Paper Information

Journal:   MODARES MECHANICAL ENGINEERING   JANUARY 2017 , Volume 16 , Number 10 #F0070; Page(s) 218 To 228.
 
Paper: 

NUMERICAL STUDY OF MID-SPAN DAMPER EFFECT ON THE PATTERN OF FLOW AND OPERATION OF TRANSONIC COMPRESSOR BLADES

 
 
Author(s):  JALALIFAR MAHDI, GHADIRI DEHKORDI BEHZAD*, FALLAH SALEH
 
* DEPARTMENT OF MECHANICAL ENGINEERING, TARBIAT MODARES UNIVERSITY, TEHRAN, IRAN
 
Abstract: 

One of the important purposes of aero-engine high speed compressor design is to decrease compressor weight. In order to achieve this purpose, it is required to increase the capability of producing pressure in each individual stage of the compressor. The most common way is use of high pressure aspect ratio blades. These long and thin blades are exposed to serious vibrations in the high speed flow because of the aeroelastic instability. Mechanical designers link adjacent blades by using mid-span shroud (damper) to decrease the blades destructive vibrations. These dampers cause flow blockage and turbomachine performance loss. In this study, the effect of mid-span damper on turbomachine aerodynamic operation has been investigated. In the previous studies there was less focus on the effect of damper on blade shocks, trailing edge vortices and near stall condition. Both with and without midspan damper have been investigated and compared. On the other hand, the damper effect on the formation and behavior of shock induced separation has been investigated in each of the two cases. As a result isentropic efficiency is decreased. These dampers also cause 33% pressure on blades. To avoid this pressure loss, the blade length is increased by 2.7%. Turbulence due to presence of damper leads to the distortion of vortices pattern in training edge.

 
Keyword(s): TRANSONIC TURBOMACHINE, MID-SPAN DAMPER, SHOCK INDUCED SEPARATION, VORTEX PATTERN, NEAR STALL
 
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