شبيه سازي عددي اثر لقي نوك پره بر عملكرد كمپرسور جريان محوري

Numerical simulation of the effect of tip clearance on axial flow compressor performance

در اين مقاله با استفاده از شبيه سازي عددي به اثرات لقي نوك پره روتور 37 ناسا بر عملكرد كمپرسور جريان محوري و پارامترهاي موثر، نمودار عملكرد و بازدهي كمپرسور در محدوده عملياتي كمپرسور پرداخته شده است. در اين مقاله علاوه بر لقي استاندارد مربوط به طراحي پره اثرات مربوط به افزايش و كاهش اندازه لقي نوك پره نيز مورد بررسي قرار گرفت. براي حل عددي از حالت پايدار ،تراكم پذير و براي شبيه سازي آشفتگي جريان از مدل توربولانسي k-ε استفاده گرديد. به منظور اعتبار سنجي استقلال حل عددي از مش از معيار شاخص همگرايي شبكه(GCI) استفاده شد.

In this paper, using numerical simulations of the Tip Clearance Size Effect of NASA Rotor 37 Blade on Axial Flow Compressor Performance and effective parameters, compressor performance and efficiency in the operating range of compressors are discussed. In this paper, In addition to the Standard design tip clearance the effect of increases and decreases the size of the tip clearance were also studied. For the numerical solution from steady state, compressibility and to simulate turbulent flow k-ε turbulence model was used. In order to validate Independence numerical mesh from the Grid Convergence Index criteria (GCI) was used. To validate numerical simulations performed in this study, the results of numerical solution were compared with experimental data. Results indicates well Tip Clearance Size Effect On efficiency, power and axial compressor overall performance.Reduce the maximum pressure in the proportion of 0.35%, 0.47% decline in yield and a 0.2% reduction in the power output of the compressor results tip clearance is 0.8.