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Blade loss transient dynamics analysis with flexible bladed diskThe transient dynamic response of a flexible bladed disk on a flexible rotor in a two rotor system is formulated by modal synthesis and a Lagrangian approach. Only the nonequilibrated one diameter flexible mode is considered for the flexible bladed disk, while the two flexible rotors are represented by their normal modes. The flexible bladed disk motion is modeled as a combination of two one diameter standing waves, and is coupled inertially and gyroscopically to the flexible rotors. Application to a two rotor model shows that a flexible bladed disk on one rotor can be driven into resonance by an unbalance in the other rotor, and at a frequency equal to the difference in the rotor speeds.
Document ID
19840005125
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gallardo, V. C.
(General Electric Co. Cincinnati, OH, United States)
Black, G.
(General Electric Co. Cincinnati, OH, United States)
Bach, L.
(General Electric Co. Cincinnati, OH, United States)
Cline, S.
(General Electric Co. Cincinnati, OH, United States)
Storace, A.
(General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-168176
NAS 1.26:168176
Report Number: NASA-CR-168176
Report Number: NAS 1.26:168176
Accession Number
84N13193
Funding Number(s)
CONTRACT_GRANT: NAS3-23281
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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