Creep Life Degradation and Microstructure Degeneration in a Low-Pressure Turbine Blade of a Military Aircraft Engine
Military aircraft engines operate under arduous environmental conditions with rapid throttle excursions as a part of its mission requirements. Life of an aircraft engine particularly of a military class is limited by the longevity of hot end components. Total technical life of a gas turbine componen...
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| Veröffentlicht in: | Journal of failure analysis and prevention 2017-06, Vol.17 (3), p.529-538 |
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| container_title | Journal of failure analysis and prevention |
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| creator | Sahoo, Benudhar Panigrahi, S. K. Satpathy, R. K. |
| description | Military aircraft engines operate under arduous environmental conditions with rapid throttle excursions as a part of its mission requirements. Life of an aircraft engine particularly of a military class is limited by the longevity of hot end components. Total technical life of a gas turbine component is dictated by the bulk properties while time between overhaul is decided by the aero-thermal degradation which in turn is influenced by the surface protective coating. In the present research, stress rupture tests were carried out to evaluate the creep life of blades while swelling of the coating and secondary reaction zone (SRZ) were evaluated to assess the coating damage. Further, an investigation was made to assess the degradation in creep life and microstructure degeneration during the service period when turbine blades made of wrought nickel-based alloy is provided with aluminide coating. Minimum creep rate and time to rupture are used as the characteristic parameters to evaluate the degradation in creep life. Coarsening of gamma prime (
γ
′) and degeneration of carbides was evaluated for microstructure degeneration in the bulk material. Degradation in coating life was evaluated by volume fraction of β-phase and development of SRZ in the coating. |
| doi_str_mv | 10.1007/s11668-017-0271-x |
| format | Article |
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γ
′) and degeneration of carbides was evaluated for microstructure degeneration in the bulk material. Degradation in coating life was evaluated by volume fraction of β-phase and development of SRZ in the coating.</description><identifier>ISSN: 1547-7029</identifier><identifier>EISSN: 1728-5674</identifier><identifier>EISSN: 1864-1245</identifier><identifier>DOI: 10.1007/s11668-017-0271-x</identifier><language>eng</language><publisher>New York: Springer US</publisher><subject>Aerospace engines ; Aging aircraft ; Aircraft components ; Aircraft engines ; Airplane engines ; Alloys ; Aluminides ; Carbides ; Characterization and Evaluation of Materials ; Chemistry and Materials Science ; Classical Mechanics ; Coarsening ; Corrosion and Coatings ; Creep life ; Creep rate ; Damage assessment ; Degeneration ; Degradation ; Gamma-prime phase (crystals) ; Intermetallic compounds ; Materials Science ; Microstructure ; Military aircraft ; Military aviation ; Nickel base alloys ; Protective coatings ; Quality Control ; Reliability ; Safety and Risk ; Solid Mechanics ; Stresses ; Technical Article---Peer-Reviewed ; Tribology ; Turbine blades</subject><ispartof>Journal of failure analysis and prevention, 2017-06, Vol.17 (3), p.529-538</ispartof><rights>ASM International 2017</rights><rights>Journal of Failure Analysis and Prevention is a copyright of Springer, 2017.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c316t-800bfea89102e61064d1f7cf26884dbfe804df690cef7f8a098adb86133293533</citedby><cites>FETCH-LOGICAL-c316t-800bfea89102e61064d1f7cf26884dbfe804df690cef7f8a098adb86133293533</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Sahoo, Benudhar</creatorcontrib><creatorcontrib>Panigrahi, S. K.</creatorcontrib><creatorcontrib>Satpathy, R. K.</creatorcontrib><title>Creep Life Degradation and Microstructure Degeneration in a Low-Pressure Turbine Blade of a Military Aircraft Engine</title><title>Journal of failure analysis and prevention</title><addtitle>J Fail. Anal. and Preven</addtitle><description>Military aircraft engines operate under arduous environmental conditions with rapid throttle excursions as a part of its mission requirements. Life of an aircraft engine particularly of a military class is limited by the longevity of hot end components. Total technical life of a gas turbine component is dictated by the bulk properties while time between overhaul is decided by the aero-thermal degradation which in turn is influenced by the surface protective coating. In the present research, stress rupture tests were carried out to evaluate the creep life of blades while swelling of the coating and secondary reaction zone (SRZ) were evaluated to assess the coating damage. Further, an investigation was made to assess the degradation in creep life and microstructure degeneration during the service period when turbine blades made of wrought nickel-based alloy is provided with aluminide coating. Minimum creep rate and time to rupture are used as the characteristic parameters to evaluate the degradation in creep life. Coarsening of gamma prime (
γ
