Calculation of screw lines of the shell for cooling combustion chambers of liquid rocket engines

One of the most important processes affecting the efficiency of liquid rocket engines is the cooling of the combustion chamber. Most liquid rocket engine chambers have external cooling, in which coolant flows through the cooling system. An important task is to find the optimal method for calculating the milling trajectory of the liquid rocket engine combustion chamber cooling channel. The initial method for calculating the cooling channel trajectory was considered. It allowed for the accuracy of the helical line construction to be ±40’. To achieve more accurate values, work was carried out to calculate the trajectory of the helical line on an arbitrary conical surface. As a result of this work, a formula was obtained that determines the value of the angular coordinate of the helical line rotation. By approximating the generating curve of an arbitrary body of revolution with a set of segments, we obtain a division of this body into a set of cylinders and cones. This method of constructing a helical line can be used when milling cooling channels on the walls of combustion chamber parts of liquid-propellant rocket engines on CNC machines. It is highly accurate, does not require special software, and has a clear method for reducing calculation errors. At the same time, the discrepancy between the orientation angle of the tool assembly relative to the edge is eliminated. The accuracy of the screw line construction is ensured within ±25’. This made it possible to manufacture cooling channels with a shape close to “ideal”, thereby improving the heat exchange conditions of the combustion chamber and eliminating a number of possible defects.
EDN: GLHBGP, https://elibrary/glhbgp

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