Combustion process effect on the swirled flow structure behind a burner of the gas turbine engine combustion chamber

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Zubrilin I. A.1*, Didenko A. A.1**, Dmitriev D. N.2***, Gurakov N. I.1****, Hernandez M. M.1*****

1. Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia
2. “Kuznetsov”, 29, Zavodskoye shosse, Samara, 443009, Russia

*e-mail: zubrilin416@mail.ru
**e-mail: aanm_didenko@rambler.ru
***e-mail: ddn-rover@mail.ru
****e-mail: nikgurakov@gmail.com
*****e-mail: mariohernandezmo_4_2@hotmail.com

Abstract

The article presents the results of computational and experimental study of the swirling flow structure of a swirling jet behind the burner unit of an industrial gas turbine installation. The burner unit being studied in this work is intended for burning poor pre-prepared mixtures. The burner consists of an axial vane swirler with hollow blades through which the main part of the fuel enters, and a “central body”, functioning as a stabilizer with a pilot flame. Natural gas is employed as a fuel. The studies were performed by applied methods of computational gas dynamics and experimental methods. Experimental velocity measurements were performed with a laser Doppler particle velocity meter LAD-056S. Combustion products composition measurements were performed by sampling with subsequent chromatographic analysis. Experimental studies were conducted under the following conditions:

- The inlet temperature Тк = 330 К;

-  Differential pressure ΔP* ≈ 3,3%;

-  Reynolds number at the burner outlet Re ≈ 12000;

-  The proportion of fuel consumption in the standby zone is 11.5% of the total fuel consumption;

-  The excess-air factor for the case of mixing fuel without combustion was α = 2.08, and for the case without combustion α = 1.8.

The flow and combustion processes modelling was performed in three-dimensional unsteady formulation using Large Eddy Simulation (LES) method. Combustion processes were being described with the Flamelet Generated Manifold model. The GRI 3.0 mechanism was selected as the kinetic mechanism of chemical reactions. As a result, a comparison of time- averaged velocity fields and turbulence characteristics was being performed for the case of fuel combustion and without combustion. The obtained simulation results are well agreed with the experimental data on the flow velocity, its fluctuation components, as well as chemical composition. Thus, the employed approach may be applied for calculation study of the combustion processes of the gaseous fuel in swirling flows. An exception is carbon monoxide, which needs to be modeled using approaches accounting for non­equilibrium chemical combustion processes, such as a network of ideal reactors. The flow structure behind the burner was studied in detail, and the characteristics of the recirculation mixing zone were obtained. It was shown, that the fuel supply does not significantly affect the flow structure. It was found, that the combustion process changes the shape of the reverse streams, increasing it in diameter. Mass flow while combustion is significantly lower than in the so-called “cold” case. Due to the air-fuel mixture low consumption through the recirculation mixing zone for the given burner unit, the combustion process characteristics are mainly affected by the interaction between the recirculation mixing zone and the main flow. Pressure fluctuations associated with the vortex core precession, detected while cold purges, were not found during combustion.

Keywords:

gas turbine power plant, combustion chamber, large eddy simulation, experimental measurements

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