrison, Rebecca

doi:10.1016/s0082-0784(65)80225-9

Cited by 65 publications

(33 citation statements)

References 11 publications

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“…For the limiting case when ␣ = 0°, the solution is identical to the case studied by Dabora. 7 The detonation products in the node fixed frame travel at the speed of sound of the burned products causing the angle of the expansion fan head to coincide with the detonation wave. In the limit of ␣ = 90°, the interface becomes parallel to the detonation wave.…”

Section: Governing Equations and Matching Conditionsmentioning

confidence: 99%

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Detonation interaction with an interface

Lieberman

Shepherd

2007

Physics of Fluids

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Detonation interaction with an interface was investigated, where the interface separated a combustible from an oxidizing or inert mixture. The ethylene-oxygen combustible mixture had a fuel-rich composition to promote secondary combustion with the oxidizer in the turbulent mixing zone ͑TMZ͒ that resulted from the interaction. Sharp interfaces were created by using a nitro-cellulose membrane to separate the two mixtures. The membrane was mounted on a wood frame and inserted in the experimental test section at a 45°angle to the bulk flow direction. The membrane was destroyed by the detonation wave. The interaction resulted in a transmitted and reflected wave at a node point similar to regular shock refraction. A detonation refraction analysis was carried out to compare with the measured shock angles. It was observed that the measured angle is consistently lower than the predicted value. An uncertainty analysis revealed possible explanations for this systematic variation pointing to factors such as the incident wave curvature and the role of the nitro-cellulose diaphragm. Analysis of the TMZ and Mach stem formed from the reflection of the transmitted shock wave off the solid boundary were carried out and found to justify the size and strength of these features as a function of the test gas composition. The role of secondary combustion in the TMZ was also investigated and found to have a small influence on the wave structure.

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Section: Governing Equations and Matching Conditionsmentioning

confidence: 99%

“…One more relevant work 7 has modeled the deflection of a contact surface arising from a detonation propagating through a channel with a compressible, nonreacting boundary for the limiting case of the detonation velocity being normal to the interface.…”

Section: Introductionmentioning

confidence: 99%

Detonation interaction with an interface

Lieberman

Shepherd

2007

Physics of Fluids

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“…There has been some previous work on layered detonations in gaseous systems; however, high-speed detonations have not been reported. Dabora 10 et al found that surrounding a gaseous detonation with a layer of inert gas in fact causes a velocity decrement that depends on the density ratio of the reactive gas to the inert, and the width of the reactive layer. When hydrogen or helium was used in the inert layer, the reaction zone was observed to propagate at 50% of the CJ velocity.…”

Section: Non-uniform Mixturesmentioning

confidence: 99%

Cryogenic, Multiphase, Hydrogen-Oxygen Detonations

Coy¹,

Watts²,

Palaniswamy³

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information , 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) NUMBER(S)Edwards AFB CA 93524-7048 AFRL-PR-ED-JA-2005-027 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited. SUPPLEMENTARY NOTESPresented at ABSTRACTDetonations of flowing mixtures of hydrogen and oxygen at temperatures between 90 and 110 K, pressures from 3 to 5 bar, and mixture densities of 3-6 kg/m3 have been studied. The effect of liquid oxygen on wave speeds and peak wall pressures are reported. Data taken at cryogenic conditions are compared with ambient temperature data taken at similar initial densities and equivalence ratios, as well as with equilibrium, Chapman-Jouget theory calculations. For the conditions studied, liquid oxygen was found to result in increased wave speeds and peak wall pressures. These observations are shown to be consistent with a highly stratified mixture with high concentrations of oxygen in a layer adjacent to the wall and low concentrations along the axis of the tube. Detonations of flowing mixtures of hydrogen and oxygen at temperatures between 90 and 110 K, pressures from 3 to 5 bar, and mixture densities of 3-6 kg/m 3 have been studied. The effect of liquid oxygen on wave speeds and peak wall pressures are reported. Data taken at cryogenic conditions are compared with ambient temperature data taken at similar initial densities and equivalence ratios, as well as with equilibrium, Chapman-Jouget theory calculations. For the conditions studied, liquid oxygen was found to result in increased wave speeds and peak wall pressures. These observations are shown to be consistent with a highly stratified mixture with high concentrations of oxygen in a layer adjacent to the wall and low concentrations along the axis of the tube. I. IntroductionHIS paper presents results from an investigation of detonations of flowing mixtures of cryogenic gaseous hydrogen and liquid oxygen. This work was undertaken to support development of pulse detonation rocket engines (PDRE). Cryogenic propellants will be desirable for PDRE applications for many of the same reasons that they are used for conventional rocket engines: the density is increased, which reduces tank volume, and...

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“…The procedure and equipmert used are essentially those developed by Dabora (2 ) with two exceptions-the addition of a humidifier to the balloonfilling circuit, and the use of a dewpoint measurement system at the entrance of the test. section.…”

Section: Il Experimental Proceduresmentioning

confidence: 99%