Date of Award

3-24-2016

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Darrell S. Crowe, PhD.

Abstract

Cooling of liquid rocket engine combustion chambers and nozzles is a critical component to liquid rocket engine design. A common method of cooling is liquid fuel film cooling. Liquid fuel is injected along the surface of the wall to act as a barrier against the core combustion gases. A numerical model is developed for simulating liquid fuel _lm cooling in a rocket engine using a hydrocarbon fuel. The model incorporates turbulent multiphase ow with species transport within the commercial ANSYS® Fluent CFD software. Conjugate heat transfer is simulated through walls containing embedded cooling channels. A novel User Defined Function is written to incorporate heterogeneous chemical reactions between the liquid fuel and the freestream gases. Comparisons are made between simulations with and without the heterogeneous reactions as well as with simplifications to the cooling channel geometry. It is found that simplifications to the cooling geometry can artificially reduce cooling performance while neglecting the heterogeneous reactions can artificially increase cooling performance.

AFIT Designator

AFIT-ENY-16-M-199

DTIC Accession Number

AD1054144

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