Simulation of supersonic nozzle cooling

Аuthors

Anikeev A. A., Bykov L. V.^*, Molchanov A. M.^**

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: bykovlv@mai.ru
**e-mail: alexmol_2000@mail.ru

Abstract

In this paper the results of simulation of conjugate heat transfer between high-temperature flow and model nozzle are presented. Different types of heat shielding (convective, porous and film) were considered. The presented methods were developed for liquid-fuel rocket engines but it is rather an illustration ofAnsys CFX package solver capabilities in this area, than a simulation of some specific engine with its own type of fuel, principal scheme, etc.

Keywords:

convective heat transfer, supersonic flows, multiphase flow, thermal protection, liquid rocket engines