Numerical Research On The Coupled Heat Transfer Of Thrust Chamber In Cooling Channel Of Liquid Rocket

The thrust chamber wall of liquid rocket engine is subjected to high gas pressure and temperature,and it is subjected to a strong erosion effect that high velocity gas f low acts on thrust chamber wall.It is necessary to take measures to cool the structure of the thrust chamber for the liquid rocket engine,in order to ensure the structural str ength of thrust chamber which is not damaged and to avoid the damage of the thrust chamber during to the high temperature.With the improvement of computer operation ability,numerical simulation has bee n widely used in various fields.In this paper,coupled heat transfer for regenerative c ooling of liquid rocket engine carrys on the numerical simulation by adopting CFD so ftware Fluent.There is no rib,rib length width ratio changes,different coolant mass f low rate,and cooling of the thrust chamber wall of liquid rocket engine which carrys on the numerical simulation under different cooling fluid flow.The influence of vario us parameters on the cooling of the chamber wall is determined,for the sake of provi ding theoretical guidance for the experiment.When coolant flow increased to a certain extent,the cooling effect of thrust cham ber structure is weaken.With the increase of the flow rate,the cooling effect of the wall becomes weaker,and the heat flux density in the wall of the thrust chamber is i ncreased by strengthening the external heat transfer.This change is most obvious neart he nozzle throat.When the coolant flow direction is opposite to the gas flow directio n,the cooling effect is better than the same direction.Compared with no rib,rib ben efits the cooling effect of the wall under the same coolant flow rate.The increase ofr ib(the increase of the depth and width ratio of rib)will improve the efficiency of rib,but the heat convection between coolant and thrust chamber wall will be weaken ed.Therefore,we should select the appropriate depth width ratio of the fin according to the actual situation,in addition,there is a direct relationship between the temperatu re on the wall of the thrust chamber and the variation of heat flux density and the g eometry of thrust chamber.In the combustion chamber section of thrust chamber,ther e will be a slight reduction in gas velocity during to the effects of fluid viscosity wh en the gas flow cross section is unchanged.In this section,the heat flux density gradually decreases along the axial direction.After entering the contraction section,the cro ss-sectional area of the gas channel decreases,the gas velocity increases,the heat flux density gradually increases,and the maximum value is reached near the throat.Fromn ozzle throat to nozzle exit,gas channel cross-sectional area gradually increases,the he at flux density gradually increase.Nozzle expansion section consists of a small curvat ure arc and a large curvature arc.Gas section change rule In this location,the gas se ction change rule has a sudden change,That make the heat flux density startes a prec ipitous decline in the downstream of the throat position and then gradually tends to b e gentle.This paper will provide the technical reference for the design of the thrust chamb er of the liquid rocket engine and the experiment.