Abstract
This paper describes on study of optimizing design for rocket combustor of LOX/LH2 engine at supercritical combustion pressure. Specifications of the target engine are the expander cycle one which having thrust of 1 MN at combustion pressure of 10 MPa. Optimization procedure of design is followed by author's formerly presented scheme. That is five cases as to the injection element and two cases as to the combustion chamber contraction ratio are selected as the candidates. Then combustion performance and combustion stability including low frequency and high frequency stability margin are evaluated. The combustion processes and heat flux distribution along the chamber axis are calculated by author's formerly presented supercritical combustion modeling. Low frequency stability is evaluated by Szuch model and by Heidmann model for high frequency instability respectively. Consequently the optimal dimensions and configurations of the injector and the combustor were obtained.
