Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine

This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several m...
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Autor*in:	J. Ngoret [verfasserIn] V. Kommula [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2019

Schlagwörter:	Inconel 713LC XRD XRF EDS-SEM

Übergeordnetes Werk:	In: Iranian Journal of Materials Science and Engineering - Iran University of Science & Technology, 2017, 16(2019), 1, Seite 49-60
Übergeordnetes Werk:	volume:16 ; year:2019 ; number:1 ; pages:49-60

Links:	Link aufrufen Link aufrufen Journal toc Journal toc

Katalog-ID:	DOAJ06418658X

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allfields	(DE-627)DOAJ06418658X (DE-599)DOAJ55c353f4c01f4d639bd1d36be55194d1 DE-627 ger DE-627 rakwb eng J. Ngoret verfasserin aut Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue. Inconel 713LC XRD XRF EDS-SEM Technology T V. Kommula verfasserin aut In Iranian Journal of Materials Science and Engineering Iran University of Science & Technology, 2017 16(2019), 1, Seite 49-60 (DE-627)101553595X 23833882 nnns volume:16 year:2019 number:1 pages:49-60 https://doaj.org/article/55c353f4c01f4d639bd1d36be55194d1 kostenfrei http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1 kostenfrei https://doaj.org/toc/1735-0808 Journal toc kostenfrei https://doaj.org/toc/2383-3882 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 16 2019 1 49-60
spelling	(DE-627)DOAJ06418658X (DE-599)DOAJ55c353f4c01f4d639bd1d36be55194d1 DE-627 ger DE-627 rakwb eng J. Ngoret verfasserin aut Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue. Inconel 713LC XRD XRF EDS-SEM Technology T V. Kommula verfasserin aut In Iranian Journal of Materials Science and Engineering Iran University of Science & Technology, 2017 16(2019), 1, Seite 49-60 (DE-627)101553595X 23833882 nnns volume:16 year:2019 number:1 pages:49-60 https://doaj.org/article/55c353f4c01f4d639bd1d36be55194d1 kostenfrei http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1 kostenfrei https://doaj.org/toc/1735-0808 Journal toc kostenfrei https://doaj.org/toc/2383-3882 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 16 2019 1 49-60
allfields_unstemmed	(DE-627)DOAJ06418658X (DE-599)DOAJ55c353f4c01f4d639bd1d36be55194d1 DE-627 ger DE-627 rakwb eng J. Ngoret verfasserin aut Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue. Inconel 713LC XRD XRF EDS-SEM Technology T V. Kommula verfasserin aut In Iranian Journal of Materials Science and Engineering Iran University of Science & Technology, 2017 16(2019), 1, Seite 49-60 (DE-627)101553595X 23833882 nnns volume:16 year:2019 number:1 pages:49-60 https://doaj.org/article/55c353f4c01f4d639bd1d36be55194d1 kostenfrei http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1 kostenfrei https://doaj.org/toc/1735-0808 Journal toc kostenfrei https://doaj.org/toc/2383-3882 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 16 2019 1 49-60
allfieldsGer	(DE-627)DOAJ06418658X (DE-599)DOAJ55c353f4c01f4d639bd1d36be55194d1 DE-627 ger DE-627 rakwb eng J. Ngoret verfasserin aut Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue. Inconel 713LC XRD XRF EDS-SEM Technology T V. Kommula verfasserin aut In Iranian Journal of Materials Science and Engineering Iran University of Science & Technology, 2017 16(2019), 1, Seite 49-60 (DE-627)101553595X 23833882 nnns volume:16 year:2019 number:1 pages:49-60 https://doaj.org/article/55c353f4c01f4d639bd1d36be55194d1 kostenfrei http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1 kostenfrei https://doaj.org/toc/1735-0808 Journal toc kostenfrei https://doaj.org/toc/2383-3882 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 16 2019 1 49-60
allfieldsSound	(DE-627)DOAJ06418658X (DE-599)DOAJ55c353f4c01f4d639bd1d36be55194d1 DE-627 ger DE-627 rakwb eng J. Ngoret verfasserin aut Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue. Inconel 713LC XRD XRF EDS-SEM Technology T V. Kommula verfasserin aut In Iranian Journal of Materials Science and Engineering Iran University of Science & Technology, 2017 16(2019), 1, Seite 49-60 (DE-627)101553595X 23833882 nnns volume:16 year:2019 number:1 pages:49-60 https://doaj.org/article/55c353f4c01f4d639bd1d36be55194d1 kostenfrei http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1 kostenfrei https://doaj.org/toc/1735-0808 Journal toc kostenfrei https://doaj.org/toc/2383-3882 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 16 2019 1 49-60
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Ngoret</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2019</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. 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author	J. Ngoret
spellingShingle	J. Ngoret misc Inconel 713LC misc XRD misc XRF misc EDS-SEM misc Technology misc T Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
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topic_title	Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine Inconel 713LC XRD XRF EDS-SEM
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title	Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
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title_full	Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
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title_sort	microstructural investigation into premature failure of compressor turbine (ct) blade material of high pressure (hp) pt6a-114a engine
title_auth	Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
abstract	This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue.
abstractGer	This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue.
abstract_unstemmed	This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) of the tips, airfoils, as well as the bases. It was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. The tips were more affected, followed by the airfoils and least at the bases. Impingement of heat from the combustors on the CT blades led to rapid graining and rafting with eventual cracking upon cooling. The results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. However, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the CT blades originated from creep and fatigue.
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title_short	Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
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Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine

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