Numerical analysis of reactive turbulent flow in the thrust chamber of RD-108 engine rocket

Taghavi, Seyed Reza; Dehnavi, Mohammad Ali; Ghafouri, Ali

doi:10.1016/j.dt.2018.12.004

Cited by 5 publications

(3 citation statements)

References 21 publications

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“…Numerical simulation is a commonly used tool for studying the internal processes in the chambers of rocket engines [1,2,3,4]. It involves solving a set of equations that describe gas dynamics in regions with curvilinear boundaries, using the finite volume method [5] on a meshes of different type.…”

Section: Introductionmentioning

confidence: 99%

The Application of the Extended Cells Method to Simulate the Flow of Combustion Gases in the Lpre Chamber

Дубровський,

Бучарський

2023

Rocket-Sp. Tech.

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Abstract. The numerical modeling of the process of two-dimensional axisymmetric flow of combustion gases in the chamber of a liquid rocket engine is considered in this study. In general, when solving such problems, meshes are used which lines coincide with the boundaries of the computational domain. However, an alternative solution is proposed here, which is to apply the extended cells method. It allows using rectangular Cartesian grids, which lines do not coincide with the boundaries of the computational domain, without reducing the stability of the numerical solution due to the fractional finite volumes. This also simplifies the setting of boundary conditions in such volumes. The advantage of the proposed approach over the generally accepted one is the absence of the global geometric transformations during the entire modelling process, which leads to a reduction in its duration. To perform the numerical modelling, an inviscid ideal compressible gas of constant chemical composition was chosen as a basic model of a continuum. It is described by a system of the unsteady Euler equations in integral form, which was closed by the Mendeleev-Clapeyron equation of state. For the numerical solution of this system, the finite volume method was used with the reconstruction of the flow parameters by the WENO algorithm of the third order of accuracy. The solution of the Riemann problem was carried out using the Lax-Friedrichs relations. Time integration of the system of equations was performed using the explicit Runge-Kutta method of the third order of accuracy. All calculations were carried out on a uniform rectangular Cartesian mesh, which lines did not coincide with the boundaries of the computational domain. The results were compared with the solution of the same problem using the ANSYS Fluent on an unstructured mesh coinciding with the boundaries of the computational domain. The value of the relative error obtained as a result of comparing both solutions did not exceed 0.05.

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Section: Introductionmentioning

confidence: 99%

The Application of the Extended Cells Method to Simulate the Flow of Combustion Gases in the Lpre Chamber

Дубровський,

Бучарський

2023

Rocket-Sp. Tech.

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“…Li [7] modeled the mixing and combustion of the jet engine on a laboratory scale by the Eulerian‐Lagrangian discrete phase model and Peng‐Robinson thermodynamic equation. Taghavi [8] simulated the liquid propellant engine in the turbulent flow field to investigate the thrust, the special impulse and the combustion chamber pressure. By comparing the finite rate chemistry model and the frozen model with experimental data, it was concluded that the finite rate chemistry model had acceptable results.…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling and Experimental Investigation of Spray Combustion Process in Regenerative Liquid Propellant Mortar

Liu¹,

Sun²,

Shen³

2022

Propellants Explo Pyrotec

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Regenerative liquid propellant guns (RLPGs) have been studied for many years. However, the presence of large pressure oscillations is observed in almost each RLPG firing. In order to push forward the liquid propellant application in guns, a low pressure firing system called regenerative liquid propellant mortar (RLPM) is developed. The multiphase multidimensional fluid‐dynamics model is presented to research the interior ballistic properties of RLPM. A high‐speed liquid sheet spray model is presented for the annular jet in RLPM based on the linear stability analysis and surface wave breakup theory. In addition to the jet atomization, the droplets secondary breakup is considered. The experiments on a 60 mm RLPM test fixture are carried out, and the results indicate that the liquid propellant combustion oscillations are effectively suppressed. The spray and combustion processes have been simulated for the 60 mm RLPM which are in agreement with the experimental data well. Numerical results indicate an important benefit for the RLPM that the muzzle velocity is improved by increasing the charge quantity while the maximum chamber pressure remains unchanged.

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“…With the development of manned space technology, aerospace missions are becoming increasingly complicated, as such technology leads to greater difficulties in launching security (Taghavi et al, 2018;Zidane et al, 2019). To improve the launch power of the heavy launch vehicle, a scheme including many engines working simultaneously was selected, what is more, an increase in the vehicle's carrying capacity was attained (Koch, 2019).…”

Section: Introductionmentioning

confidence: 99%

Numerical study for the flame deflector design of four-engine liquid rockets

Zhou

Zhang²,

2020

Engineering Applications of Computational Fluid Mechanics

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The thermal environment of four-engine liquid rocket exhaust plume impinging on the flame deflector with different impingement and uplift angles is analysed. The supersonic exhaust gas impinging model was established by using the compressible, multi-component, Reynolds-Averaged Navier-Stokes (RANS) equations with the finite volume method. A comparison between the numerical results and experimental data in the literature is made, which verified the validity and accuracy of the numerical model. Additionally, the flow fields of the four-engine rocket impinging on the flame deflector under different impingement and uplift angles are simulated. The results show that high temperatures on the deflector surface mainly occur on the impingement point or the cambered surface. A large impingement angle causes the reverse flow intensity to increase whilst a small angle causes the exhaust gas to deflect a little, a suitable uplift angle can smoothly guide the exhaust gas away from the deflector that the best thermal environment of the deflector channel appears at an impingement angle of 25°and an uplift angle of 5°. This study demonstrates that our model can effectively simulate the impinging flow field, and can be of use for the design of the flame deflector under the multi-engine rocket exhaust gas impact.

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Numerical analysis of reactive turbulent flow in the thrust chamber of RD-108 engine rocket

Cited by 5 publications

References 21 publications

The Application of the Extended Cells Method to Simulate the Flow of Combustion Gases in the Lpre Chamber

The Application of the Extended Cells Method to Simulate the Flow of Combustion Gases in the Lpre Chamber

Numerical Modeling and Experimental Investigation of Spray Combustion Process in Regenerative Liquid Propellant Mortar

Numerical study for the flame deflector design of four-engine liquid rockets

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