Combustion following turbulent mixing in muzzle flows

Klingenberg, G.; Heimerl, Joseph M.

doi:10.1016/0010-2180(87)90055-1

Cited by 9 publications

(10 citation statements)

References 5 publications

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“…12(b) is magnified. The combustion region is the core of intermediate flame, as mentioned by Klingenberg [19]. The magnified area is shown in Fig.…”

Section: Combustion In Muzzle Flowmentioning

confidence: 98%

“…Previous studies analyzed the influence of the precursor flow based on comparing data acquired from cases with and without a precursor flow field [14], or directly simulating the muzzle flow coupled with the precursor flow [12,13]. But, to date, there is no published research describing the detailed process of the precursor flow interacting with the propellant gas flow, especially the oxygen contribution of the precursor gas to the intermediate flash which directly affects the ignition of secondary combustion [19]. From Fig.…”

Section: Introductionmentioning

confidence: 98%

“…Conclusions were drawn that oxygen from the entrained air is transported to the core of the flow in the vicinity of the Mach disk, i.e., the so-called ''intermediate" flash, or ''intermediate" flow region and combustion reactions take place there. A more vital conclusion was drawn that the ignition sequence leading to secondary muzzle flash is governed by an ignition temperature whose value is determined by two energy sources: the well-known shock heating and the combustion reactions in the intermediate flash [19]. Zhuo simulated the muzzle flows with base bleed projectile based on dynamic overlapping grids.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical investigation on combustion in muzzle flows using an inert gas labeling method

Qin

Zhang

2016

International Journal of Heat and Mass Transfer

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“…12(b) is magnified. The combustion region is the core of intermediate flame, as mentioned by Klingenberg [19]. The magnified area is shown in Fig.…”

Section: Combustion In Muzzle Flowmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical investigation on combustion in muzzle flows using an inert gas labeling method

Qin

Zhang

2016

International Journal of Heat and Mass Transfer

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“…Combustion in a traditional axisymmetric supersonic jet in muzzle flow has been deeply investigated by Klingenberg et al. . Klingenberg and Mach treated the muzzle flash as three regions separated in space and time, i. e., the primary flash, the intermediate flash and the secondary flash.…”

Section: Introductionmentioning

confidence: 99%

“…The combustion of solid propellants and the gas dynamic processes occurring within the flow inside and at the exit plane of the muzzle was investigated by Klingenberg and Mach . The development of the intermediate flash region was examined by Klingenberg and Heimerl and a phenomenon was observed in which oxygen was entrained into the core of the intermediate flow region and reactions took place there. These combustion reactions controlled the ignition sequence leading to the secondary flash.…”

Section: Introductionmentioning

confidence: 99%

Study on the Initiation Mechanism of Non‐Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet

Qin

Zhang

2019

Propellants Explo Pyrotec

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The reflection of a supersonic propellant gas jet always happens during the firing of the weapon system of aircraft. The reflection induces complex non‐premixed shock induced combustion. It is of great importance to investigate the initiation mechanism of the combustion in the supersonic jet of propellant gas. The mechanism is vital for the design of any suppression method of the secondary combustion. To investigate the combustion in the reflected supersonic jet, a solid propellant combustion model and a numerical model based on compressible multispecies Navier‐Stokes equations are established. A detailed reaction mechanism consisting of 9 species and 12 reactions is utilized for the combustion of the propellant gas. Based on the models, the supersonic precursor flow field and the supersonic propellant gas jet flow are obtained and discussed. A secondary jet is observed which has not been reported before. A sandwich structure is proposed to reveal the initiation of the combustion. The oxygen supply in the secondary jet is found to be dominated by a vortex. An inert gas atmosphere can be adopted to suppress the mass transfer at the contact surface. Special devices could be designed to suppress the formation of the vortex in the secondary propellant jet.

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Investigation of thermal performance in dual‐fuel units

Xue

2022

Energy Science & Engineering

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Numerical studies were carried out to investigate the thermal performance of the muzzle flow with strong shock discontinuities and gas-gas heat transfer mechanism in the base bleed unit (BBU) of an aerodynamic vehicle under the combined effects of muzzle flow and depressurization process. The process was modeled using the Navier-Stokes equations with chemical kinetics and interior ballistic equations. The results show that the muzzle phenomena with large temperature gradients and different wave structures appear after the supersonic vehicle enters into the free-flight stage. The BBU also experiences a strong depressurization process with the release of high-temperature propellant gas at 2200 K. However, the igniter combustion gas at a higher temperature of 3050 K in the BBU develops downstream and upstream repeatedly under the combined effects of the base wave and depressurization process, which makes the energy conversion process in the unit more complicated. With the projectile leaving the control of the muzzle flow, the BBU is full of the igniter combustion gas and the energy in the unit is uniformly distributed gradually. The high-temperature area, at approximately 2750 K, propagates downstream along the axial and radial directions simultaneously until it finally dominates the entire unit. The maximum temperature of the combustion gas acting on the propellant surface is always 2740 K and the maximum heat flux remains approximately 1250 W/cm 2 at later periods.

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Combustion following turbulent mixing in muzzle flows

Cited by 9 publications

References 5 publications

Numerical investigation on combustion in muzzle flows using an inert gas labeling method

Numerical investigation on combustion in muzzle flows using an inert gas labeling method

Study on the Initiation Mechanism of Non‐Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet

Investigation of thermal performance in dual‐fuel units

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