Experimental study on ablation of thermal insulation layer in afterburning chamber of solid rocket ramjet during maneuvering flight conditions
The overload effect caused by maneuvering flight can result in the accumulation of combustion gases within afterburning chamber of solid rocket ramjet,leading to a serious erosion area in the thermal insula-tion layer.To address this issue,a test device is designed and established to simulate the thermal environment of the afterburning chamber during maneuvering flight.Numerical simulation is employed to obtain variations in two-phase flow field parameters.Controllability is achieved for ablation parameters such as combustor pressure,surface temperature of the thermal insulation layer,gas velocity,and angle between the gas and thermal insula-tion layer.An experimental investigation is conducted on the maneuvering flight conditions of a certain type of sol-id rocket ramjet using the device,the results demonstrate that the experimental findings satisfy the simulation re-quirements for serious ablation area in the afterburning chamber.The target pressure is 0.45 MPa,and the mea-sured pressure is 0.467 MPa,resulting in a relative error of 3.78%.Additionally,temperature tests during the ex-periment yielded values of 1 245 K and 1 341 K,exhibiting relative errors of 5.62%and 5.14%compared to nu-merical simulation results,respectively.Furthermore,the center temperature of the test specimen is 2 367 K,which corresponds to a relative error of 2.9%when compared to the target temperature.The experimental thermal insulation layer exhibits erosion craters in the direct action area of the gas,with a maximum linear erosion rate of approximately 0.03 mm/s.In the indirect action area,specimen expands,and the crater shapes were influenced by the distribution pattern of the flow field near the specimen.
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