Accession Number:

ADA616256

Title:

Study of Liquid Breakup Process in Solid Rocket Motors

Descriptive Note:

Technical paper Jan 2014-Jan 2015

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA ROCKET PROPULSION DIV

Personal Author(s):

Report Date:

2014-01-01

Pagination or Media Count:

20.0

Abstract:

In a solid rocket motor SRM, when the propellant combusts, the aluminum is oxidized into alumina Al2O3 which, under the right flow conditions, tends to agglomerate into molten droplets, impinge on the chamber walls, and then flow along the nozzle wall. Such agglomerates can cause erosive damage. The focus of the current research is to characterize the agglomerate flow within the nozzle section by studying the breakup process of a liquid film that flows along the wall of a straight channel while a high-speed gas moves over it. We have used an unsteady-flow Reynolds-Averaged Navier-Stokes code URANS to investigate the interaction of the liquid film flow with the gas flow, and analyzed the breakup process for different flow conditions. The rate of the wave breakup was characterized by introducing a breakup-length-scale for various flow conditions based on the Volume Fraction VF of the liquid, which is an indicator of a two-phase flow liquid breakup level. A smaller breakup-length-scale means that smaller drops have been created during the breakup process. The study covers the breakup and fluid behaviors based on different gas-liquid momentum flux ratios, different surface tension and viscosity settings, different Ohnesorge numbers Oh, and different Weber numbers. Both water and molten aluminum flows were considered in the simulation studies. The analysis demonstrates an effective method of correlating the liquid breakup with the main flow conditions in the nozzle channel path.

Descriptors:

Subject Categories:

  • Fluid Mechanics
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE


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