TY - GEN
T1 - Numerical Analysis on Nozzle Erosion in Hybrid Rocket Motors with Different Injection Parameters
AU - Jiang, Xianzhu
AU - Tian, Hui
AU - Gu, Xiaoming
AU - Gao, Jingfei
N1 - Publisher Copyright:
© 2023 IEEE.
PY - 2023
Y1 - 2023
N2 - This paper investigates the effect of injection parameters on the nozzle erosion in hybrid rocket motors. Hydrosyl-Terminated polybutadiene (HTPB) and 90% hydrogen peroxide \left(\mathrmH-2 \mathrmO_2\right) are adopted as propellants. Two-dimensional steady numerical simulations of gas-liquid two-phase flow are performed. An united numerical calculation of oxidizer atomization and vaporization, propellant combustion, and nozzle thermochemical erosion is conducted. Different oxidizer droplet diameters are considered, and characteristics of combustion flow field and nozzle erosion are discussed. The simulation results indicate that when the droplet diameter increases from 25 μto 50 μm, the residence time increases from 3.21 μms to 22.6 μms. The average fuel regression rate, combustion temperature, chamber pressure, and characteristic velocity of liquid-phase injection are higher than that of gas-phase injection. The throat erosion rate of liquid-phase injection varies from 0.0363 mm/s to 0.0387 mm/s, while that of gas-phase injection is 0.0244 mm/s. When droplet diameter is greater than 50 μm, the throat erosion rate decreases.
AB - This paper investigates the effect of injection parameters on the nozzle erosion in hybrid rocket motors. Hydrosyl-Terminated polybutadiene (HTPB) and 90% hydrogen peroxide \left(\mathrmH-2 \mathrmO_2\right) are adopted as propellants. Two-dimensional steady numerical simulations of gas-liquid two-phase flow are performed. An united numerical calculation of oxidizer atomization and vaporization, propellant combustion, and nozzle thermochemical erosion is conducted. Different oxidizer droplet diameters are considered, and characteristics of combustion flow field and nozzle erosion are discussed. The simulation results indicate that when the droplet diameter increases from 25 μto 50 μm, the residence time increases from 3.21 μms to 22.6 μms. The average fuel regression rate, combustion temperature, chamber pressure, and characteristic velocity of liquid-phase injection are higher than that of gas-phase injection. The throat erosion rate of liquid-phase injection varies from 0.0363 mm/s to 0.0387 mm/s, while that of gas-phase injection is 0.0244 mm/s. When droplet diameter is greater than 50 μm, the throat erosion rate decreases.
KW - hybrid rocket motor
KW - injection parameters
KW - nozle erosion
KW - two-phase combustion flow
UR - https://www.scopus.com/pages/publications/85186743923
U2 - 10.1109/ICMAE59650.2023.10424660
DO - 10.1109/ICMAE59650.2023.10424660
M3 - 会议稿件
AN - SCOPUS:85186743923
T3 - 2023 14th International Conference on Mechanical and Aerospace Engineering, ICMAE 2023
SP - 278
EP - 283
BT - 2023 14th International Conference on Mechanical and Aerospace Engineering, ICMAE 2023
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 14th International Conference on Mechanical and Aerospace Engineering, ICMAE 2023
Y2 - 18 July 2023 through 21 July 2023
ER -