Abstract

With reusability being a novel design parameter for liquid rocket engines (LRE), the need to lower internal wall temperatures for an increased engine longevity is a desired outcome. One of the mechanisms that has been effectively implemented is the use of high aspect ratio cooling channels (HARCC) to promote fin-like effects from internal cooling channel sidewalls. In the gas turbine industry, the use of wedge turbulators has gained recognition for its heat augmentation properties with relatively low pressure drop penalty. In an ideal case, LRE's could adopt the wedge turbulator cooling technique to enhance the benefits of HARCC with minimal penalty; however, the relationship between these two cooling schemes in a LRE environment is relatively unknown. A conjugate heat transfer analysis is performed on wedge turbulator features on various channels of differing aspect ratios. The boundary and initial conditions of the validation channel geometry is taken from a simulated 1 MN Vulcain engine high-aspect ratio cooling channel environment. After smooth walled channels are validated from a previous study, backward facing wedge turbulators are introduced into the channel in order to observe and analyze heat augmentation and pressure drop effects across various aspect ratios.

Notes

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Graduation Date

2021

Semester

Fall

Advisor

Kapat, Jayanta

Degree

Master of Science in Aerospace Engineering (M.S.A.E.)

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Degree Program

Aerospace Engineering; Thermofluid Aerodynamic Systems

Format

application/pdf

Identifier

CFE0008836; DP0026115

Language

English

Release Date

December 2021

Length of Campus-only Access

None

Access Status

Masters Thesis (Open Access)

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