Investigation of HP Turbine Blade Failure in a Military Turbofan Engine

Failure of a high pressure (HP) turbine blade in a military turbofan engine is investigated to determine the root cause of failure. Forensic and metallurgical investigations are carried out on the affected blades. The loss of coating and the presence of heavily oxidized intergranular fracture featur...

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Bibliographic Details
Published inInternational journal of turbo & jet-engines Vol. 34; no. 1; pp. 23 - 31
Main Authors Mishra, R. K., Thomas, Johny, Srinivasan, K., Nandi, Vaishakhi, Bhatt, R. Raghavendra
Format Journal Article
LanguageEnglish
Published Berlin De Gruyter 01.01.2017
Walter de Gruyter GmbH
Subjects
62.20.mq
blade
Blades
Coating
coating spallation
curling
Failure
fractography
intergranular cracking
Military
Oxidation
Roots
Substrates
turbine
turbofan engine
Turbofan engines
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Summary:Failure of a high pressure (HP) turbine blade in a military turbofan engine is investigated to determine the root cause of failure. Forensic and metallurgical investigations are carried out on the affected blades. The loss of coating and the presence of heavily oxidized intergranular fracture features including substrate material aging and airfoil curling in the trailing edge of a representative blade indicate that the coating is not providing adequate oxidation protection and the blade material substrate is not suitable for the application at hand. Coating spallation followed by substrate oxidation and aging leading to intergranular cracking and localized trailing edge curling is the root cause of the blade failure. The remaining portion of the blade fracture surface showed ductile overload features in the final failure. The damage observed in downstream components is due to secondary effects.
Bibliography:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 23
ISSN:0334-0082
2191-0332
DOI:10.1515/tjj-2015-0049