Investigation of certain techniques for stabilizing detonationwaves in a supersonic flow

Zhuravskaya, T.A.; Левин, В. А.

doi:10.1134/s0015462812060129

Cited by 13 publications

(3 citation statements)

References 6 publications

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“…Разработка гиперзвуковых летательных аппаратов инициирует исследования детонационного горения, которое по некоторым оценкам, может быть более эффективным, чем медленное или турбулентное (см., например, [1][2]). В [3][4][5][6][7][8] показана возможность использования детонационного горения водородовоздушных смесей в сверхзвуковой прямоточной камере горения. Однако в авиации в качестве основного топлива традиционно используется керосин, который характеризуется низкой детонационной способностью.…”

Section: Introductionunclassified

Ignition of kerosene vapor in supersonic flow around a cylinder with an end windward wall

Tunik¹,

Gerasimov²

2018

PhChGD

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The detonation capacity of kerosene vapor is numerically studied in supersonic flow around a circular cylinder with an end windward wall. The model of kerosene combustion in the air takes into account 68 reactions for 44 components. Its testing is made by the way of comparison with the available calculated and experimental data on the ignition delay time under adiabatic conditions at a constant density. The mathematical model flow past cylinder is based on twodimensional non-stationary Euler equations for a multi-component reacting gas. The enthalpy and entropy of the initial mixture and combustion products are determined by polynomials from the NASA base. Calculations are performed on the basis of the Godunov finite-difference scheme and its modification of increased accuracy. The results allow justifying the parameters of the nozzle with a central body for a supersonic direct-flow chamber with detonative combustion of kerosene.

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Section: Introductionunclassified

Ignition of kerosene vapor in supersonic flow around a cylinder with an end windward wall

Tunik¹,

Gerasimov²

2018

PhChGD

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“…Wintenberger & Shepherd (2003), Wintenberger (2004), Vasil'ev, Zvegintsev & Nalivaichenko (2006) and Zhuravskaya & Levin (2012). Wintenberger (2004) carried out a detailed investigation of applications of detonative combustion to propulsion.…”

Section: Introductionmentioning

confidence: 99%

“…Detonations running with and against the flow were studied and the effect of the flow boundary layers in the channel on the detonation velocity was investigated. In Zhuravskaya & Levin (2012), stabilization by variation of the channel geometry was considered numerically using a model with multi-step kinetics for a hydrogen-air mixture. The authors concluded that variations of the channel cross-section can be used to stabilize the detonation wave in a channel.…”

Section: Introductionmentioning

confidence: 99%

Detonation in supersonic radial outflow

Kasimov

Korneev

2014

J. Fluid Mech.

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We report on the structure and dynamics of gaseous detonation stabilized in a supersonic flow emanating radially from a central source. The steady-state solutions are computed and their range of existence is investigated. Two-dimensional simulations are carried out in order to explore the stability of the steady-state solutions. It is found that both collapsing and expanding two-dimensional cellular detonations exist. The latter can be stabilized by putting several rigid obstacles in the flow downstream of the steady-state sonic locus. The problem of initiation of standing detonation stabilized in the radial flow is also investigated numerically.

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Stabilization of Detonation Combustion of a Supersonic Flow due to Using the Special Form Plane Channel

Левин

Zhuravskaya

2017

30th International Symposium on Shock Waves 1

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Investigation of certain techniques for stabilizing detonationwaves in a supersonic flow

Cited by 13 publications

References 6 publications

Ignition of kerosene vapor in supersonic flow around a cylinder with an end windward wall

Ignition of kerosene vapor in supersonic flow around a cylinder with an end windward wall

Detonation in supersonic radial outflow

Stabilization of Detonation Combustion of a Supersonic Flow due to Using the Special Form Plane Channel

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