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Numerical simulation of axial liquid film cooling in rocket combustor

航空动力学报 2013年第2期28卷 459-465页

作者： YANG Wei SUN Bing ZHENG Li-ming School of Astronautics Beijing University of Aeronautics and Astronautics

Numerical simulation has been done for liquid film cooling in liquid rocket combustor.Multiple species of axial Navier-Stokes equations have been solved for liquid-film / hot-gas flow field,and k-εequations have been used for compressible turbulent flow.The results of the model agree well with the results of software FLUENT.The results show that :(1) liquid film can decrease the wall heat flux and temperature effectively,and the cold border area formed by the film covers the whole combustor and nozzle wall.(2) The turbulent viscosity is higher than the physical viscosity,and its biggest value is in the border area of the convergent area in nozzle.The effect of turbulent flow on the whole simulation field can not be ignored.(3) The mass fraction of kerosene at the film inlet is 1,but it decreases along the nozzle wall and achieves its lowest value at the outlet.However,the mass fraction of kerosene near the wall is the biggest at any axial location.

关键词： liquid rocket engine liquid film cooling heat flux numerical simulation turbulent flow

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Numerical investigation of transcritical liquid film cooling in a methane/oxygen rocket engine

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航空动力学报 2011年第4期26卷 903-916页

作者： YANG Wei SUN Bing School of Astronautics Beijing University of Aeronautics and Astronautic Beijing 100191 China

Transcritical film cooling was investigated by numerical study in a methane cooled methane/oxygen rocket engine.The respective time-averaged Navier-Stokes equations have been solved for the compressible steady three-dimensional(3-D) flow.The flow field computations were performed using the semi-implicit method for pressure linked equation(SIMPLE) algorithm on several blocks of nonuniform collocated grid.The calculation was conducted over a pressure range of 202 650.0 Pa to 1.2×107 Pa and a temperature range of 120.0 K to 3 568.0 K.Twenty-nine different cases were simulated to calculate the impact of different factors.The results show that mass flow rate,length,diameter,number and diffused or convergence of film jet channel,injection angle and jet array arrangements have great impact on transcritical film cooling effectiveness.Furthermore,shape of the jet holes and jet and crossflow turbulence also affect the wall temperature distribution.Two rows of film arranged in different axial angles and staggered arrangement were proposed as new liquid film arrangement.Different radial angles have impact on the film cooling effectiveness in two row-jets cooled cases.The case of in-line and staggered arrangement are almost the same in the region before the second row of jets,but a staggered arrangement has a higher film cooling effectiveness from the second row of jets.

关键词： liquid film cooling numerical study rocket transcritical semi-implicit method for pressure linked equation(SIMPLE) film cooling effectiveness

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Numerical study of wave disturbance in liquid cooling film

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Propulsion and Power Research 2013年第2期2卷 107-118页

作者： S.R.Shine S.SunilKumar B.N.Suresh deparment of aeroxpace engineering indian institute of space science and teclnologythirnvananthapuram695547ndia thermal engineering division liquid propulsion systems centreindian space research organization.thiriwvananthapuram695547india indian space research organization isro hobangaloreindia

Transient numerical simulations are carried out to investigate the liquid-gas interfacecharacteristics associated with liquid film cooling flows.A two-dimensional axisymmetricmulti-phase numerical model using finite volume formulation is developed.The model hasbeen validated against available experimental data for liquid-film cooling flows inside tubes.The model has been used to predict the interface characteristics for a variety of imposedparameters and momentum flux ratios under cold flow conditions wherein both the coolant andmainstream are maintained at the same temperature.Disturbance waves are observed at theliquid-gas interface for coolant flows above a critical value and after a finite distance from theinlet.The distance toward the wave inception point increased with the increase of momentumflux ratio.However,at higher momentum flux ratios,the properties of the disturbance wavesdid not vary significantly.The parameters related to the liquid-gas interface waves,namely,wave velocity,frequency,amplitude and wave length have been analyzed in detail.Analysisindicates that the liquid entrainment is due to the shearing of the disturbance wave crest.

关键词： liquid film cooling liquid entrainment Interface disturbances Rocket combustion chamber Numerical analysis

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