Modified computation of the nozzle damping coefficient in solid rocket motors

Liu, Peijin1; Wang, Muxin1; Yang, Wenjing1; Gupta, Vikrant2; Guan, Yu3; Li, Larry K. B.3

2018-02

10.1016/j.actaastro.2017.12.006

ACTA ASTRONAUTICA   影响因子和分区

0094-5765

1879-2030

In solid rocket motors, the bulk advection of acoustic energy out of the nozzle constitutes a significant source of damping and can thus influence the thermoacoustic stability of the system. In this paper, we propose and test a modified version of a historically accepted method of calculating the nozzle damping coefficient. Building on previous work, we separate the nozzle from the combustor, but compute the acoustic admittance at the nozzle entry using the linearized Euler equations (LEEs) rather than with short nozzle theory. We compute the combustor's acoustic modes also with the LEEs, taking the nozzle admittance as the boundary condition at the combustor exit while accounting for the mean flow field in the combustor using an analytical solution to Taylor-Culick flow. We then compute the nozzle damping coefficient via a balance of the unsteady energy flux through the nozzle. Compared with established methods, the proposed method offers competitive accuracy at reduced computational costs, helping to improve predictions of thermoacoustic instability in solid rocket motors.

Nozzle damping coefficient Nozzle admittance Solid rocket motor

SCI ; EI

英语

其他

Engineering

Engineering, Aerospace

WOS:000427342500039

PERGAMON-ELSEVIER SCIENCE LTD

20175004533583

Combustors ; Computation theory ; Damping ; Rocket engines ; Rockets ; System stability ; Thermoacoustics

Combustors:521.2 ; Fluid Flow, General:631.1 ; Rockets and Missiles:654.1 ; Rocket Engines:654.2 ; Computer Theory, Includes Formal Logic, Automata Theory, Switching Theory, Programming Theory:721.1 ; Acoustics, Noise. Sound:751 ; Mechanics:931.1 ; Systems Science:961

ENGINEERING

Web of Science

1.Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian, Shaanxi, Peoples R China
2.Southern Univ Sci & Technol, Dept Mech & Aerosp Engn, Shenzhen, Peoples R China
3.Hong Kong Univ Sci & Technol, Dept Mech & Aerosp Engn, Hong Kong, Hong Kong, Peoples R China

Liu, Peijin,Wang, Muxin,Yang, Wenjing,et al. Modified computation of the nozzle damping coefficient in solid rocket motors[J]. ACTA ASTRONAUTICA,2018,143:391-397.

Liu, Peijin,Wang, Muxin,Yang, Wenjing,Gupta, Vikrant,Guan, Yu,&Li, Larry K. B..(2018).Modified computation of the nozzle damping coefficient in solid rocket motors.ACTA ASTRONAUTICA,143,391-397.

Liu, Peijin,et al."Modified computation of the nozzle damping coefficient in solid rocket motors".ACTA ASTRONAUTICA 143(2018):391-397.