Masters Theses

Abstract

"The use of detonations in combustors has been receiving increased attention in recent times. The presence of shock waves in such combustors invariably poses the existence of two domains that present different physics for the flow processes. The variation of upstream temperature due to radiative heating by the products of combustion was given particular attention in the present study. The modeling of heat transfer across a normal shock wave of negligible thickness was done by considering the reactants and the products of combustion to be in radiative equilibrium with each other. The quantification of emissivity of the products of combustion required the use of suitable numerical gray gas models. Similarly, experimental data from literature were used to obtain the absorptivities of the gaseous reactants used for analyses. The behavior of the species in the reactions were dependent upon the chemical kinetics mechanism used in this study, the reduced GRI-Mech 1.2 mechanism - DRM 19. Parametric analysis of the reactant mixture was carried out to analyze its effect on the upstream variation of temperature and on the absorption length. It was found that a decrease in the inertness of the reactant mixture and the addition of polyatomic gases receptive to radiation reduced the absorption lengths. Increased inlet pressures were found to have increased impact on the upstream region and resulted in extremely small increases in flow temperature. The subsequent effects of radiative preheating on ignition delay were studied and more pronounced reductions in induction times were observed with more oxygen content in the reactants. Overall, the study with one-dimensional approximation provides for an understanding of the process of detonations and describes the inter-dependence of radiative heat transfer and downstream chemical kinetics"--Abstract, page iii.

Advisor(s)

Isaac, Kakkattukuzhy M.

Committee Member(s)

Homan, Kelly
Drallmeier, J. A.

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

Missouri University of Science and Technology

Publication Date

Summer 2012

Pagination

xiii, 89 pages

Note about bibliography

Includes bibliographical references (leaves 75-90).

Rights

© 2012 Pratibha Raghunandan, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Library of Congress Subject Headings

Heat -- Radiation and absorption
Heat -- Transmission
Rocket engines -- Combustion
Shock waves

Thesis Number

T 10067

Print OCLC #

828936600

Electronic OCLC #

801399592

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