Characteristics of heat transfer to nickel plated chamber walls of high pressure rocket combustors.

摘要

The performance of two prototype rocket combustors was studied by water-cooled high-pressure combustion tests to reduce the thermal load and to enhance the lifetine of combudtors. In both liquid oxygen (LOX)/gaseous hydrogen and LOX/gaseous methane propellants, the thermal load was reduced by 30-30% by nickel-plated chamber wall, and the thermal resistance of the nickel layer was much larger than calculated values. Many microcracks were observed in the nickel layer in the direction of thickness after tests, and those probably increased the thermal resistance. In LOX/RJ-1J propellant, characteristics of carbon deposition were greatly affected by wall material and/or temperature, the presence of hydrogen, and the injection pattern of propellant. The heat flux was reduced to 50% by carbon deposition under the same combustion pressure and mixture ratio conditions. The nickel layer survived in 30 combustion tests with a total duration of 600 sec. 7 refs., 19 figs., 1 tab.