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Performance Study of Air Turbo Rocket Engine with Precooler
Author(s): 
Pages: 302-307
Year: Issue:  2
Journal: Journal of Engineering Thermophysics

Keyword:  air turbo rocketintake precoolingvariable specific heatchemical equilibrium;
Abstract: A thermodynamic cycle model that considers the chemical equilibrium relationships of the fluid compositions and the effect of temperatures and pressures on the thermophysical properties of the fluid is established to investigate the performance of air turbo rocket engines with intake precooler.The cycle performances of three air turbo rocket engines,which adopt LH2,LCH4 and n-C10H22 fuel respectively,are obtained by the model.And the effects of the preheated temperature of the fuel,the temperature at the outlet of the gas generator and the temperature at the outlet of the main burner on the cycle performance are analyzed.The results indicate that the inlet temperature of the compressor is decreased by the intake precooling using fuel.It results in a reduced compression work as the pressure ratio of the compressor is constant.Correspondingly,the temperature of the fuel is increased due to the heating effect of the air to the fuel.The higher temperature of the fuel tends to decrease the flow rate of the propellant.It causes the decrease of the ratio of the propellant flow rate to the air flow rate and the increase of the specific impulse.The results also show that the increase of the fuel temperature results in the decrease of the ratio of the oxygen flow rate to the fuel flow rate.A lower ratio of the propellant flow rate to the air flow rate is obtained.And the specific impulse of the engines is increased.The numerical results indicate that a lower outlet temperature of the gas generator and main burner trends to reduce the the ratio of the propellant flow rate to the air flow rate.It results in the increase of the specific impulse and the decrease of the specific thrust.Compared with the engines without precooler,the application of the precooler will upgrade the flight speed and the specific impulse of the engines.And the comparison among the LH2,LCH4 and n-C10H22 fuels shows that the LH2 fuel is more propitious to the enhancement of the flight speed and the specific impulse for the engines due to the higher ratio of the specific heat capacity to the heat value.It indicates that a higher ratio of the specific heat capacity to the heat value of the fuel will result in a better precooling effect of the engines.The ratio of the specific heat capacity to the heat value of the fuel can be used to evaluate the precooling effect of the engines.
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