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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes
SJR: 0.176 SNIP: 0.48 CiteScore™: 1.3

ISSN Print: 1093-3611
ISSN Online: 1940-4360

High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes

DOI: 10.1615/HighTempMatProc.2016017155
pages 23-32

FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY

Omair Alhatim
King Abdul-Aziz City for Science and Technology

ABSTRACT

The influence of the initial conditions in modeling an atomized fuel on the accuracy of evaluating the gas temperature field nonuniformity at the helicopter gas turbine engine annular reverse flow combustor outlet is investigated based on the numerical solution of the problem of combustion two-phase three-dimensional flow. Calculations of four fuel droplet supply models are performed based on the integration of the Reynolds equations for the gas phase and the Lagrange equations for the droplet phase. A slight impact of the initial conditions on the gas temperature field nonuniformity at the combustor outlet is revealed. Comparison of the calculation results and experimental data shows that they are better reconciled in relation to radial nonuniformity than in relation to circumferential one.


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