Assessment of the modified rotation/curvature correction SST turbulence model for simulating swirling reacting unsteady flows in a solid-fuel ramjet engine

Musa, Omer; Chen, Xiong; Zhou, Changsheng; Gong, Lunkun

doi:10.1016/j.actaastro.2016.09.016

Cited by 22 publications

(4 citation statements)

References 39 publications

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“…While in reattachment point, the temperature is proportional to In Equation ( 18), λ fluid is the thermal conductivity of the fluid domain, ∂T/∂n represents the temperature gradient, and T w and T aw stand for the temperature of the fuel surface and recovery temperature, respectively. T aw can be calculated by Equation (19) and T ∞ and P rl represent the temperature of the inlet and Prandtl numbers, respectively. γ fluid is specific heat ratio of propellant and Ma ∞ represents the Mach number at inlet.…”

Section: Effects Of Sudden Expansion Ratio On Regression Ratementioning

confidence: 99%

Numerical Investigation of the Effect of Sudden Expansion Ratio of Solid Fuel Ramjet Combustor with Swirling Turbulent Reacting Flow

Chen

Cai

et al. 2019

Energies

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In this paper, the effect of sudden expansion ratio of solid fuel ramjet (SFRJ) combustor is numerically investigated with swirl flow. A computational fluid dynamics (CFD) code is written in FORTRAN to simulate the combustion and flow patterns in the combustion chamber. The connected-pipe facility is used to perform the experiment with swirl, and high-density Polyethylene (HDPE) is used as the solid fuel. The investigation is performed with different sudden expansion ratios, in which the port and inlet diameters are independently varied. The results indicated that the self-sustained combustion of the SFRJ occurs around the reattachment point at first, and then the heat released in reattachment point is used to achieve the self-sustained combustion in the redevelopment zone. The average regression rate is proportional to the sudden expansion ratio for the cases with a fixed port diameter, which is mainly dominated by the enhancement of heat transfer in backward-facing step. However, the average regression rate is inversely proportional to the sudden expansion ratio for the cases with fixed inlet diameter, which is influenced by the heat transfer mechanism of developed turbulent flow in the redevelopment zone.

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Section: Effects Of Sudden Expansion Ratio On Regression Ratementioning

confidence: 99%

Numerical Investigation of the Effect of Sudden Expansion Ratio of Solid Fuel Ramjet Combustor with Swirling Turbulent Reacting Flow

Chen

Cai

et al. 2019

Energies

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“…In addition, the base code has been also validated using swirl benchmark cases in the previous work [17]. Furthermore, the extended code with combustion model needs to be validated on combustion cases, to do so; additional two cases have been studied as well in [18][19][20].…”

Section: Governing Equations Of Solid Domainmentioning

confidence: 99%

Numerical study on a new design of solid-fuel ramjet combustor with swirl flow

Musa

Chen

Huang

2019

FJES

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A new design of solid-fuel ramjet is proposed and examined numerically in this paper. Multi-physics coupling code is developed using FORTRAN and parallel computing to solve the problems of multi-physics coupling of fluid mechanics, solid pyrolysis, heat transfer, thermodynamics, and chemical kinetics. Simulations are carried out for the proposed design then the results are compared with the classic design of the solid-fuel ramjet. It is found that the proposed design has improved the regression rate significantly; besides, the amount of released solid fuel is increased for the same size. A new flame has been observed inside the combustion chamber of the proposed design then the two flamed were emerged in the afterburning chamber.

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“…Besides the addition of the burning rate, the pressure in the combustion chamber has a slight decrease due to the high-speed rotation [5,6]. Musa [7,8] carried on an experiment on the solid-fuel ramjet to study the turbulent swirling flow field with combustion, and a numerical model with an SST-CCM turbulence model was developed. The relationship between rotation speed, inflow mass flow rate, inflow temperature, and propellant average burning rate was obtained.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of the Reacting Flow for the Base‐Bleed Projectile under Dual Stress

Zhou

et al. 2021

Propellants Explo Pyrotec

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While the base‐bleed projectile (BBP) is ejected from the muzzle, high‐speed rotation and rapid depressurization in the combustion chamber bring much initial disturbance to the BBP. In order to research the effect of propellant gas on the drag reduction performance for the BBP, a chemical non‐equilibrium flow model is established under the dual environmental stress of high‐speed rotation and rapid depressurization. This numerical model is coupled with a H2‐CO reaction mechanism and propellant burning rate model. Detailed numerical results of flow patterns, heat energy addition, and mass addition for various rotation speeds are discussed. The results show that the supersonic under‐expanded jet gradually transforms into a subsonic jet, and a low‐pressure recirculation zone appears at the wake of BBP. Moreover, the tangential velocity in the combustion chamber presents a typical distribution of the Rankie combined vortex. The high‐pressure jet rapidly expands to the outside low‐pressure environment, and the pressure in the combustion chamber (pc) drops sharply. After 1.15 ms, the outside gas flows back into the combustion chamber, and the rotation increases the fluctuation intensity of the inter flow field. pc reaches 0.718 p0 and remains stable after 4.0 ms. The rotation of BBP increases the pressure and Mach number near the nozzle at 5.0 ms.

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Assessment of the modified rotation/curvature correction SST turbulence model for simulating swirling reacting unsteady flows in a solid-fuel ramjet engine

Cited by 22 publications

References 39 publications

Numerical Investigation of the Effect of Sudden Expansion Ratio of Solid Fuel Ramjet Combustor with Swirling Turbulent Reacting Flow

Numerical Investigation of the Effect of Sudden Expansion Ratio of Solid Fuel Ramjet Combustor with Swirling Turbulent Reacting Flow

Numerical study on a new design of solid-fuel ramjet combustor with swirl flow

Characteristics of the Reacting Flow for the Base‐Bleed Projectile under Dual Stress

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