Optimization of cooling channels of liquid rocket engines using a differential heat transfer model

Volodymyr Sliusariev

Abstract


The subject matter of this study is the thermophysical processes occurring in the cooling channels of liquid-propellant rocket engines. The goal of this research is to create an algorithm for optimizing cooling channels. The tasks include formulating the optimization problem and performing test calculations. The problems were solved using applied mathematics and optimization theory methods. The following results were obtained in the course of addressing the research objectives. The problem formulation was developed based on a literature review, and the structural mass was selected as the objective function. Changes in the geometric parameters of the cooling channels also influence the required pressure of the corresponding pump and, consequently, its mass. The objective function was defined as the total mass of the cooling channels and the coolant pump. The primary function of the cooling circuit is to keep the chamber wall temperature within acceptable limits. To ensure the operability of the optimized geometry, a constraint was implemented through the penalty function method. Furthermore, an optimization algorithm was developed based on the previously derived differential model of the cooling channels. Test calculations were performed using the proposed algorithm. The RD-111 engine’s gas generator and the RD-119 engine’s thrust chamber, for which data were obtained from open sources, were used as test cases. The calculations resulted in a new optimal channel geometry. In the case of the RD-119 engine chamber, the system mass was reduced by 5%. Conclusions. The scientific novelty of the obtained results consists of the development and verification of a new approach to optimizing cooling channels in liquid-propellant rocket engines. This approach is based on a previously proposed differential heat transfer model. The developed optimization algorithm simplifies the cooling system design process, thereby reducing both the time and cost of liquid-propellant rocket engine design.

Keywords


liquid-propellant rocket engine; cooling channels; differential heat transfer model; optimization algorithm; channel geometric parameters; mass minimization

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References


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DOI: https://doi.org/10.32620/aktt.2025.6.03