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Part of a CF6-80C2 turbofan engine, owned by Garuda Indonesia, which frequently gets damaged and causes an unscheduled engine removal is turbine blade stage I. Based on failure analysis from the metallurgical viewpoint on the turbine which ruptured, it was reported that the failure happens due to cr...

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Main Author: SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR
Format: Final Project
Language:Indonesia
Online Access:https://digilib.itb.ac.id/gdl/view/17231
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Institution: Institut Teknologi Bandung
Language: Indonesia
id id-itb.:17231
spelling id-itb.:172312017-10-09T10:33:27Z#TITLE_ALTERNATIVE# SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR Indonesia Final Project INSTITUT TEKNOLOGI BANDUNG https://digilib.itb.ac.id/gdl/view/17231 Part of a CF6-80C2 turbofan engine, owned by Garuda Indonesia, which frequently gets damaged and causes an unscheduled engine removal is turbine blade stage I. Based on failure analysis from the metallurgical viewpoint on the turbine which ruptured, it was reported that the failure happens due to crack propagation. Crack initiation was started in the surface of internal cavities due to structure degradation which is caused by a high temperature operational environment. It is assumed that the initial crack appears from inside the turbine blade because it has a higher stress than the other parts of the turbine blade. <br /> <br /> <br /> <br /> <br /> Stress analysis on the CF6-80C2 turbine blade structure is performed by using element method and Abaqus software. The applied load are static loads (centrifugal, aerodinamics, and thermal stress) in a steady condition. Metallography was carried out for detecting cracks on a blade which has not suffered rupture failure. It is consists of blade cutting, mounting, grinding, polishing and examination using stereo microscope. <br /> <br /> <br /> <br /> <br /> The result of the stress analysis shows that the highest stress occur in the internal cavities. Tensile stress occurs in the outer airfoil surface, while compressive stress occurs in the internal cavities regiom. It means that the coating surface on the internal cavities surface is more prone to damage. The result of metallography shown that the crack initiation comes from inside the turbine blade. The crack is difficult to be detected by a boroscope inspection during overhaul, so it needs new methods that could detect the crack. One of those which can be done is by doing the radiography inspection. However, radiography is not discussed further in this study and needs to perform in the next study. text
institution Institut Teknologi Bandung
building Institut Teknologi Bandung Library
continent Asia
country Indonesia
Indonesia
content_provider Institut Teknologi Bandung
collection Digital ITB
language Indonesia
description Part of a CF6-80C2 turbofan engine, owned by Garuda Indonesia, which frequently gets damaged and causes an unscheduled engine removal is turbine blade stage I. Based on failure analysis from the metallurgical viewpoint on the turbine which ruptured, it was reported that the failure happens due to crack propagation. Crack initiation was started in the surface of internal cavities due to structure degradation which is caused by a high temperature operational environment. It is assumed that the initial crack appears from inside the turbine blade because it has a higher stress than the other parts of the turbine blade. <br /> <br /> <br /> <br /> <br /> Stress analysis on the CF6-80C2 turbine blade structure is performed by using element method and Abaqus software. The applied load are static loads (centrifugal, aerodinamics, and thermal stress) in a steady condition. Metallography was carried out for detecting cracks on a blade which has not suffered rupture failure. It is consists of blade cutting, mounting, grinding, polishing and examination using stereo microscope. <br /> <br /> <br /> <br /> <br /> The result of the stress analysis shows that the highest stress occur in the internal cavities. Tensile stress occurs in the outer airfoil surface, while compressive stress occurs in the internal cavities regiom. It means that the coating surface on the internal cavities surface is more prone to damage. The result of metallography shown that the crack initiation comes from inside the turbine blade. The crack is difficult to be detected by a boroscope inspection during overhaul, so it needs new methods that could detect the crack. One of those which can be done is by doing the radiography inspection. However, radiography is not discussed further in this study and needs to perform in the next study.
format Final Project
author SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR
spellingShingle SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR
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author_facet SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR
author_sort SASAKAWA ISKANDAR (NIM: 13607048); Pembimbing: Dr. Hendri Syamsudin; Dr. Eng. Arif Sugiant, SILUR
title #TITLE_ALTERNATIVE#
title_short #TITLE_ALTERNATIVE#
title_full #TITLE_ALTERNATIVE#
title_fullStr #TITLE_ALTERNATIVE#
title_full_unstemmed #TITLE_ALTERNATIVE#
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url https://digilib.itb.ac.id/gdl/view/17231
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