TY - JOUR
T1 - Numerical investigation of surface roughness effects on non-equilibrium flow in expansion section of rocket nozzle
AU - Liu, Yang
AU - Wang, Hai feng
AU - Ma, Dong
AU - Gao, Yong gang
AU - Zhao, Wei
N1 - Publisher Copyright:
© 2022 Elsevier Masson SAS
PY - 2022/5
Y1 - 2022/5
N2 - To further understand the non-equilibrium flow characteristics in a rocket nozzle, we have to consider the rough wall surface caused by nozzle ablation, and explore the relative influence of surface roughness on the flow field, composition field, and wall heat transfer in the nozzle. In this study, first, the data of the inner wall morphology of the real nozzle is obtained through measurement experiments. The parameters used to characterize the inner wall morphology of the expansion section of the nozzle are determined. Then, a computational physical model is built based on these parameters. Finally, the simplified chemical reaction mechanism is used to solve the chemical non-equilibrium flow in the nozzle through the eddy dissipation conceptual model. The numerical calculation method of large eddy simulation is used to obtain the fine structure of the flow field with the shape of the inner wall of the expansion section of the nozzle. The results of the numerical study show that the influence of the wall roughness element of the nozzle expansion section caused by ablation cannot be ignored during the working process of the solid rocket motor. For the non-equilibrium flow in the supersonic nozzle, the roughness element is a crucial factor to promote the flow transition and the generation of hairpin vortices, and it also affects the wall heat transfer and gas composition near the roughness element.
AB - To further understand the non-equilibrium flow characteristics in a rocket nozzle, we have to consider the rough wall surface caused by nozzle ablation, and explore the relative influence of surface roughness on the flow field, composition field, and wall heat transfer in the nozzle. In this study, first, the data of the inner wall morphology of the real nozzle is obtained through measurement experiments. The parameters used to characterize the inner wall morphology of the expansion section of the nozzle are determined. Then, a computational physical model is built based on these parameters. Finally, the simplified chemical reaction mechanism is used to solve the chemical non-equilibrium flow in the nozzle through the eddy dissipation conceptual model. The numerical calculation method of large eddy simulation is used to obtain the fine structure of the flow field with the shape of the inner wall of the expansion section of the nozzle. The results of the numerical study show that the influence of the wall roughness element of the nozzle expansion section caused by ablation cannot be ignored during the working process of the solid rocket motor. For the non-equilibrium flow in the supersonic nozzle, the roughness element is a crucial factor to promote the flow transition and the generation of hairpin vortices, and it also affects the wall heat transfer and gas composition near the roughness element.
KW - Large eddy simulation
KW - Non-equilibrium flow
KW - Nozzle expansion section
KW - Rough wall
KW - Solid rocket motor
UR - https://www.scopus.com/pages/publications/85127511543
U2 - 10.1016/j.ast.2022.107523
DO - 10.1016/j.ast.2022.107523
M3 - 文章
AN - SCOPUS:85127511543
SN - 1270-9638
VL - 124
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 107523
ER -