Disk Crack Detection for Seeded Fault Engine Test

TITLE AND SUBTITLE:
Disk Crack Detection for Seeded Fault Engine Test

AUTHOR(S):
Huageng Luo, Hector Rodriguez, Darren Hallman, and Dennis Corbly

REPORT DATE:
May 2004

FUNDING NUMBERS:
WBS-22-728-30-03
NAS3-01135, Task 7

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
GE Global Research
1 Research Circle
Niskayuna, New York 12309

PERFORMING ORGANIZATION REPORT NUMBER:
E-14545

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Final Contractor Report

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA CR-2004-213069

SUPPLEMENTARY NOTES:
Huageng Luo, Hector Rodriguez, and Darren Hallman, GE Global Research, 1 Research Circle, Niskayuna, New York 12309; and Dennis Corbly, GE Aircraft Engines, 1 Neumann Way, Cincinnati, Ohio 45215-1988. Project Manager, David G. Lewicki, Structures and Acoustics Division, NASA Glenn Research Center, organization code 5950, 216-433-3970.

ABSTRACT:
Work was performed to develop and demonstrate vibration diagnostic techniques for the on-line detection of engine rotor disk cracks and other anomalies through a real engine test. An existing single-degree-of-freedom non-resonance-based vibration algorithm was extended to a multi-degree-of-freedom model. In addition, a resonance-based algorithm was also proposed for the case of one or more resonances. The algorithms were integrated into a diagnostic system using state-of-the-art commercial analysis equipment. The system required only non-rotating vibration signals, such as accelerometers and proximity probes, and the rotor shaft 1/rev signal to conduct the health monitoring. Before the engine test, the integrated system was tested in the laboratory by using a small rotor with controlled mass unbalances. The laboratory tests verified the system integration and both the non-resonance and the resonance-based algorithm implementations. In the engine test, the system concluded that after two weeks of cycling, the seeded fan disk flaw did not propagate to a large enough size to be detected by changes in the synchronous vibration. The unbalance induced by mass shifting during the start up and coast down was still the dominant response in the synchronous vibration.

SUBJECT TERMS:
Fault detection; Turbine wheels; Cracks; TF-41 engine

NUMBER OF PAGES:
53

PDF AVAILABLE FROM URL:
2004/CR-2004-213069.pdf ( 5,524 KB )
This page contains an Adobe® Acrobat® Reader PDF file. The PDF documents have been created to show thumbnails of each page. If the thumbnails do not display properly, download the file to the hard drive and view through Acrobat® Reader. You can download Acrobat® Reader for free.

A service of the NASA Glenn Research Center Logistics and Technical Information Division

Suggestions or questions about this site can be directed to:

NASA official: Technical Publications Manager, Sue.E.Butts@nasa.gov

Web curator: Caroline.A.Rist@grc.nasa.gov

Privacy Policy and Important Notices