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Simulation of Aircraft Engine Blade-Out Structural DynamicsA primary concern of aircraft structure designers is the accurate simulation of the blade-out event and the subsequent windmilling of the engine. Reliable simulations of the blade-out event are required to insure structural integrity during flight as well as to guarantee successful blade-out certification testing. The system simulation includes the lost blade loadings and the interactions between the rotating turbomachinery and the remaining aircraft structural components. General-purpose finite element structural analysis codes such as MSC NASTRAN are typically used and special provisions are made to include transient effects from the blade loss and rotational effects resulting from the engine's turbomachinery. The present study provides the equations of motion for rotordynamic response including the effect of spooldown speed and rotor unbalance and examines the effects of these terms on a cantilevered rotor. The effect of spooldown speed is found to be greater with increasing spooldown rate. The parametric term resulting from the mass unbalance has a more significant effect on the rotordynamic response than does the spooldown term. The parametric term affects both the peak amplitudes as well as the resonant frequencies of the rotor.
Document ID
20020008015
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Lawrence, Charles (NASA Glenn Research Center Cleveland, OH United States)
Carney, Kelly (NASA Glenn Research Center Cleveland, OH United States)
Gallardo, Vicente (Ohio Aerospace Inst. Brook Park, OH United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2001
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2001-210957/REV1
E-12812-1/REV1
NAS 1.15:210957/REV1
Meeting Information
Meeting: Worldwide Aerospace Conference and Technology Showcase
Location: Toulouse
Country: France
Start Date: September 24, 2001
End Date: September 26, 2001
Sponsors: MSC Software
Funding Number(s)
PROJECT: RTOP 708-24-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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