固體火箭發(fā)動機碳/碳復合材料噴管的傳熱及燒蝕特性研究

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中圖分類號：TK124 文獻標志碼：A

DOI： 10.7652/xjtuxb202506003 文章編號：0253-987X（2025）06-0021-11

Research on Heat Transfer and Ablation Characteristics of C/C Composite Nozzle in Solid Rocket Motor

GUO Zhenyuan，DAI Yanjun，WANG Yungang （School of Energy and Power Engineering，Xi'an Jiaotong University，Xi'an 71oo49，China）

Abstract： To accurately analyze the ablation process of the nozzle and predict the accurate ablation rate， a dynamically coupled model that integrates chemical ablation， mechanical erosion， and wall recession，based on FLUENT software and user defined functions，is developed in this paper. Numerical simulations were conducted to model the flow，heat transfer，and ablation within the nozzle，exploring the flow characteristics， heat transfer， ablation process， and the factors affecting ablation. The results indicated that the ablation was most severe in the upstream region of the nozzle throat，with the peak ablation rate reaching at the 5th second. Chemical ablation was the primary factor causing nozzle ablation，and it was positively correlated with the inlet pressure and inlet temperature of the nozzle. The influence of radiative heat transfer on erosion was particularly noticeable during the initial ignition phase. Mechanical erosion primarily occurred in the converging section of the nozzle and was approximately proportional to the particle size and the mass flow rate. The peak value of mechanical erosion rate was 0.04mm?s-1 when the particle diameter was . Additionally，the peak mechanical erosion rate increased by 0.01 to 0.02mm?s-1 for every 25μm increase in particle diameter，and approximately 0.015mm?s-1 for every increase of 0.2kg?s-1 in mass flow rate. The research provides a reference basis for the thermal protection design of solid rocket engine nozzles.

Keywords： nozzle;chemical erosion;mechanical erosion;wall recession

固體火箭發(fā)動機（SRM）通過噴管，將藥柱燃燒產(chǎn)生的高溫高壓燃氣從相對較低的速度轉(zhuǎn)化為高動能狀態(tài)，從而產(chǎn)生推力[1]。（剩余17013字）