Case 27: Failure of a First-Stage Compressor Blade in an Aircraft Engine
-
Published:2005
Abstract
This chapter discusses the failure of a first-stage compressor blade in an aircraft engine and explains how investigators determined that it was caused by fatigue, with a crack originating from corrosion pits that developed in the root transition region on the convex side of the airfoil.
Failure of a First-Stage Compressor Blade in an Aircraft Engine, Failure Analysis of Engineering Structures: Methodology and Case Histories, By V. Ramachandran, A.C. Raghuram, R.V. Krishnan, S.K. Bhaumik, ASM International, 2005, p 128–129, https://doi.org/10.31399/asm.tb.faesmch.t51270128
Download citation file:
Join ASM International
Being a member of the world’s largest association of materials professionals provides the benefits and resources you need to accomplish your personal and professional goals.
