Novell Application of CFD for Rocket Engine Nozzle Optimization

  • Csaba Jéger Department of Aeronautical and Vehicle Engineering, School of Engineering Sciences, Royal Institute of Technology, Stockholm, Sweden
  • Árpád Veress Department of Aeronautics, Naval Architecture and Railway Department, Faculty of Transport and Vehicle Engineering, Budapest University of Technology and Economics, Hungary

Abstract

Numerical analyses, validation and geometric optimization of a converging-diverging nozzle flows has been established in the present work. The optimal nozzle contour for a given nozzle pressure ratio and length yields the largest obtainable thrust for the conditions and thus minimises the losses. Application of such methods reduces the entry cost to the market, promote innovation and accelerate the development processes. A parametric geometry, numerical mesh and simulation model is constructed first to solve the problem. The simulation model is then validated by using experimental and computational data. The optimizations are completed for conical and bell shaped nozzles also to find the suitable nozzle geometries for the given conditions. Results are in good agreement with existing nozzle flow fields. The optimization loop described and implemented here can be used in the all similar situations and can be the basis of an improved nozzle geometry optimization procedure by means of using a multiphysics system to generate the final model with reduced number sampling phases.

Keywords: rocket engine, converging-diverging nozzle flow, validation, optimization, CFD
Published online
2018-01-10
How to Cite
Jéger, C. and Veress, Árpád “Novell Application of CFD for Rocket Engine Nozzle Optimization”, Periodica Polytechnica Transportation Engineering. doi: https://doi.org/10.3311/PPtr.11490.
Section
Articles