Conjugate heat and mass transfer at heterogeneous burning surface of AP/HTPB/Al composite propellant at 2-10 MPa

被引:6
作者
Liu, Shuyuan [1 ]
Han, Luyang [1 ]
He, Pengxiang [1 ]
Wang, Limin [2 ]
Han, Jinchao [1 ]
Hu, Songqi [1 ]
机构
[1] Northwestern Polytech Univ, Internal Flow & Thermostruct Lab, Sci & Technol Combust, Xian 710072, Peoples R China
[2] Natl Univ Def Technol, Coll Aerosp Sci & Engn, Changsha 410073, Peoples R China
基金
中国国家自然科学基金;
关键词
HTPB composite propellant; Combustion mechanism; Conjugate heat and mass transfer; Burning rate model; Heterogeneous burning surface; COMBUSTION; TURBULENCE; PARTICLES;
D O I
10.1016/j.applthermaleng.2023.120362
中图分类号
O414.1 [热力学];
学科分类号
摘要
Conjugate heat and mass transfer at heterogeneous burning surface has significant effect on combustion char-acteristics of AP/HTPB/Al composite propellant. In the present study, the conjugate heat and mass transfer characteristics of AP/HTPB/Al composite propellant are studied experimentally and numerically based on formulated combustion model and experimental facilities. With the increase of pressure and Al content, flame temperature increases significantly and leads to stronger heat transfer to the burning surface. With the content of Al varying from 18 wt% to 9 wt%, the total heat transfer coefficient decreases for all the sampled positions of the burning surface with a maximum decrease of 12% at the AP/HTPB interface. It is found that heat convection accounts for more than 97% of the total heat transfer coefficient. However, with pressure increasing from 2 MPa to 10 MPa, the total heat transfer coefficient and the respective contribution of heat convection and radiation vary slightly. Owing to the heterogeneous sandwich-like structure of the propellant, the temperature distribution at the burning surface of propellant is highly non-uniform. Therefore, heat transfer characteristics vary signifi-cantly at different positions of the burning surface. The heterogeneity of the burning surface is exacerbated by the non-uniform distribution of heat transfer coefficients at different positions of the burning surface. The burning rate of the propellant varies from 0.5 mm/s to 9.5 mm/s for different positions of the burning surface at 10 MPa. The results of micro-scale flame structure show that the mass transfer of fine Al particles in the com-bustion of AP/HTPB/Al composite propellant can be basically divided into four stages, i.e., migration, melting, agglomeration and oxidation/combustion. Coral reef-like aggregate structure is formed by some of the fine Al particles before oxidation and combustion. Increasing pressure is conducive to avoiding formation of large Al agglomerates and enhancing mass transfer at the heterogeneous burning surface.
引用
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页数:16
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