Investigation of first stage compressor rotor blade of an aeroengine
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
View Archive Info| Field | Value | |
| Title |
Investigation of first stage compressor rotor blade of an aeroengine
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| Creator |
Suresh Kumar, M
Madan, M Venkataswamy, MA Sujata, M Parameswara, MA Bhaumik, SK |
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| Subject |
Aeronautics (General)
Chemistry and Materials (General) |
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| Description |
The compressor rotor blade in question had failed by fatigue. There were two fatigue cracks in the airfoil of the blade: one in the longitudinal direction and the other, in the transverse direction of the blade airfoil. Analysis shows that a longitudinal crack had developed on the concave surface of the airfoil probably due to tip rubbing. It appears that once the tip clearance was established by wear, this crack had ceased to propagate. Subsequently, another fatigue crack had initiated on the existing longitudinal crack due to notch effect, which eventually propagated progressively through the blade thickness leading to fracture. The microstructure and the composition of the blade material conform to Ti-alloy of IMI 550 specification. No metallurgical and/or mechanical abnormalities were responsible for the fatigue crack initiation.
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| Publisher |
National Aerospace Laboratories
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| Date |
2005
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| Type |
Proj.Doc/Technical Report
NonPeerReviewed |
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| Identifier |
Suresh Kumar, M and Madan, M and Venkataswamy, MA and Sujata, M and Parameswara, MA and Bhaumik, SK (2005) Investigation of first stage compressor rotor blade of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.
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| Relation |
http://nal-ir.nal.res.in/9927/
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