Turbulent boundary layer with mass transfer and pressure gradient in solid propellant rocket motors

1995 ◽  
Author(s):  
A Bizot
Keyword(s):  
Boundary Layer ◽  
Mass Transfer ◽  
Turbulent Boundary Layer ◽  
Pressure Gradient ◽  
Solid Propellant ◽  
Rocket Motors ◽  
Solid Propellant Rocket ◽  
Propellant Rocket

scholarly journals Effect of the fluid–structure interaction on solid rocket motors instabilities

2012 ◽  
Author(s):  
J. Richard ◽  
T. Morel ◽  
F. Nicoud
Keyword(s):  
Solid Propellant ◽  
Gas Flow ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Firing Test ◽  
Solid Propellant Rocket ◽  
Acoustic Instabilities ◽  
Solid Rocket ◽  
Coupling Algorithm ◽  
Propellant Rocket

Large solid propellant rocket motors may be subjected to aero-acoustic instabilities arising from a coupling between the burnt gas flow and the acoustic eigenmodes of the combustion chamber. Given the size and cost of any single firing test or launch, it is of first importance to predict and avoid these instabilities at the design level. The main purpose of this paper is to build a numerical tool in order to evaluate how the coupling of the fluid flow and the whole structure of the motor influences the amplitude of the aeroacoustic oscillations living inside of the rocket. A particular attention was paid to the coupling algorithm between the fluid and the solid solvers in order to ensure the best energy conservation through the interface. A computation of a subscaled version of the Ariane 5 solid propellant engine is presented as illustration.

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