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Methods and systems for assessing residual life of turbomachine airfoils

US9103741B2 · US · B2

Patent metadata
FieldValue
Publication numberUS-9103741-B2
Application numberUS-86982210-A
CountryUS
Kind codeB2
Filing dateAug 27, 2010
Priority dateAug 27, 2010
Publication dateAug 11, 2015
Grant dateAug 11, 2015

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  1. Title

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  2. Abstract

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  5. First independent claim

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Abstract

Official abstract text for this publication.

Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Processing the cracked airfoil finite element model includes accessing the cracked airfoil finite element model, computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis, and computing a vibratory SIF based, at least in part, on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.

First claim

Opening claim text (preview).

The invention claimed is: 1. A method comprising: receiving, at a processing system, at least one vibration response parameter associated with an airfoil, wherein the at least one vibration response parameter comprises at least one of an airfoil excitation frequency, an airfoil vibration amplitude, and an airfoil structural damping; using the processing system for: computing a modal stress intensity factor (SIF) of at least one cracked airfoil finite element model using fractu…

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What does patent US9103741B2 cover?
Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element mod…
Who is the assignee on this patent?
Baik Sanghum, Badami Vivek Venugopal, Potdar Yogesh Kesrinath, and 3 more
What technology area does this patent fall under?
Primary CPC classification G01M5/0016. Mapped technology areas include Physics.
When was this patent published?
Publication date Tue Aug 11 2015 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
What related patents are in patentsdb?
We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).