Investigation of heat transfer processes in cooling systems of liquid-propellant rocket engines with additive porous structures

Аuthors

Basharina T. A.^*, Levina A. V.^**, Akolzin I. V.^***, Vinokurov D. ^****, Shmatov D. P.^*****

LLC SPE "InterPolaris", Pervomayskaya str., 2, Novovoronezh, Voronezh Region, Russia, 396073

*e-mail: ta@interpolyaris.ru
**e-mail: levinaav@interpolyaris.ru
***e-mail: akolziniv@interpolyaris.ru
****e-mail: vinokurovdmnik@gmail.com
*****e-mail: shmatov@inlerpolyaris.ru

Abstract

To improve the stability and reliability of rocket engines, new technologies are being introduced to intensify heat exchange processes. The combination of the investigated technologies is an innovative cooling system for a liquid-propellant rocket engine in the form of a highly efficient porous structures made by an additive method within cooling path. To study the heat transfer processes during the movement of a single-phase coolant in a cooling path with a porous structure, a computational experiment and thermal-hydraulic tests were carried out. The mathematical model, based on the complete geometric identification of the innerporous space, determines with a high degree of accuracy the thermal-hydraulic characteristics of the coolant, on the basis of which the criterial equations of Nusselt numbers for porous structures with different porosity coefficients are determined. The influence of thermal-hydraulic and geometrical properties of an additive porous medium on the value of the Nusselt number is established. Preliminary computational experiments were carried out, confirming a high degree of reliability of finding the coefficients in the criteria equations for Nusselt numbers and indicating the correctness of the mathematical model of the study. To confirm the effectiveness of the use of porous structures in the cooling path, fire tests of a prototype liquid-propellant low-thrust rocket engine manufactured by an additive method were carried out. It is shown that the use of an additive porous structure in the cooling system of a low-thrust liquid-propellant rocket engine allows for the efficient implementation of the heat removal process from the inner surface of the combustion chamber.

Keywords:

liquid-propellant rocket engine, porous structure, cooling path, thermal-hydraulic studies, mathematical modeling, additive manufacturing, computational experiment, firing tests of liquid-propellant rocket engines

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