Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector

Nobuyuki YATSUYANAGI

doi:10.2322/tjsass.52.180

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Online ISSN : 2189-4205
Print ISSN : 0549-3811
ISSN-L : 0549-3811

Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector

Nobuyuki YATSUYANAGI

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Keywords: LOX/Liquid-Methane Rocket Engine, LOX/LNG Rocket Engine, Coaxial Injector, C^* Efficiency, Combustion Stability

JOURNAL FREE ACCESS

2009 Volume 52 Issue 177 Pages 180-187

DOI https://doi.org/10.2322/tjsass.52.180

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Abstract

A comprehensive design method for a LOX/Liquid-Methane (L-CH₄) rocket engine combustor with a coaxial injector and the preliminary design of the regenerative cooling combustor with 100-kN thrust in vacuum at a combustion pressure of a 3.43 MPa are presented. Reasonable dimensions for the combustor that satisfy the targeted C^* efficiency of more than 98% and combustion stability are obtained.

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