Fig. 13From: Static fracture and modal analysis simulation of a gas turbine compressor blade and bladed disk system a First bending mode localized around blade with crack depth \(=\) 8Â mm. b Second bending mode localized around blade with crack depth \(=\) 8Â mm. c First torsional mode localized around blade with crack depth \(=\) 8Â mmBack to article page