Deflagration to detonation transition in chemical rockets with sudden expansion / divergence regions

Sanal Kumar, VR and Chandrasekaran, N and Sankar, V and Sukumaran, A and Nejaamtheen, MN and Doddi, HSN and Rafic, SARM and Baskaran, RV and Mariappan, A and Thianesh, UK and Anandmoorthi, . and Mohan, E and Pradeep, R and Ajay, M (2020) Deflagration to detonation transition in chemical rockets with sudden expansion / divergence regions. In: AIAA Propulsion and Energy 2020 Forum, 24-28 August 2020, Virtual, Online, pp. 1-14.

PDF AIAA_PRO_ENG_FOR_1-14.pdf - Published Version Restricted to Registered users only Download (1MB) | Request a copy

Abstract

We discovered through theoretical studies that, at the creeping inflow conditions, any chemical rocket having port with the sudden expansion / divergent could predispose to deflagration-to-detonation-transition (DDT) at a critical total-to-static pressure ratio (TSPR) due to the phenomenon of Sanal flow choking. At the Sanal flow choking condition, the subsonic flow will get accelerated in the port of a rocket having uniform cross-sectional area due to the area blockage caused by the boundary layer displacement thickness (BLDT). At the Sanal flow choking condition, the lower critical detonation index (LCDI) is an exclusive function of the lowest heat capacity ratio (HCR) of the evolved gases; and the non-dimensional BLDT is an exclusive function of the HCR and the igniter/inflow Mach number. The mathematical model presented herein predicts the possibilities of DDT in all real-world fluid flow systems (continuum / non-continuum), at a critical TSPR, having port with sudden expansion and/or divergence regions or in constricted streamtubes. Note that when the pressure of the non-continuum fluid/nanofluid increases, average-mean-free-path decreases and thus, the Knudsen number reduces leading to a no-slip boundary condition with compressible viscous (CV) flow effect. The Sanal flow choking is a CV flow effect at which both the thermal choking and the wall-friction induced the flow choking converge at the sonic-fluid-throat creating the real-world fluid flow effect, which satisfies all the conservation laws of nature. The offshoot of this study reveals that the Sanal flow choking could lead to asymptomatic hemorrhage in biological systems, and susceptible to catastrophic failures of chemical energy systems including micro and nano thrusters due to the detonation. The risk of Sanal flow choking could be reduced by breaking the blockage, reducing the TSPR and/or increasing the HCR of the gases generating from the upstream region of the port of an internal flow system for keeping the TSPR always lower than LCDI. © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	AIAA Propulsion and Energy 2020 Forum
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	cited By 0; Conference of AIAA Propulsion and Energy 2020 Forum ; Conference Date: 24 August 2020 Through 28 August 2020; Conference Code:244349
Keywords:	Boundary layers; Combustion; Expansion; Incompressible flow; Propulsion; Rockets; Specific heat, Catastrophic failures; Chemical energy systems; Cross sectional area; Deflagration to detonation transition; Displacement thickness; Fluid flow effect; No-slip boundary conditions; Static-pressure ratio, Detonation
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering) Others
Date Deposited:	02 Dec 2020 06:41
Last Modified:	02 Dec 2020 06:41
URI:	http://eprints.iisc.ac.in/id/eprint/66785

Actions (login required)

View Item