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Crack-Detection Experiments on Simulated Turbine Engine Disks in NASA Glenn Research Center's Rotordynamics LaboratoryThe development of new health-monitoring techniques requires the use of theoretical and experimental tools to allow new concepts to be demonstrated and validated prior to use on more complicated and expensive engine hardware. In order to meet this need, significant upgrades were made to NASA Glenn Research Center s Rotordynamics Laboratory and a series of tests were conducted on simulated turbine engine disks as a means of demonstrating potential crack-detection techniques. The Rotordynamics Laboratory consists of a high-precision spin rig that can rotate subscale engine disks at speeds up to 12,000 rpm. The crack-detection experiment involved introducing a notch on a subscale engine disk and measuring its vibration response using externally mounted blade-tip-clearance sensors as the disk was operated at speeds up to 12 000 rpm. Testing was accomplished on both a clean baseline disk and a disk with an artificial crack: a 50.8-mm- (2-in.-) long introduced notch. The disk s vibration responses were compared and evaluated against theoretical models to investigate how successful the technique was in detecting cracks. This paper presents the capabilities of the Rotordynamics Laboratory, the baseline theory and experimental setup for the crack-detection experiments, and the associated results from the latest test campaign.
Document ID
Document Type
Technical Memorandum (TM)
Woike, Mark R.
(NASA Glenn Research Center Cleveland, OH, United States)
Abdul-Aziz, Ali
(Cleveland State Univ. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
March 1, 2010
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2010-587
Meeting Information
Meeting: 48th Aerospace Sciences Meeting
Location: Orlando, FL
Country: United States
Start Date: January 4, 2010
End Date: January 7, 2010
Funding Number(s)
WBS: WBS 645546 .
Distribution Limits
Public Use Permitted.
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