Abstract
This paper investigates the effects of random blade mistiming on the dynamics of an advanced gas turbine rotor. Both free and forced responses of the rotor are examined using the finite element method, and a computationally inexpensive reduced-order modeling technique based on component mode synthesis. The spatially extended free modes of vibration of the tuned rotor are found to undergo severe localization upon the introduction of blade mistuning. In turn, this results in dramatic displacement and stress amplitude increases in the forced response of individual blades. The mistuned forced response amplitude is found to vary considerably with mistuning strength and the degree of aerodynamic and disk structural coupling between the blades. The paper concludes with a statistical study in which Weibull distributions are used to calculate approximate forced response statistics.
Original language | English |
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DOIs | |
State | Published - 1996 |
Event | 32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States Duration: 1 Jul 1996 → 3 Jul 1996 |
Conference
Conference | 32nd Joint Propulsion Conference and Exhibit, 1996 |
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Country/Territory | United States |
City | Lake Buena Vista |
Period | 1/07/96 → 3/07/96 |