固体火箭发动机碳/碳复合材料喷管的传热及烧蚀特性研究

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中图分类号：TK124 文献标志码：A

DOI： 10.7652/xjtuxb202506003 文章编号：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

固体火箭发动机（SRM）通过喷管，将药柱燃烧产生的高温高压燃气从相对较低的速度转化为高动能状态，从而产生推力[1]。（剩余17013字）