Failure analysis of two sets of aircraft blades

Engineering Failure Analysis

Volumn 17, Issue 3, 2010, Pages 641-647

  Silveira, E ^a   Atxaga, G ^a   Irisarri, A M ^a  

^a TECNALIA RESEARCH AND INNOVATION   (Spain)

Author keywords

Aircraft engines; Blades; Failure analysis; Methodology; Nickel base superalloys

Indexed keywords

FOREIGN-OBJECT DAMAGE; HIGH PRESSURE COMPRESSOR; HIGH PRESSURE TURBINE; NICKEL BASE SUPERALLOY; PREMATURE FAILURES; THERMOMECHANICAL FATIGUE;

AIRCRAFT; AIRCRAFT ENGINES; DEBRIS; FAILURE ANALYSIS; MICROSTRUCTURE; NICKEL; NICKEL ALLOYS; SAFETY FACTOR; SCANNING ELECTRON MICROSCOPY; SUPERALLOYS;

QUALITY ASSURANCE;

EID: 76049110820     PISSN: 13506307     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.engfailanal.2008.10.015     Document Type: Article

References (9)

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3. http://www.boeing.com.
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6. Nowell D., Duo P., and Stewart I.F. Prediction of fatigue performance in gas turbine blades after foreign object damage. Int J Fatigue 25 9-11 (2003) 963-969
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9. Anon. Metallurgy, processing and properties of superalloys, in heat resistant materials (1997), ASM International, Materials Park (OH) p. 221-54