In an attempt to increase jet engine efficiences, typically smaller rotor-stator-running clearances are being employed. Because of this and the ever present need to improve maintenance, reliability and structural integrity under various modes of operation, more sophisticated analyses tools are required to model the engine. Due to the wide-spread usage of general purpose finite element codes, this report seeks to adapt the procedure to use in modeling turbine rotor-bearing-stator structure. The work outlined in this report covers the second phase of work on a three-phase NASA Lewis sponsored research grant on engine dynamic simulation by developing strategies which enable the use of available finite element codes.

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