Numerical simulation of gas temperature spatial distribution in a one-burner sector of a gas turbine combustor with uncertain initial conditions of fuel atomization

Abstract


The influence of the initial conditions used when modeling atomized fuel on the accuracy of gas temperature field non-uniformity at the exit of a helicopter gas turbine annular reverse-flow combustor is analyzed. The analysis is based on the numerical solution of the problem of a three-dimensional two-phase flow with combustion. Computations for four models of fuel droplet feed are based on the integration of Reynolds equations for the gas phase and Lagrange equations for the fuel droplets. The influence of the initial conditions on the combustor exit gas temperature field non-uniformity is found to be insignificant. The comparison of the numerical results with the test data showed their better agreement for radial rather than circumferential nonuniformity.


About the authors

V. Ye. Kostyuk

National Aerospace University – Kharkiv Aviation Institute (KhAI)

Author for correspondence.
Email: kostyuk.v@mail.ru

Ukraine

Candidate of Technical Science

Senior Researcher

Ye. I. Kirilash

National Aerospace University – Kharkiv Aviation Institute (KhAI)

Email: kirilashelena@rambler.ru

Ukraine

Research Assistant

A. V. Stasyuk

«Motor Sich» plc, Zaporozhye

Email: kb-5.ugk@motorsich.com

Ukraine

Head of the Combustion Chambers Department

V. V. Shein

«Motor Sich» plc, Zaporozhye

Email: kb-5.ugk@motorsich.com

Ukraine

Head of Design- and-experimental Group of the Combustion Chambers Department

D. V. Karzov

«Motor Sich» plc, Zaporozhye

Email: kb-5.ugk@motorsich.com

Ukraine

Engineer of the Combustion Chambers Department

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