Finite element design study of a bladed, flat rotating disk to simulate cracking in a typical turbine disk

Ali Abdul-Aziz; Jeffrey J. Trudell; George Y. Baaklini

doi:10.1117/12.601896

19 May 2005 Finite element design study of a bladed, flat rotating disk to simulate cracking in a typical turbine disk

Ali Abdul-Aziz, Jeffrey J. Trudell, George Y. Baaklini

Proceedings Volume 5767, Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure IV; (2005) https://doi.org/10.1117/12.601896
Event: Nondestructive Evaluation for Health Monitoring and Diagnostics, 2005, San Diego, CA, United States

Abstract

Developing health management and ultrasafe engine technologies are the primary goals of NASA's Aviation Safety Program. Besides improving safety, health monitoring can also reduce maintenance costs. A unique disk spin simulation system was assembled by the Nondestructive Evaluation (NDE) Group at NASA Glenn Research Center to verify and study a crack detection technique based upon observing center of mass changes of the rotor system using various sensing technologies. This paper describes the finite element analysis results of low cost, a 25.4 cm (10 in.) diameter, flat turbine disk used to evaluate the detection techniques by simulating typical cracks observed in turbine engine disks. Changes in radial tip displacement and center of mass are presented as a function of speed, crack size and location.

Citation Download Citation

Ali Abdul-Aziz, Jeffrey J. Trudell, and George Y. Baaklini "Finite element design study of a bladed, flat rotating disk to simulate cracking in a typical turbine disk", Proc. SPIE 5767, Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure IV, (19 May 2005); https://doi.org/10.1117/12.601896

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