Diagnostic investigation of radiation effects on pre-ignition heat flux distribution in dual thrust solid rockets

Vignesh, S and Vishnu, N and Anbarasan, S and Prasanna, TR and Nijanthan, M and Vineeshwar, S and Hemasai, ND and Sathyan, P and Sulthan Ariff Rahman, M and Kumar, VRS (2018) Diagnostic investigation of radiation effects on pre-ignition heat flux distribution in dual thrust solid rockets. In: 12th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2018, 25 - 29 June 2018, Atlanta, Georgia.

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Abstract

Numerical studies have been carried out to examine the radiation effects on the pre-ignition heat flux distribution in the port of the dual-thrust solid propellant rocket motors. Parametric analytical studies have been carried out using an axisymmetric, pressure-based, SST k-ω turbulence model. In the numerical study, a fully implicit finite volume scheme of the compressible Navier–Stokes equation is employed. As a part of the code validation and calibration, the numerically predicted boundary-layer blockage at the Sanal flow choking condition for channel flows is verified using the closed-form analytical model of Sanal Kumar V. R. et al. (AIP Advances, 8, 025315, 2018) and found excellent agreement with the exact solution. Comprehensive diagnostic studies have been carried out in dummy (unignited) dual-thrust solid rocket motors with different port geometries, with and without radiation effects, to examine the influence of transition region on the flow separation and pre-ignition propellant surface heat flux distribution. We observed through several comparisons that with the same inflow conditions and propellant properties the heat flux histories and the time sequences to reach the propellant ignition temperature are different for different port geometries. The numerical results presented in this paper with dummy motor test cases made it possible to examine a number of factors, which are important in the ignition transient studies of high performance dual-thrust solid propellant rocket motors.

Item Type:	Conference Paper
Publication:	2018 Joint Thermophysics and Heat Transfer Conference
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to the American Institute of Aeronautics and Astronautics Inc, AIAA.
Keywords:	Boundary layers; Flow separation; Heat transfer; Ignition; Incompressible flow; Navier Stokes equations; Oceanography; Radiation effects; Rocket engines; Rockets; Solid propellants; Turbulence models, Analytical studies; Finite volume schemes; Heat flux distributions; Ignition temperatures; K-Omega turbulence model; Propellant surfaces; Solid propellant rocket motor; Solid rocket motors, Heat flux
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	20 Aug 2022 06:01
Last Modified:	20 Aug 2022 06:01
URI:	https://eprints.iisc.ac.in/id/eprint/76023

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