Slide 1 CFMI PROPRIETARY INFORMATION Investigation • Initial metallurgical results – Fatigue initiation origin from inside mid cooling cavity, convex side, .420 inches from shank base – 14 additional blades in set have internal cracks at same location (found by borescope, confirmed by destructive evaluation) • Investigation task team formed – Review manufacturing records – Dimensionally inspect disk and blades – Inspect other blade sets (BS and destructive evaluation) – Review/refine analysis models – Crack propagation analysis – Material program on coating effects CFM56 3D Aero HPT Blade Shank Separation • CFM56-5B/2P engine experienced HPT blade failure – Fully contained IFSD – TSN/CSN 9027 / 8745 – Primary blade released in shank below platform – One additional blade failed in shank in tensile overload, remainder of blades failed at the airfoil root in tensile overload • Failed blade was a 2002M52P04 – ~29 P04 blade sets shipped in 5B/P fleet – No P04 blades in CFM56-7 fleet – Shank geometry common to all HPT aero 3D aero blades (P04, P05, P09, P11) Background Action Plan • Initial metallurgical results Complete • Review of manufacturing records Complete • Disk/blade geometry inspections Complete • 3D blade/disk analysis update Complete • Blade inspection cutups Ongoing • Crack propagation analysis* Feb 2001 • Define root cause March 2001 • Material testing program complete June 2001 • Define improvement June 2001 * Additional studies ongoing Radial cross section of shank Crack Location Fatigue Origin of Prime Blade Secondary damage (tensile overload) Primary Blade Failure CFM56 3D aero HPT blade has experienced a new failure mode in-service作者: 979199501 时间: 2011-4-12 00:18:23 标题: 回复 1# 航空 的帖子
CFM56-7B TRAINING MANUAL ENGINE FAN TRIM BALANCE作者: kinran 时间: 2011-6-4 23:44:52
