Method of calculating the thickness of the combustion chamber of a liquid rocket engine made with the use of innovative technologies and materials

Abstract

The use of innovative techniques in the production of parts and assembly units is one of the promising trends connected with increasing mass-energy characteristics of liquid- propellant jet engines. The article presents a concept of development of a liquid-propellant jet engine combustion chamber with the use of modern technologies and materials. We propose making the mixing head according to the additive technology. The cylindrical part of the combustion chamber integrated with the nozzle is to be made of carboncarbon composite material. The article presents a configuration of innovative combustion chamber design and indicates its advantages. The results of calculating geometrical parameters are given for certain initial data. The formulas and results of calculations of the specific heat flow rate along the length of the combustion chamber and the nozzle are also given in the article. The existing methods of over-heating protection of the wall of the chamber are described in the article. The results of testing all these methods of over-heating protection show that they are not efficient enough for the innovative combustion chamber. The new method suggested by the author gives the opportunity to solve the problem by means of calculating the wall thickness taking into account the influence of inner pressure and high temperatures. The method includes both solving the task of transient heat conduction by the finite-deference method and strength calculation using the momentless theory of shells.