Convective heat transfer characteristics of rocket kerosene in circular mini-tubes at ultra-high parameter conditions
The regenerative cooling process using rocket kerosene has the specifications of high pressure,high temperature,high heat flux and high mass flow rate.Under the condition of ultra-high parameters,the low-voltage and high-current electrical heating method was used to simulate the thermal environment of the thrust chamber in the rocket engine,and the heat transfer characteristics of rocket kerosene are studied in the high-temperature alloy steel ø2 mm × 0.5 mm round tube.The parameter ranges are of pressure 25-65 MPa,mass flow rate 8 500～51 000 kg/(m2·s),fluid temperature up to～500 ℃and heat flux up to 35 MW/m2.The results indicate that under the tested conditions,the rocket kerosene is in a single-phase liquid forced convection heat transfer mechanism.The heat transfer performance is mainly affected by the fluid temperature and mass flow rate.As the fluid temperature increased,the heat transfer coefficient increases.As the mass flow rate increased,the heat transfer coefficient increases.The pressure in the range of 25-65 MPa has no significant effect on the heat transfer performance.With the increase of heat flux,the inner wall temperature increases significantly,but the variation of heat flux has no significant effect on the heat transfer coefficient.Under the influence of the heat transfer enhance effect at the inlet,the heat transfer coefficient increases,and the higher the heat flux,the more obvious the inlet effect is.The heat transfer characteristics of rocket kerosene under ultra-high parameters,especially under ultra-high pressure conditions,provide a reference for the application of regenerative cooling technology in the rocket engine.
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维普
