Numerical simulation of kerosene atomization in injector of a gas turbine engine

This paper presents the computational study carried out on an aero gas turbine combustor to assess important performance parameters. The CFD results are compared with experimental dataobtained from the full scale combustor tested at ground test stand simulating various operational conditions. The CFD predictions have agreed very well with the experimental data. The model is then extended to predict combustor exit temperature pattern factors, pressure loss, and combustion efficiency and exhaust gas constituents over a wide range of operating pressure and temperature conditions. The paper also presents the studies carried out on the effect of atomizer spray cone angle, particle size and fuel flow variations expected due to manufacturing tolerances in various flow passages as well as due to operational degradations on temperature pattern factors. The pattern factors are also analyzed on cold and hot day environment. The radial pattern factor (RPF) at mid height is found to increase as altitude increases from sea level to 12 km. Spray cone angle is found to have a predominant effect on temperature non-uniformity at exit, lower cone angle increasing both radial and circumferential pattern factors. The findings of this study are valuable inputs for engine performance estimation.

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Calculation of flow characteristics of liquid fuel supplied through pressure jet atomizers of small-sized gas turbine engines

Gurakov

Zubrilin

Morales

et al. 2021

VESTNIK of Samara University. Aerospace and Mechanical Engineer

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The paper presents the results of studying the flow characteristics of liquid fuel in pressure jet atomizers of small-sized gas turbine engines with nozzle diameters of 0.4-0.6 mm for various operating and design parameters. The study was carried out using experimental measurements, semi-empirical correlations and CFD (computational fluid dynamics) methods. The Euler approach, the volume- of- fluid (VOF) method, was used to model multiphase flows in CFD simulations. Good agreement was obtained between experimental and predicted data on the fuel coefficient and the primary spray cone angle at the nozzle outlet. Besides, the assessment of the applicability of semi-empirical techniques for the nozzle configurations under consideration is given. In the future, the flow characteristics in question (the nozzle flow rate, the fuel film thickness, and the primary spray cone angle) can be used to determine the mean diameter of the droplets (SMD) required to fully determine the boundary conditions of fuel injection when modeling combustion processes in combustion chambers of small-sized gas turbine engines.

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Numerical simulation of kerosene atomization in injector of a gas turbine engine

Cited by 3 publications

References 2 publications

Validation of the VOF method for liquid spray process simulation from a pressure-swirl atomizer

Validation of the VOF method for liquid spray process simulation from a pressure-swirl atomizer

Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation

Calculation of flow characteristics of liquid fuel supplied through pressure jet atomizers of small-sized gas turbine engines

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