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    Turbulent flow in converging nozzles, part one: Boundary layer solution

    , Article Applied Mathematics and Mechanics (English Edition) ; Volume 32, Issue 5 , 2011 , Pages 645-662 ; 02534827 (ISSN) Maddahian, R ; Farhanieh, B ; Firoozabadi, B ; Sharif University of Technology
    2011
    Abstract
    The boundary layer integral method is used to investigate the development of the turbulent swirling flow at the entrance region of a conical nozzle. The governing equations in the spherical coordinate system are simplified with the boundary layer assumptions and integrated through the boundary layer. The resulting sets of differential equations are then solved by the fourth-order Adams predictor-corrector method. The free vortex and uniform velocity profiles are applied for the tangential and axial velocities at the inlet region, respectively. Due to the lack of experimental data for swirling flows in converging nozzles, the developed model is validated against the numerical simulations. The... 

    Simulation of turbulent swirling flow in convergent nozzles

    , Article Scientia Iranica ; Volume 19, Issue 2 , 2012 , Pages 258-265 ; 10263098 (ISSN) Nouri-Borujerdi, A ; Kebriaee, A ; Sharif University of Technology
    Abstract
    This work simulates the turbulent boundary layer of an incompressible viscous swirling flow through a conical chamber. To model the pressure gradient normal to the wall, the radial and tangential velocity components across the boundary layer have been calculated by both the integral and numerical methods. The numerical solution is accomplished by finite difference, based on the finite volume method. The results show that the radial and tangential boundary layer thicknesses depend on the velocity ratios, Reynolds number and nozzle angle. The peak of radial and tangential boundary layer thicknesses are located at zL≈0.2 and zL≈0.8 from the nozzle inlet, respectively. Due to the short length of... 

    Acoustic characteristics of a rocket combustion chamber: radial baffle effects

    , Article Applied Acoustics ; Volume 70, Issue 8 , 2009 , Pages 1051-1060 ; 0003682X (ISSN) Farshchi, M ; Mehrjou, H ; Salehi, M. M ; Sharif University of Technology
    2009
    Abstract
    This paper describes methods used for determining the characteristic acoustic modes and frequencies of a liquid-propellant rocket-motor combustion chamber and effects of radial baffles on the chamber's acoustic field. A multi-point sensing experimental setup, including stationary and moving sensors, was used to measure characteristic frequencies and mode shapes of a combustion chamber. A new technique based on the comparison of signal phase angles from stationary sensors to that of a moving sensor was used to map complex characteristic mode shapes of a combustor. A three-dimensional Helmholtz acoustic solver was also developed using an efficient finite volume approach for complex geometries...