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

GUO Zhenyuan; DAI Yanjun; WANG Yungang

doi:10.7652/xjtuxb202506003

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

Special Topic　Combustion Process | 更新时间：2025-08-26

- Research on Heat Transfer and Ablation Characteristics of C/C Composite Nozzle in Solid Rocket Motor
- Journal of Xi’an Jiaotong University Vol. 59, Issue 6, Pages: 21-31(2025)
- 作者机构：
  
  西安交通大学能源与动力工程学院， 710049，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202506003
  CLC： TK124
- Received：11 November 2024，
  
  Online First：07 February 2025，
  
  Published：10 June 2025
- 稿件说明：
移动端阅览
GUO Zhenyuan, DAI Yanjun, WANG Yungang. Research on Heat Transfer and Ablation Characteristics of C/C Composite Nozzle in Solid Rocket Motor[J]. Journal of Xi’an Jiaotong University, 2025, 59(6): 21-31.
DOI：

GUO Zhenyuan, DAI Yanjun, WANG Yungang. Research on Heat Transfer and Ablation Characteristics of C/C Composite Nozzle in Solid Rocket Motor[J]. Journal of Xi’an Jiaotong University, 2025, 59(6): 21-31. DOI： 10.7652/xjtuxb202506003.

摘要

为精确分析火箭发动机喷管烧蚀过程及准确预

测喷管壁面的烧蚀率，基于FLUENT软件和自定义函数二次开发程序，建立考虑化学烧蚀、机械侵蚀和壁面退移的动态耦合模型，采用数值方法模拟喷管内的流动传热和烧蚀，分析了喷管内的流动、传热、烧蚀特性以及影响烧蚀的主要因素。模拟结果表明：喷管喉部上游区域烧蚀最为严重，第5 s时，烧蚀率峰值为0.44 mm·s

－1

；化学烧蚀是造成喷管烧蚀的主要原因，与喷管入口压力和温度正相关；辐射换热对烧蚀的影响主要体现在点火初期；机械侵蚀主要发生在喷管收敛段区域，与颗粒粒径和质量流量近似成正比，颗粒粒径为100 μm时，机械侵蚀率峰值为0.04 mm·s

－1

，粒径每增大25 μm，机械侵蚀率峰值增加0.01～0.02 mm·s

－1

，质量流量每增大0.2 kg·s

－1

，机械侵蚀率峰值约增加0.015 mm·s

－1

。该研究可为固体火箭发动机喷管的热防护设计提供参考。

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 0.44 mm·s

－1

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 0.04 mm·s

－1

when the particle diameter was 100 μm. Additionally

the peak mechanical erosion rate increased by 0.01 to 0.02 mm·s

－1

for every 25 μm increase in particle diameter

and approximately 0.015 mm·s

－1

for every increase of 0.2 kg·s

－1

in mass flow rate. The research provides a reference basis for the thermal protection design of solid rocket e

ngine nozzles.

关键词

Keywords

references

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