TY - GEN
T1 - Varying Secondary Flow Area in a Single Coaxial Injector for a Methane/Oxygen Diffusion Flame Burner
AU - Ianuzzi, Makayla L.L.
AU - Hollingshead, Joshua M.
AU - Moore, Jeffrey D.
AU - Risha, Grant A.
N1 - Funding Information:
The authors wish to thank the Penn State Altoona Research and Sponsored Programs Office and Mr. Corey Gracie-Griffin for sponsoring this internally-funded effort. The authors would like to also thank Dr. Ivan Esparragoza for sponsoring this research through a grant. Special thanks to Mr. Tom Hatch, Mr. Russ Heaton, and Mr. Jonathan Hileman for fabrication of the injector end caps.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2021
Y1 - 2021
N2 - The focus of this research work was understanding the effect of varying the secondary flow area in a single coaxial injector on flame stability in an experimental non-premixed flame burner. The reactants were methane and oxygen, mixed and ignited in a horizontally-mounted, rectangular combustion chamber using a retractable spark plug. Gaseous oxygen was the primary flow and gaseous methane was the secondary flow. Using optical windows on both sides of the chamber parallel to the axis of the flame, the product flame behavior and flame standoff distance was observed. Results will be presented on the stability of the non-premixed flame based upon equivalence ratio, reactant Reynolds numbers, and injector impingement angle.
AB - The focus of this research work was understanding the effect of varying the secondary flow area in a single coaxial injector on flame stability in an experimental non-premixed flame burner. The reactants were methane and oxygen, mixed and ignited in a horizontally-mounted, rectangular combustion chamber using a retractable spark plug. Gaseous oxygen was the primary flow and gaseous methane was the secondary flow. Using optical windows on both sides of the chamber parallel to the axis of the flame, the product flame behavior and flame standoff distance was observed. Results will be presented on the stability of the non-premixed flame based upon equivalence ratio, reactant Reynolds numbers, and injector impingement angle.
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U2 - 10.2514/6.2021-3361
DO - 10.2514/6.2021-3361
M3 - Conference contribution
AN - SCOPUS:85126604325
SN - 9781624106118
T3 - AIAA Propulsion and Energy Forum, 2021
BT - AIAA Propulsion and Energy Forum, 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum, 2021
Y2 - 9 August 2021 through 11 August 2021
ER -