Abstract
Analysis of an aeroelastically unstable F100 labyrinth air seal has shown a stable design could be produced by tailoring the knife-edge lip clearance. An extensive engine experimental program confirmed that seals experienced high cycle fatigue (HCF) cracking resulting from clearance. Correlation has been demonstrated between analytically predicted instability and that observed during test engine operation. Experimental apparatus was developed to selectively augment or squelch the instability. These techniques improve definition of stability boundaries and provide a conservative means of substantiating stability margin with the revised configuration.
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