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CSME 2020/08
Volume 41 No.4
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479-491
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Effect of Geometric Parameters of Part Span Damper on Aerodynamic Operation in a Transonic Turbomachine
Jalalifar Mahdi a, Fallah Saleh and Ghadiri Dehkordi Behzad a
aDepartment of Mechanical Engineering, Tarbiat Modares University (TMU), Tehran, Iran.
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Abstract:
Decreasing compressor weight is one of the important purposes of aero-engine high speed compressor design. A common way to achieve this is to increase the pressure producing capability of the individual stages. The usual method is to use of a high aspect ratio blade. These long and thin blades are exposed to severe vibrations in the high speed fluid flow because of the aeroelastic instability. In order to decrease these destructive vibrations, mechanical designers link adjacent blades by part span dampers. These dampers cause flow blockage and a loss in turbomachine’s performance. In this study, the effect of dampers on turbomachine aerodynamic operation is investigated. Nature of Flow is steady state until near stall, thus, simulations performed assume steady state conditions. In the previous studies, little attention has been given to the effect of dampers on blade shocks and trailing edge vortices. On the other hand, the damper effect on the formation and behavior of shock induced separation has been investigated in both cases. The results show that the presence of dampers cause a decrease in isentropic efficiency. Efficiency drops with reduction in the distance between damper’s leading edge and blade’s leading edge, increasing damper’s leading edge radius, and increasing damper thickness.
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Keywords: Transonic turbomachine, Part span damper, Shock induced separation, Vortex pattern.
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©
2020
CSME , ISSN 0257-9731
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