IJE TRANSACTIONS A: Basics Vol. 29, No. 4 (April 2016) 554-562   

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B. S. Sikarwar, A. Bhadauria and P. Ranjan
( Received: January 26, 2016 – Accepted in Revised Form: April 14, 2016 )

Abstract    The objective of this work is to develop deep theoretical methods that are based on the solution of the integral boundary layer equations for investigating film cooling in liquid rocket engine. The integral model assumes that heat is transferred from hot free stream gas to the liquid film both by convection and radiation. The mass is transferred to the free srteam gas by the well-known blowing process. Downstream of the liquid film, the gas effectiveness is obtained by solving boundary layer integral equations. It incorporates a differential model for calorimeter mixing between liquid vapors in the boundary layer with the free stream gas entrained in the boundary layer. Comparisons with existing theoretical and experimental results indicate the film coating trends were well predicted by the present integral model proposed by us.


Keywords    Film, Cooling, Analytical, Heat transfer, Rocket, Model


چکیده    هدف از این کار، توسعه روش عمیق تئوری است که بر پایه راه حل معادلات لایه مرزی جدایی ناپذیر برای بررسی خنک کننده فیلم در موتور موشک مایع است. مدل انتگرال فرض می کند که گرما از جریان گاز داغ آزاد به فیلم مایع توسط همرفت و تابش منتقل شده است. جرم بوسیله فرایند دمش شناخته شده به جریان گاز آزاد منتقل شده است. در پایین دست فیلم مایع، اثربخشی گاز با حل معادلات انتگرال لایه مرزی به دست آمده است. آن یک مدل دیفرانسیل را برای اختلاط گرماسنج بین بخارات مایع در لایه مرزی با جریان گاز آزاد در لایه مرزی ترکیب می کند. مقایسه نتایج تجربی و تئوری موجود نشان می دهد که روند پوشش دهی فیلمی به خوبی توسط مدل انتگرالی حاضر پیشنهادی توسط ما پیش بینی شده بود.


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