The Effect Of Number Of Blades On Compressor Cascade Bladesperformance By Using 3D CFD

Azli, Siti Nurazeera (2017) The Effect Of Number Of Blades On Compressor Cascade Bladesperformance By Using 3D CFD. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

A compressor is one of the mechanical devices in gas turbine engine that compresses air to increases its pressure as well as changing its temperature. In order to design the efficient gas turbine engine, high efficiency of engine is required. Smoothness of airflow in gas turbine has an impact on engine performance. Compressor efficiency is one of the parameter should be considered to maintain that airflow. Hence, compressor blade design was play important role to obtain high efficiency of compressor. A computational investigation has been carried out on the effect of number of blade on 3-Dimensional of compressor cascade blade performance. In order to design the good performance of compressor cascade blade, higher efficiency of cascade is required. It is give benefit to the compressor efficiency, hence produce the efficient turbomachine. The study of flow field is analyzed with help of Computational Fluid Dynamics using the FLUENT software. The flow considered steady with inlet velocity of 30 m/s. NACA 65-206 chosen as blade profile with angle of attack of 10º. The compressor cascade blade is modelled by using SolidWorks software. The blade is twisted. The analysis has been made on different number of blade, namely 3, 5, 7 and 9 with fixed geometry and parameter. The performance of compressor cascade blade have been shown in results of pressure distribution, velocity profile, lift and drag coefficient, pressure different and cascade efficiency. The results have been shown in 2-Dimensional taken at four ratio of position plane. The pattern of velocity profile around the cascade blade and pressure distribution on the surface of cascade blade followed the Bernoulli’s principle stated that the velocity on the suction side of airfoil higher than pressure side of airfoil. The acceleration of air creates the lower pressure system and vice versa. Thus, the pattern of pressure distribution is inversely to the velocity profile of cascade blade. Nine blade of compressor have the higher pressure different of inlet and outlet between the blade passages with value of 5.7095 Pa. In order to design the compressor cascade blade, maximum lift and minimize drag should be considered. As result of the effect of number of blade to the lift and drag, it is showed that lift coefficient is higher that drag coefficient for various number of blades. However, five blades of compressor have better result of efficiency of cascade and lift to drag ratio with 75% and 7.857, respectively. It is shown that the five blades of compressor have the best performance compared to the other number of blades.

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