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


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 carbon–carbon 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.

About the authors

A. V. Krivonogov

branch of the Military Academy of Strategic Missile Forces named after Peter the Great, branch in Serpukhov, Moscow region

Author for correspondence.

Russian Federation

adjunct (graduate student)


  1. Dezhina I.G., Ponomarev A.K., Frolov A.S., Zorin D.N., Psakhie S.G., Gurdal Zafer, Azarov A.V., Abaimov S.G., Belov M.V., Danilin I.V., Efimov A.R., Kurakova N.G., Zinov V.G., Tsvetkova L.A., Eremchenko O.A. Novye proizvodstvennye tekhnologii: publichnyy analiticheskiy doklad [Public Analytical Report on «Advanced Manufacturing Technologies»]. Moskow: Izdatel'skiy Dom «Delo» RANKhiGS Publ., 2015. 272 p.
  2. Solodovnikov A.V., Krivonogov A.V. Primenenie additivnykh tekhnologiy i sovremennykh materialov v zhidkostnykh raketnykh dvigatelyakh. Sbornik trudov 35-y Vseros-siyskoy nauchno-tekhnicheskoy konferentsii «Problemy effektivnosti i bezopasnosti funktsionirovaniya slozhnykh tekhnicheskikh i informatsionnykh sistem».V. 2. Serpukhov: Filial VA RVSN im. Petra Velikogo Publ., 2016. P. 254-258. (In Russ.)
  3. Grechukh L.I., Grechukh I.N. Proektirovanie zhidkostnogo raketnogo dvigatelya [Design of a liquid-propellant rocket engine]. Omsk: Omsk State Technical University Publ., 2011. 69 p.
  4. Galkin G.N., Chezhegov V.E. Dvigatel'nye ustanovki raket. Raschet i postroenie ukorochennogo profilirovannogo sopla s uglovym vkhodom [Rocket power plants. Calculation and construction of a shortened bell-shaped nozzle with an angular entrance]. Serpukhov: Izdatel'sko-poligraficheskiy Kompleks SVIRV Publ., 2005. 56 p.
  5. Vasil'ev A.P., Kudryavtsev V.M., Kuznetsov V.A., Kurpatenkov V.D., Obel'nitskiy A.M., Polyaev V.M., Poluyan B.Ya. Osnovy teorii i rascheta zhidkostnykh raketnykh dvigateley: uchebnik dlya vuzov [Fundamentals of theory and calculation of liquid rocket engines. Undergraduate textbook]. Moscow: Vysshaya Shkola Publ., 1975. 656 p.
  6. Alemasov V.E. Teoriya raketnykh dvigateley [Theory of rocket engines]. Moscow: NGTI Oborongiz Publ., 1963. 476 p.
  7. Kuznetsov G.V., Sheremet M.A. Raznostnye metody resheniya zadach teploprovod-nosti: uchebnoe posobie [Difference methods for solving heat conduction problems. Study guide].Tomsk: Tomsk Polytechnic University Publ., 2007. 172 p.



Abstract - 92

PDF (Russian) - 235

Article Metrics

Metrics Loading ...




  • There are currently no refbacks.

Copyright (c) 2017 VESTNIK of Samara University. Aerospace and Mechanical Engineering

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies