Analysis of failed LPTR blades of an aeroengine

Suresh Kumar, M and Sujata, M and Madan, M and Venkataswamy, MA and Bhaumik, SK (2006) Analysis of failed LPTR blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore, India.

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The failed LPT rotor blade (No. XA9798-13) of an aeroengine K5 build 13 was analyzed. Fractographic study showed that the blade had failed by fatigue. The fatigue crack had initiated on the convex surface of the airfoil at a distance of about 3-4 mm from the blade root platform. After initiation, the crack had propagated progressively over about 80% of the blade cross section before culminating in final overload failure. The blade material and the coating thickness were found to conform to specification, and no metallurgical abnormalities were found responsible for the fatigue crack initiation. Analysis showed that the coating had developed cracks due to excessive bending of the blade and one of these cracks had then propagated by fatigue leading to the failure. A detailed analysis of the failure has been presented in this report. A few recommendations have also been suggested.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine;LPTR blade;Fatigue;Blade bending;Coating cracks
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Ms. Alphones Mary
Date Deposited: 27 Jul 2011 08:45
Last Modified: 27 Jul 2011 08:45

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