Experimental study for vibration effect on aerodynamic flow-through cascade blades of gas turbine.

This research has cared about studying the effect of vibration obtained by the rotor blade row of the turbine on the aerodynamics flow between the turbine blades. The research focuses on studying the pressure distribution and velocity profile between blades turbine with effect force vibration for a different frequency (3-33 Hz). By this study, the effect of vibration on the gas turbine performance. An experimental rig was created at the University of Babylon University /Iraq by the authors. The cascade blades examined in this work are a real part that is mainly collected from Hilla/Iraq gas turbine power station. The distribution pressure is examined by sensor pressure at 18 in the region of the blade and is divided into two groups the first group on the suction side of the blade and the second on the pressure side. The pressure in X-positions was calculated with a different frequency for the blade. In the middle of the chord, at the suction and pressure sides of the blade, compared to the numerical simulation, the experimental results show that there is an increase of 5%, a decrease of 6%, and an increase of 6% at level 6,21, and 36 mm, respectively, from the base. In addition, the increase in frequency leads to an increase in the pressure on the pressure and suction sides. The pressure distribution on both sides of the blade is affected by the shape of each blade section. Three sections of the blade are taken at different heights. [ABSTRACT FROM AUTHOR]