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某新型号固体火箭发动机的钨渗铜喉衬试车后发生了直径收缩。通过对钨渗铜材料的金相组织、断口形貌、工艺制度以及成分分析发现引起喉衬收缩的原因：一是钨渗铜材料的钨骨架在试车点火时产生的二次烧结收缩；二是材料的高温强度不足，点火试车过程中喉衬沿轴向伸长，相应以径向收缩来补偿体积变化。提出了改善钨－铜材料高温尺寸稳定性的途径并在后续发动机试车实验中获得了成功。
A new type of solid rocket engine tungsten copper lined lining test occurred after the diameter contraction. Through the analysis of microstructure, fracture morphology, process system and composition analysis of the tungsten infiltration copper material, the causes of the contraction of the throat lining were found: firstly, the tungsten skeleton of the tungsten infiltration copper material was shrinked by secondary sintering during the ignition of the test car; The high temperature strength of the material is insufficient. During the test run, the throat lining expands along the axial direction and accordingly compensates for the volume change by radial contraction. The ways to improve the dimensional stability of tungsten-copper material at high temperature were put forward and the success was achieved in the following engine test run.