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Investigation of the stream parameter on output power of helicopter’s APU
Today’s the need of industries to the gas turbine implies the study more than ever. In this study, for better understanding of gas turbine combustors, the research begins with an introduction to the equipment of gas turbines and then the numerical computation of the two types of combustors has been checked; the first is annular type and the second is can type.  Most of these engines in aviation industries in Iran get utilized in producing electric power. To investigate the term of operation of the engine, the variation of mass flow and out flow of gas to the compressor and mass discharge of the fuel to the combustor were analyzed. Therefore the investigation used CFD to analyze the temperature contour of combustors and the flow envisage as three dimensions, stable, compressible, viscose, agitated with radiation in combustion.in order to the modeling the combustion process were used the non-premixed combustion model with liquid fuel. After that the fluent software 16.1, the injection and evaporation of the fuel were modeled. The results were compared to the actual results of the SOLAR T62T-2A which were introduced by the manufacturer. For fuel flows less than 0.0125 kilograms per second, increasing inlet air temperature for the compressor causes increase of power but higher fuel flows from it causes a reduction in power.
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دوره 8، شماره 2 - شماره پیاپی 2
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اغنیا, مهدی, & اعلایی, محمد. (1398). بررسی اثر پارامترهای جریان بر توان خروجی میکروتوربین واحد توان کمکی بالگرد. دانش و فناوری هوافضا, 8(2), 243-255.
مهدی اغنیا; محمد اعلایی. "بررسی اثر پارامترهای جریان بر توان خروجی میکروتوربین واحد توان کمکی بالگرد". دانش و فناوری هوافضا, 8, 2, 1398, 243-255.
اغنیا, مهدی, اعلایی, محمد. (1398). 'بررسی اثر پارامترهای جریان بر توان خروجی میکروتوربین واحد توان کمکی بالگرد', دانش و فناوری هوافضا, 8(2), pp. 243-255.
اغنیا, مهدی, اعلایی, محمد. بررسی اثر پارامترهای جریان بر توان خروجی میکروتوربین واحد توان کمکی بالگرد. دانش و فناوری هوافضا, 1398; 8(2): 243-255.