Abstract
The effects of blade-to-blade variations in the damping coefficients on the forced response of a bladed disk are investigated. It is found that this nonuniformity of the disk can lead to variations in the blades' amplitudes of response which are similar, in magnitude, to those obtained with stiffness mistuning but are potentially more dangerous because of the skewness of the distribution toward large amplitudes. The influence of various structural parameters on the scatter of blade amplitudes is also studied. Finally, the adequacy of the combined Closed-Form Perturbation (CFP) method is demonstrated by comparison with simulation results.
Original language | English (US) |
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Title of host publication | American Society of Mechanical Engineers (Paper) |
Publisher | Publ by ASME |
State | Published - 1993 |
Event | International Gas Turbine and Aeroengine Congress and Exposition - Cincinnati, OH, USA Duration: May 24 1993 → May 27 1993 |
Other
Other | International Gas Turbine and Aeroengine Congress and Exposition |
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City | Cincinnati, OH, USA |
Period | 5/24/93 → 5/27/93 |
ASJC Scopus subject areas
- Mechanical Engineering