Abstract
Method of obtaining tangential holes in the shell of a combustion chamber of liquid-propellant rocket engine is presented in this article. Advantages and disadvantages of technologies for making small diameter holes are consired. The developed technology and tooling made it possible to obtain small diameter holes designed to swirl the coolant flow in the veil belt of the combustion chamber shell. As a result, material and labor costs were reduced in the manufacture of engine components.
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