Reduced Kinetic Model of RP-1/O2 Mixture Combustion for CFD modeling of Rocket Engines

A reduced combustion kinetic model of the RP-1 and oxygen mixture are developed. Constants of reaction rates are presented. Model verification was performed by NASA CEA code comparison in the pressure and the stoichiometric ratio of fuel component range specific for a chambers of rocket engines. Results of computational modeling of the rocket engine RD-170 / RD-180 are described. The model predictions agreed reasonably with known experimental and computational data.

nozzle, gas dynamics, burning, kinetic mechanism, computational modeling, RP-1, liquid rocket engine

Volume 17, issue 1, 2016 year

Упрощенная кинетическая схема горения смеси RP-1/O2 для CFD-расчетов ракетных двигателей

Разработан упрощенный кинетический механизм процесса горения топливной смеси керосина марки RP-1 и кислорода, приведены кинетические константы реакций. Ве-рификация механизма выполнена в диапазоне давлений и стехиометрических соот-ношений компонент топлива, характерных для камер сгорания ракетных двигателей. Описаны результаты численного моделирования ракетного двигателя РД-170/РД-180, демонстрирующие согласование данного механизма с известными паспортными и расчетными данными.

сопло, газодинамика, горение, кинетический механизм, численное моделирование, керосин, жидкостный ракетный двигатель

Volume 17, issue 1, 2016 year

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DOI: 10.2514/6.2013-492