Research on coupled heat transfer of film cooling in LOX/GH&lt;sub&gt;2&lt;/sub&gt; thrust chambers

Xiang, Jixin; Sun, Bing

doi:10.1299/jtst.2018jtst0035

Cited by 7 publications

(4 citation statements)

References 29 publications

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“…The study showed that the growth rate of the shear layer between the hot and the cold streams is significantly influenced by compressibility. A recent numerical study by Xiang and Sun [ 19 ] incorporating the effect of fuel injection and combustion on film cooling showed that vortex structures formed in the regions close to the injectors enhance the mixing of the coolant with the mainstream and thereby adversely impact the cooling effectiveness.…”

Section: Introductionmentioning

confidence: 99%

Enhancement of Film Cooling Effectiveness in a Supersonic Nozzle

Somasekharan

Srikrishnan

Kumar

et al. 2023

Entropy

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Film cooling as applied to rocket nozzles is analyzed numerically with emphasis on the assessment of the effect of the mixing of coolant with the hot stream. Cooling performance, as characterized by cooling effectiveness, is studied for three different coolants in the three-dimensional, turbulent flow field of a supersonic convergent-divergent nozzle operating with a hot stream temperature of 2500 K over a range of blowing ratios. The coolant stream is injected tangentially into the mainstream using a diffuser-type injector. Parameters influencing the effectiveness, such as coolant injector configuration and mixing layer, are analyzed. Thermal and species mixing between the coolant and the mainstream are investigated with regard to their impact on cooling effectiveness. The results obtained provide insight into the film cooling performance of the gases and the heat transfer characteristics associated with these three gases. An injector taper angle of 30° results in the most effective cooling among the configurations considered (0°, 15°, 30° and 45°). Mixing of the coolant with the hot stream is examined based on the distributions of velocity, temperature and species. The higher values of cooling effectiveness for Helium are attributed to its thermophysical properties and the reduced rate of mixing with the hot stream. The results further indicate that through optimization of the blowing ratio and the coolant injector configuration, the film cooling effectiveness can be substantially improved.

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Section: Introductionmentioning

confidence: 99%

Enhancement of Film Cooling Effectiveness in a Supersonic Nozzle

Somasekharan

Srikrishnan

Kumar

et al. 2023

Entropy

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“…In terms of film cooling, Shine's research [15][16][17] showed that the injector structure has an important impact on film cooling, and there is an optimal blowing ratio for a given geometry. Xiang et al [18][19][20] studied the effect of gas film cooling holes with different angles on the cooling effect in rocket engines with various propellant combinations through experiments and numerical simulation. Fu et al [20] developed a droplet/wall impact model which performed better than the O'Rourke and Amsden model.…”

Section: Introductionmentioning

confidence: 99%

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Chen

Jian

et al. 2023

Aerospace

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To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber, radiation heat transfer, heat conduction in the wall, heat transfer of coolant flow in the cooling channel, and gas film cooling in the thrust chamber wall. The numerical method used in each physical area, the data transfer method between each computing module, the strategy of data transfer on the coupling interface, the calculation process, and the convergence criterion are all introduced in detail. The calculation scheme was verified by analyzing a water-cooled nozzle. Then, the coupled heat transfer calculation was carried out for a liquid rocket engine using a propellant composed of unsymmetrical dimethylhydrazine and dinitrogen tetroxide. Two working conditions were analyzed: whether the gas film cooling was performed or not. The results showed that the algorithm successfully indicated the protective effect of the gas film on the wall surface, and the calculation results were reasonable. It played a guiding role for the coupled heat transfer of the liquid rocket engine using a composite cooling method.

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“…The feasibility of applying the fluid nozzle throat to solid rocket motors was verified. In order to deeply study the performance of film cooling near the ejector area in the LOX/GH2 thrust chamber, Xiang et al 23 studied the conjugate flow and heat transfer behavior of film coolant, hot gas, cooling channel and regeneration coolant through numerical simulation, and established the three-dimensional non-adiabatic flamelet model which used the real gas state equation. Wang et al 24 conducted numerical simulations to study the working characteristics of axisymmetric divergent bypass dual-throat nozzles.…”

Section: Introductionmentioning

confidence: 99%

Analysis of fluid-solid-thermal coupling characteristics of axial-symmetric vectoring exhaust nozzle

Yao

Zhang

Wei

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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Aiming at the problems of axial-symmetric vectoring exhaust nozzle (AVEN) mechanism due to its complex structure, which leads to the large amount of digital simulation calculation under the coupling of multi-physics, and it is difficult to establish the fluid domain model, a complex AVEN structure is proposed as the research object, the method of AVEN flow field simplify model in cylindrical coordinate system. This method simplifies the contact domain between the expansion regulator plate, the cruciform joint, the convergent regulator plate and the flow field into a cylindrical overall physical model, and constructs a fluid-solid coupling heat transfer physical model. The feasibility of the model is verified. The AVEN fluid-solid-thermal coupling digital simulation calculation is carried out using the sequential one-way coupling method. First, based on computational fluid dynamics, the AVEN fluid-solid coupling heat transfer calculation is carried out to calculate the coupling surface temperature and pressure field. Second, the calculated coupling surface temperature is used as the thermal analysis boundary condition. Then, the temperature field calculated by the thermal analysis and the pressure field calculated by the fluid-solid coupling heat transfer analysis are used as the boundary conditions of the structural strength analysis. Finally, fluid-solid-thermal coupling analysis of AVEN including aerodynamic load and thermal load is carried out. The calculation results show that the digital simulation method proposed in this paper can be used in engineering practice. The temperature and pressure of the AVEN coupling surface show a trend of first decreasing, then increasing, and then decreasing with the change of the position from the throat. Some AVEN mechanical components and parts have stress singular phenomena. The deformation of the AVEN structure is obviously affected by the thermal load, and the minimum change of rate is 9.54%, the maximum change of rate is 1845.37%.

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Research on coupled heat transfer of film cooling in LOX/GH<sub>2</sub> thrust chambers

Cited by 7 publications

References 29 publications

Enhancement of Film Cooling Effectiveness in a Supersonic Nozzle

Enhancement of Film Cooling Effectiveness in a Supersonic Nozzle

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Analysis of fluid-solid-thermal coupling characteristics of axial-symmetric vectoring exhaust nozzle

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