Low-frequency self-oscillatory processes in propellant combustion

Svetlichnyi, I. B.; Margolin, A. D.; Pokhil, P. F.

doi:10.1007/bf00748964

Cited by 11 publications

(5 citation statements)

References 2 publications

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“…The first resonant frequency, 0lJ varies with mean pressure, Pre/" The variation is found to obey the relation Downloaded by [Umeå University Library] at 10:49 06 April 2015 decrease in the index with mean pressure was observed by T'ien (1972) also. In experiments on Double Base propellant burning in a constant-pressure bomb (Svetlichnyi and Margolin, 1971), the relationship W n ex p;;; has been observed over the range of pressures where both the primary and secondary flames merge. A small decrease in the index can be attributed to relaxation of the quasi-steady gas-phase assumption, because for classical QSHOD models, W n ex p;;; at all mean pressures.…”

Section: Comparison With Transient Gas-phase Resultsmentioning

confidence: 95%

Nonlinear Intrinsic Instability of Solid Propellant Combustion Including Gas-Phase Thermal Inertia

Kumar

Lakshmisha

2000

Combustion Science and Technology

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The problem of homogeneous solid propellant combustion instability is studied with a one-dimensional flame model, including the effects of gas-phase thermal inertia and nonlinearity. Computational results presented in this paper show nonlinear instabilities inherent in the equations, due to which periodic burning is found even under steady ambient conditions such as pressure. The stability boundary is obtained in terms of Denison-Baum parameters. It is found that inclusion of gas-phase thermal inertia stabilizes the combustion. Also, the effect of a distributed heat release in the gas phase. compared to the flame sheet model. is to destabilize the burning.Direct calculations for finite amplitude pressure disturbances show that two distinct resonant modes exist. the first one near the natural frequency as obtained from intrinsic instability analysis and a second mode occurring at a much higher driving frequency. It is found that even in the low frequency region, the response of the propellant is significantly affected by the specific type of gas-phase chemical heat-release model employed. Examination of frequency response function reveals that the role of gas-phase thermal inertia is to stabilize the burning near the first resonant mode. Calculations made for different amplitudes of driving pressure show that the mean burning rate decreases with increasing amplitude. Also, with an increase in the driving amplitude, higher harmonics are generated in the burning rate.

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Section: Comparison With Transient Gas-phase Resultsmentioning

confidence: 95%

Nonlinear Intrinsic Instability of Solid Propellant Combustion Including Gas-Phase Thermal Inertia

Kumar

Lakshmisha

2000

Combustion Science and Technology

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“…In particular, results [83] are explained by radiation absorption at a finite depth beneath the SP surface and by the presence of the corresponding relaxation time different from the relaxation time of the preheated layer. For experiments [84], convincing arguments were put forward [85] which attribute the effect to the action of hot-spot pulsating combustion, and experiments [80] did not show the existence of the second maximum.…”

Section: Models That Do Not Use the Phenomenological Approachmentioning

confidence: 97%

“…In experiments [84], two frequencies different from the natural acoustic frequencies of the combustion chamber were observed simultaneously in a certain range of SP combustion parameters. However, one cannot say with confidence that results [77][78][79][80][81] are supported by experiments [83,84]: similar forms of the theoretical and experimental dependences could be due to different physicochemical mechanisms. In particular, results [83] are explained by radiation absorption at a finite depth beneath the SP surface and by the presence of the corresponding relaxation time different from the relaxation time of the preheated layer.…”

Section: Models That Do Not Use the Phenomenological Approachmentioning

confidence: 99%

“…Two maxima in the curve of the real part the response function versus frequency were obtained in experiments [83]. In experiments [84], two frequencies different from the natural acoustic frequencies of the combustion chamber were observed simultaneously in a certain range of SP combustion parameters. However, one cannot say with confidence that results [77][78][79][80][81] are supported by experiments [83,84]: similar forms of the theoretical and experimental dependences could be due to different physicochemical mechanisms.…”

Section: Models That Do Not Use the Phenomenological Approachmentioning

confidence: 99%

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Analysis of unsteady solid-propellant combustion models (review)

Gusachenko

Зарко

2008

Combust Explos Shock Waves

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Recent studies of solid-propellant combustion models are briefly analyzed. The models are divided into purely one-dimensional (classical and phenomenological models with various generalizations of the Zel'dovich approach) and non-one-dimensional. The latter include models with local non-one-dimensionality, which is always accompanied by local unsteadiness. This all can be eliminated by averaging. The main disadvantage of unsteady solid-propellant combustion models, which is no fault of their authors, is the same as in the case of steady-state models: the lack of detailed information on chemical and physical processes in the condensed phase. Impropriety of extending the purely one-dimensional approach to the instability region is noted. Possible directions for further development of unsteady (and quasi-steady-state) solid-propellant combustion models for homogeneous compositions may involve accounting for local non-one-dimensionality and the unsteadiness due to instability of the subsurface reactions zone and verification of the possibility of the existence of chemical instability capable of causing similar non-one-dimensionality and unsteadiness.

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“…[81][82][83][84][85][86][87], oscillatory burning (Refs. [88][89][90][91][92][93][94][95][96][97][98][99][100][101][102][103][104][105][106][107], deflagration and low pressure extinction of ammonium oerchlorate (Refs. [108][109][110][111][112][113][114][115][116][117][118][119][120][121][122], low pressure extinction of composite propellants (Refs.…”

Section: -Background or The Research Studymentioning

confidence: 99%