Dimension-Optimizing Design Method For Annular-Type Cooling Channel Of ThrustChamber

摘要

The new-generation liquid oxygen/hydrocarbon propellant liquid fuel rocket enginewill use a high-pressure combustion chamber arrangement. In this case, cooling the thrust chamber becomes a key technical problem. The article presents a design scheme for the geometric-dimension optimization of annular-type regenerative cooling channels. The aim of the optimization is minimum pressure losses as coolant passes through the cooling channel. As shown in typical computations and experiments, application of this optimizing design method can reduce 50% of pressure losses. In other words, the optimization design is advantageous in solving the cooling problem in high-pressure thrust chambers. jg.