Blade loss transient dynamic analysis of turbomachineryThis paper reports on work completed to develop an analytical method for predicting the transient non-linear response of a complete aircraft engine system due to the loss of a fan blade, and to validate the analysis by comparing the results against actual blade loss test data. The solution, which is based on the component element method, accounts for rotor-to-casing rubs, high damping and rapid deceleration rates associated with the blade loss event. A comparison of test results and predicted response show good agreement except for an initial overshoot spike not observed in test. The method is effective for analysis of large systems.
Document ID
19820051447
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stallone, M. J. (General Electric Co. Cincinnati, OH, United States)
Gallardo, V. (General Electric Co. Cincinnati, OH, United States)
Storace, A. F. (General Electric Co. Cincinnati, OH, United States)
Bach, L. J. (General Electric Co. Cincinnati, OH, United States)
Black, G. (General Electric Co. Cincinnati, OH, United States)
Gaffney, E. F. (General Electric Co. Cincinnati, OH, United States)