A Computational Study Of Gas Turbine Combustion Chamber Flow Field


This paper describes the calculation of the flow field in a gas turbine combustion chamber. The extension of an incompressible flow calculation method to the calculation of subsonic compressible flow is used for the present work. The method incorporates a special feature very useful for the gas turbine flow field calculations in that it avoids any special formulation of the numerical scheme to account for density variations; instead, density is calculated directly from the perfect gas equation of state. Convergence problems associated with the calculation of density from the equation of state are avoided because the procedure involves only small changes in the flow variables at each step. The suitability of the K-E turbulence model to predict gas turbine flow fields is discussed. A discussion of the computational grid used for the present predictions is provided to put in perspective the question of grid independent solutions. Velocity and turbulent kinetic energy profiles are provided and comparisons are made with experimental data. The important question of the relationship between the reattachment length and heat transfer is addressed in detail. Results from the present study along with those from previous studies are provided in order to shed light on the reattachment phenomenon, and concludes that the problems of heat transfer and reattachment are closely related. The results of this study have practical applications in turbojet combustion chamber design and development which require accurate information on aspects such as mixing, flow separation, reattachment and heat transfer. © Freund Publishing House Ltd.


Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)

2191-0332; 0334-0082

Document Type

Article - Journal

Document Version

Final Version

File Type





© 2023 De Gruyter, All rights reserved.

Publication Date

01 Jan 1992