Analysis of failed compressor stator blades of an aeroengine

Sujata, M and Bhaumik, SK (2003) Analysis of failed compressor stator blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for investigation. Examination revealed that both the blades failed by fatigue. The fatigue was of high cycle-low stress type. The fracture surface of blade-377 (Stage-I) was damaged due to rubbing of the mating fracture surfaces and therefore, the crack origin in the blade could not be determined. In blade-17 (Stage-II), the fatigue crack initiated at the hub (concave surface) at about 2 mm away from the fillet. Rough machining marks observed at the crack origin region appears to be the most probable reason for the fatigue crack initiation in this blade. Reworking also reduced the beneficial residual compressive stress to a great extent and thereby facilitated the fatigue crack initiation.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aeroengine;compressor stator blades;fatigue;machining marks
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division, Materials Science Division
Depositing User: Mrs Manoranjitha M D
Date Deposited: 14 Jul 2011 16:30
Last Modified: 14 Jul 2011 16:30

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