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Solid rocket engine throat liner - hafnium carbide

As Carbon/carbon composite (C/C) has more superior high temperature thermal physical and mechanical properties than other materials, it has been taken as the preferred material of solid rocket engine throat liner. In the process of engine working, under the bad thermal environment, internal curve surface of C/C composite throat liner is damaged due to heat flow scouring ablation with corrosive particles at high temperature, high pressure, and high speed, so the throat diameter enlarges, the surface becomes rough, and the profile is not neat, which will affect the engine working pressure and reduce the exhaust nozzle efficiency. 

If adding 8%-10% HfC material produced by our company in the exhaust nozzle liner carbon substrate of weapon system of certain model, the anti-ablation property of HfC-C/C composite can be improved greatly. The ablation resistance effect of HfC to HfC-C/C composite throat liner mainly includes two aspects: First, under the ablation temperature of 3500℃, HfC reacts in priority with oxygen to form HfO2 in the process of high temperature ablation, effectively preventing the oxidation of carbon fibers and carbon substrate in composite materials in aerobic atmosphere;  Second, HfC has very high strength and hardness, also effectively improving the integrated mechanical abrasion and erosion resistance property of the material, to effectively restrain mechanism erosion caused by the fuel gas to the internal curve surfaces of throat liner. Obviously, the anti-ablation property of Hf C-C/C composite increases along with the increase of HfC content, the test experiment result indicates that when the content of HfC is up to 8%-10%, the linear ablation rate of Hf C-C/C composite throat liner raises an approximate constant stable ablation stage; Under the condition of solid rocket engine test run, integrated throat liner of Hf C-C/C composite shows good anti-ablation property.