NUMERICAL INVESTIGATION OF THE INFLUENCE OF FRONT CAMBER ON THE STABILITY OF A COMPRESSOR AIRFOIL

• Main Author: Li, Rui
• Format: Others
• Published: UKnowledge 2005
• Subjects: Flutter|High Cycle Fatigue|Active Flutter Control
• Online Access: http://uknowledge.uky.edu/gradschool_theses/345; http://uknowledge.uky.edu/cgi/viewcontent.cgi?article=1348&context=gradschool_theses

With the advent of smart materials it is becoming possible to alter the structural characteristics of turbomachine airfoils. This change in structural characteristics can include, but is not limited to, changes in the shape (morphing) of the airfoil. Through changes in the airfoil shape, aerodynamic performance can be improved. Moreover, this technique has the potential to act as a flutter suppressant. In this investigation changes in the airfoil front camber while maintaining the airfoil thickness distribution are made to increase airfoil stability. The airfoil section is representative of current low aspect ratio fan blade tip sections. To assess the influence of the change in airfoil shape on stability the work-per-cycle was evaluated for torsion mode oscillations around the mid-chord at an inlet Mach number of 0.5 with an interblade phase angle of 180 degree Cchordal incidence angles of both 0 degree and 10 degree, and a reduced frequency of 0.4.