′) and degeneration of carbides was evaluated for microstructure degeneration in the bulk material. Degradation in coating life was evaluated by volume fraction of β-phase and development of SRZ in the coating.</description><subject>Aerospace engines</subject><subject>Aging aircraft</subject><subject>Aircraft components</subject><subject>Aircraft engines</subject><subject>Airplane engines</subject><subject>Alloys</subject><subject>Aluminides</subject><subject>Carbides</subject><subject>Characterization and Evaluation of Materials</subject><subject>Chemistry and Materials Science</subject><subject>Classical Mechanics</subject><subject>Coarsening</subject><subject>Corrosion and Coatings</subject><subject>Creep life</subject><subject>Creep rate</subject><subject>Damage assessment</subject><subject>Degeneration</subject><subject>Degradation</subject><subject>Gamma-prime phase (crystals)</subject><subject>Intermetallic compounds</subject><subject>Materials Science</subject><subject>Microstructure</subject><subject>Military aircraft</subject><subject>Military aviation</subject><subject>Nickel base alloys</subject><subject>Protective coatings</subject><subject>Quality Control</subject><subject>Reliability</subject><subject>Safety and Risk</subject><subject>Solid Mechanics</subject><subject>Stresses</subject><subject>Technical Article---Peer-Reviewed</subject><subject>Tribology</subject><subject>Turbine blades</subject><issn>1547-7029</issn><issn>1728-5674</issn><issn>1864-1245</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2017</creationdate><recordtype>article</recordtype><sourceid>AFKRA</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><recordid>eNp1kMtOwzAQRSMEEuXxAewssTbMxKntLEspDykVLMrachO7clWSYjui_D0OYcGGlS2dc8fjm2VXCDcIIG4DIueSAgoKuUB6OMomKHJJp1wUx-k-LQQVkJen2VkIWwA2xSKfZHHujdmTyllD7s3G60ZH17VEtw1Zutp3Ifq-jr3_waY1fuQuKaTqPumrNyEMeNX7tWsNudvpxpDOJr50Oxe1_yIz52uvbSSLdpOci-zE6l0wl7_nefb2sFjNn2j18vg8n1W0ZsgjlQBra7QsEXLDEXjRoBW1zbmURZOQhKKxvITaWGGlhlLqZi05MpaXbMrYeXY9zt377qM3Iapt1_s2PamwBC5RMIbJwtEafhu8sWrv3XtaWyGooVw1lqtSuWooVx1SJh8zIbntxvg_k_8NfQMPu31y</recordid><startdate>20170601</startdate><enddate>20170601</enddate><creator>Sahoo, Benudhar</creator><creator>Panigrahi, S. 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K.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c316t-800bfea89102e61064d1f7cf26884dbfe804df690cef7f8a098adb86133293533</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2017</creationdate><topic>Aerospace engines</topic><topic>Aging aircraft</topic><topic>Aircraft components</topic><topic>Aircraft engines</topic><topic>Airplane engines</topic><topic>Alloys</topic><topic>Aluminides</topic><topic>Carbides</topic><topic>Characterization and Evaluation of Materials</topic><topic>Chemistry and Materials Science</topic><topic>Classical Mechanics</topic><topic>Coarsening</topic><topic>Corrosion and Coatings</topic><topic>Creep life</topic><topic>Creep rate</topic><topic>Damage assessment</topic><topic>Degeneration</topic><topic>Degradation</topic><topic>Gamma-prime phase (crystals)</topic><topic>Intermetallic compounds</topic><topic>Materials Science</topic><topic>Microstructure</topic><topic>Military aircraft</topic><topic>Military aviation</topic><topic>Nickel base alloys</topic><topic>Protective coatings</topic><topic>Quality Control</topic><topic>Reliability</topic><topic>Safety and Risk</topic><topic>Solid Mechanics</topic><topic>Stresses</topic><topic>Technical Article---Peer-Reviewed</topic><topic>Tribology</topic><topic>Turbine blades</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Sahoo, Benudhar</creatorcontrib><creatorcontrib>Panigrahi, S. 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Total technical life of a gas turbine component is dictated by the bulk properties while time between overhaul is decided by the aero-thermal degradation which in turn is influenced by the surface protective coating. In the present research, stress rupture tests were carried out to evaluate the creep life of blades while swelling of the coating and secondary reaction zone (SRZ) were evaluated to assess the coating damage. Further, an investigation was made to assess the degradation in creep life and microstructure degeneration during the service period when turbine blades made of wrought nickel-based alloy is provided with aluminide coating. Minimum creep rate and time to rupture are used as the characteristic parameters to evaluate the degradation in creep life. Coarsening of gamma prime (
γ
′) and degeneration of carbides was evaluated for microstructure degeneration in the bulk material. Degradation in coating life was evaluated by volume fraction of β-phase and development of SRZ in the coating.</abstract><cop>New York</cop><pub>Springer US</pub><doi>10.1007/s11668-017-0271-x</doi><tpages>10</tpages></addata></record> |
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| subjects | Aerospace engines Aging aircraft Aircraft components Aircraft engines Airplane engines Alloys Aluminides Carbides Characterization and Evaluation of Materials Chemistry and Materials Science Classical Mechanics Coarsening Corrosion and Coatings Creep life Creep rate Damage assessment Degeneration Degradation Gamma-prime phase (crystals) Intermetallic compounds Materials Science Microstructure Military aircraft Military aviation Nickel base alloys Protective coatings Quality Control Reliability Safety and Risk Solid Mechanics Stresses Technical Article---Peer-Reviewed Tribology Turbine blades |
| title | Creep Life Degradation and Microstructure Degeneration in a Low-Pressure Turbine Blade of a Military Aircraft Engine |
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