AN EXPERIMENTAL INVESTIGATION OF MULTIPLE MODE EXCITATION OF AN INTEGRALLY BLADED DISK

 
 
 
 

AN EXPERIMENTAL INVESTIGATION OF MULTIPLE MODE EXCITATION OF AN INTEGRALLY BLADED DISK

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Title: AN EXPERIMENTAL INVESTIGATION OF MULTIPLE MODE EXCITATION OF AN INTEGRALLY BLADED DISK
Author: Garafolo, Nicholas Gordon
Description: High cycle fatigue of jet aircraft engine turbomachinery components is a serious problem for aircraft engine designers. State-of-the-art compressor designs have reduced mechanical damping and increased unsteady aerodynamic interaction between blade rows. New manufacturing techniques have enabled the rotor to be comprised of an integrally bladed disk, called a blisk. Advanced compressor designs have blades with low aspect ratios, highly complex geometry and higher tip speeds. Inherent in the single disk stage designs is a reduction in mechanical damping; no longer do the connections of blade to disk offer a viable source of damping. Thus, it is important to accurately portray the structural response of the component in a laboratory environment. In an engine environment, a blade row is simultaneously excited from a number of sources. This multiple mode environment was simulated by the modification of the Traveling Wave test rig at the Turbine Engine Fatigue Facility of the Air Force Research Laboratory. The objective of the research presented herein is to measure response of the ADLARF fan rotor excited in a multiple mode environment. The ADLARF fan is significantly structurally mistuned through the replacement of two opposing metallic blades with composite blades done in a past experiment. In this substantially mistuned environment, the assumption of the linear superposition theory for these multiple mode excitations was validated through spatial discrete Fast Fourier transforms and a data point superposition. It has been shown that the response of a bladed disk depends on the engine order of the excitation. Showing the necessity for matching the spatial mode order of the response with that of the engine order of the excitation has provided valuable insight towards fatiguing a complete bladed disk in a laboratory setting.
Permanent Link: http://rave.ohiolink.edu/etdc/view?acc_num=akron1164047919
http://hdl.handle.net/2374.OX/3579
Date: 2006

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