Analysis of nonstationary thermal state of a low-thrust liquid rocket engine taking into account injection, evaporation and combustion of liquid fuel droplets

Abstract

The physico-chemical state of reaction products in the combustion chamber of a liquid rocket engine of 500N thrust with account for the evaporation of liquid fuel droplets (highly concentrated hydrogen peroxide (96%) - and kerosene) and their combustion is discussed and analyzed in the paper on the basis of numerical methods. The software system “ANSYS Fluent” which is a universal program for the solution of thermohydraulic problems is used for the purpose.

About the authors

A. G. Vorobiev

Moscow Aviation Institute (National Research University)

Author for correspondence.
Email: formula1_av@mail.ru

Candidate of Science (Engineering), Associate Professor 

Russian Federation

I. N. Borovik

Moscow Aviation Institute (National Research University)

Email: borra2000@mail.ru

Candidate of Science (Engineering), Associate Professor

Russian Federation

Song-Up Ha

KARI - Korea Aerospace Research Institute

Email: mars_hadius@hotmail.com

Senior Research Engineer

Advanced Rocket Research Team

Korea, Republic of

References

  1. Vorobiev A.G., Borovik I.N., Ha S. Developing LRE of low thrust using propellants: strong hydrogen peroxide with kerosene // Vestnik SibGAU im. M.F. Reshetneva. 2011, No. 4 (37). P. 121-126. (In Russ.)
  2. Vasiliev A.P., Kudryavtsev V.M., Kuznetsov V.A., Kurpatenkov V.D., Obelnitsky A.M., Polyaev V.M., Poluyan B.Ja. Osnovy teorii i rascheta ZhRD [Foundations of liquid-propellant engine design theory]. Moscow: Vysshaja Shkola Publ., 1993.
  3. Kozlov A.A., Abashev V.M. Raschet i proektirovanie zhidkostnogo raketnogo dvigatelja maloj tjagi [Calculation and design of a low-thrust liquid-propellant engine]. Moscow: MAI Publ., 2003.
  4. [Fluent Documentation http://www.engres.odu.edu/Applications/fluent6.2/help/index.htm]

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