This 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.
Blade loss transient dynamic analysis of turbomachinery
Joint Propulsion Conference ; 1982 ; Cleveland, OH
1982-06-01
Conference paper
No indication
English
Blade loss transient dynamic analysis of turbomachinery
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