Failure investigation of 5th stage compressor rotor blade pertaining to an aeroengine

Madan, M and Bhuvana, R and Sujata, M and Venkataswamy, MA and Bhaumik, SK (2009) Failure investigation of 5th stage compressor rotor blade pertaining to an aeroengine. Project Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertaining to an aeroengine was forwarded to this laboratory for investigation. Examination revealed that the blade has failed by fatigue. The fatigue crack was found to have initiated on the concave surface at a height of about 15 mm from the blade root platform and approximately 4 mm from the trailing edge. After initiation, the crack has propagated progressively over about 60% of the cross section before culminating in final overload fracture. A part of the fracture surface towards the trailing edge had post fracture damages. The trailing edge available with the fractured blade was found to have rubbing marks with resultant deformation and material flow in a direction opposite to the direction of rotation. The rubbing was found to have occurred right up to the blade root. By examining the failed blade alone, it was not possible to establish unambiguously as to whether or not the rubbing had taken place prior to the fatigue crack initiation.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aeroengine;Compressor blade;Fatigue
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division
Depositing User: Ms. Alphones Mary
Date Deposited: 18 Jul 2011 11:48
Last Modified: 18 Jul 2011 11:48
URI: http://nal-ir.nal.res.in/id/eprint/9421

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