Reynolds-Averaged Navier-Stokes Analysis of the Flow through a Model Rocket-Based Combined Cycle Engine with an Independently-Fueled Ramjet Stream

CFD;combustion;turbulence;propulsion

Bond, Ryan Bomar ; Dr. Jack R. Edwards, Committee Co-Chair,Dr. D. Scott McRae, Committee Co-Chair,Dr. Hassan A. Hassan, Committee Member,Dr. C. Timothy Kelley, Committee Member,Bond, Ryan Bomar ; Dr. Jack R. Edwards ; Committee Co-Chair ; Dr. D. Scott McRae ; Committee Co-Chair ; Dr. Hassan A. Hassan ; Committee Member ; Dr. C. Timothy Kelley ; Committee Member

University:North Carolina State University

关键词: CFD;    combustion;    turbulence;    propulsion;   

Others  :  https://repository.lib.ncsu.edu/bitstream/handle/1840.16/5383/etd.pdf?sequence=1&isAllowed=y

美国|英语

来源: null

【 摘 要 】

A new concept for the low speed propulsion mode in rocket based combined cycle (RBCC) engines has been developed as part of the NASA GTX program.This concept, called the independent ramjet stream (IRS) cycle, is a variation of the traditional ejector ramjet (ER) design and involves the injection of hydrogen fuel directly into the air stream, where it is ignited by the rocket plume.Experiments and computational fluid dynamics (CFD) are currently being used to evaluate the feasibility of the new design.In this work, a Navier-Stokes code valid for general reactive flows is applied to the model engine under cold flow, ejector ramjet, and IRS cycle operation.Pressure distributions corresponding to cold-flow and ejector ramjet operation are compared with experimental data.The engine response under independent ramjet stream cycle operation is examined for different reaction models and grid sizes.The engine response to variations in fuel injection is also examined.Mode transition simulations are also analyzed both with and without a nitrogen purge of the rocket.The solutions exhibit a high sensitivity to both grid resolution and reaction mechanism, but they do indicate that thermal throat ramjet operation is possible through the injection and burning of additional fuel into the air stream.The solutions also indicate that variations in fuel injection location can affect the position of the thermal throat.The numerical simulations predicted successful mode transition both with and without a nitrogen purge of the rocket; however, the reliability of the mode transition results cannot be established without experimental data to validate the reaction mechanism.