Evaluation of service-induced damage and restoration of cast turbine blades
Conventionally cast turbine blades of Inconel 713C, from a military gas turbine aircraft engine, have been investigated with regard to service-induced microstructural damage and residual creep life time. For cast turbine blades, service life is defined by statistical values. The statistical methods...
Gespeichert in:
| Veröffentlicht in: | Journal of materials engineering and performance 1993-08, Vol.2 (4), p.565-569 |
|---|---|
| Hauptverfasser: | , |
| Format: | Artikel |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | 569 |
|---|---|
| container_issue | 4 |
| container_start_page | 565 |
| container_title | Journal of materials engineering and performance |
| container_volume | 2 |
| creator | PERSSON, C PERSSON, P.-O |
| description | Conventionally cast turbine blades of Inconel 713C, from a military gas turbine aircraft engine, have been investigated with regard to service-induced microstructural damage and residual creep life time. For cast turbine blades, service life is defined by statistical values. The statistical methods can prove to be uneconomical, because safe limits must be stated with regard to the statistical probability that some blades will have higher damage than normal. An alternative approach is to determine the service-induced microstructural damage on each blade, or a representative number of blades, to better optimize blade usage. Ways to use service-induced [gamma][prime] rafting and void formation as quantified microstructural damage parameters in a service lifetime prediction model are suggested. The damage parameters were quantified, in blades with different service exposure levels, and correlated to remaining creep life evaluated from creep test specimens taken from different positions of serviced blades. Results from tests with different rejuvenation treatments, including hot isostatic pressing and/or heat treatment, are discussed briefly. |
| doi_str_mv | 10.1007/BF02661742 |
| format | Article |
| fullrecord | <record><control><sourceid>pascalfrancis_osti_</sourceid><recordid>TN_cdi_osti_scitechconnect_5307563</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>3815812</sourcerecordid><originalsourceid>FETCH-LOGICAL-c326t-a35466df9de38e2520d7d56f326f84087f5d0aefee72fd554b6a7947f3cb75b13</originalsourceid><addsrcrecordid>eNpF0E1Lw0AQBuBFFKzVi78giCchut-bHLW0Kha86DlMdmd1JU3K7rbgvzcSqacZmOedw0vIJaO3jFJz97CiXGtmJD8iM6akLBnl8njcqarLWtbqlJyl9EVHzLmckZflHrod5DD0xeCLhHEfLJahdzuLrnCwgQ8soHdFxJSHeJAWUi7yLrahx6LtwGE6JyceuoQXf3NO3lfLt8VTuX59fF7cr0sruM4lCCW1dr52KCrkilNnnNJ-PPpK0sp45SigRzTcO6Vkq8HU0nhhW6NaJubkavo7pByaZENG-2mHvkebGyWoUVqM6GZCNg4pRfTNNoYNxO-G0ea3q-a_qxFfT3gLyULnI_Q2pENCVExVjIsfP0VoFw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>article</recordtype></control><display><type>article</type><title>Evaluation of service-induced damage and restoration of cast turbine blades</title><source>SpringerLink Journals</source><creator>PERSSON, C ; PERSSON, P.-O</creator><creatorcontrib>PERSSON, C ; PERSSON, P.-O</creatorcontrib><description>Conventionally cast turbine blades of Inconel 713C, from a military gas turbine aircraft engine, have been investigated with regard to service-induced microstructural damage and residual creep life time. For cast turbine blades, service life is defined by statistical values. The statistical methods can prove to be uneconomical, because safe limits must be stated with regard to the statistical probability that some blades will have higher damage than normal. An alternative approach is to determine the service-induced microstructural damage on each blade, or a representative number of blades, to better optimize blade usage. Ways to use service-induced [gamma][prime] rafting and void formation as quantified microstructural damage parameters in a service lifetime prediction model are suggested. The damage parameters were quantified, in blades with different service exposure levels, and correlated to remaining creep life evaluated from creep test specimens taken from different positions of serviced blades. Results from tests with different rejuvenation treatments, including hot isostatic pressing and/or heat treatment, are discussed briefly.</description><identifier>ISSN: 1059-9495</identifier><identifier>EISSN: 1544-1024</identifier><identifier>DOI: 10.1007/BF02661742</identifier><language>eng</language><publisher>New York, NY: Springer</publisher><subject>330103 - Internal Combustion Engines- Turbine ; 360102 - Metals & Alloys- Structure & Phase Studies ; 360103 - Metals & Alloys- Mechanical Properties ; ADVANCED PROPULSION SYSTEMS ; Aircraft industry. Spacecraft ; AIRFOILS ; ALLOY-NI53CR19FE19NB5MO3 ; ALLOYS ; ALUMINIUM ADDITIONS ; ALUMINIUM ALLOYS ; Applications ; Applied sciences ; CHROMIUM ALLOYS ; CORROSION RESISTANT ALLOYS ; CREEP ; DATA ; Engineering techniques in metallurgy. Applications. Other aspects ; ENGINES ; Exact sciences and technology ; EXPERIMENTAL DATA ; GAS TURBINE ENGINES ; HEAT ENGINES ; HEAT RESISTANT MATERIALS ; HEAT RESISTING ALLOYS ; INCONEL 718 ; INCONEL ALLOYS ; INFORMATION ; INTERNAL COMBUSTION ENGINES ; IRON ALLOYS ; LIFETIME ; MATERIALS ; MATERIALS SCIENCE ; MECHANICAL PROPERTIES ; Metals. Metallurgy ; MICROSTRUCTURE ; MOLYBDENUM ALLOYS ; NICKEL ALLOYS ; NICKEL BASE ALLOYS ; NIOBIUM A ; NUMERICAL DATA ; SERVICE LIFE ; TURBINE BLADES</subject><ispartof>Journal of materials engineering and performance, 1993-08, Vol.2 (4), p.565-569</ispartof><rights>1994 INIST-CNRS</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c326t-a35466df9de38e2520d7d56f326f84087f5d0aefee72fd554b6a7947f3cb75b13</citedby><cites>FETCH-LOGICAL-c326t-a35466df9de38e2520d7d56f326f84087f5d0aefee72fd554b6a7947f3cb75b13</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,309,310,314,777,781,786,787,882,23911,23912,25121,27905,27906</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=3815812$$DView record in Pascal Francis$$Hfree_for_read</backlink><backlink>$$Uhttps://www.osti.gov/biblio/5307563$$D View this record in Osti.gov$$Hfree_for_read</backlink></links><search><creatorcontrib>PERSSON, C</creatorcontrib><creatorcontrib>PERSSON, P.-O</creatorcontrib><title>Evaluation of service-induced damage and restoration of cast turbine blades</title><title>Journal of materials engineering and performance</title><description>Conventionally cast turbine blades of Inconel 713C, from a military gas turbine aircraft engine, have been investigated with regard to service-induced microstructural damage and residual creep life time. For cast turbine blades, service life is defined by statistical values. The statistical methods can prove to be uneconomical, because safe limits must be stated with regard to the statistical probability that some blades will have higher damage than normal. An alternative approach is to determine the service-induced microstructural damage on each blade, or a representative number of blades, to better optimize blade usage. Ways to use service-induced [gamma][prime] rafting and void formation as quantified microstructural damage parameters in a service lifetime prediction model are suggested. The damage parameters were quantified, in blades with different service exposure levels, and correlated to remaining creep life evaluated from creep test specimens taken from different positions of serviced blades. Results from tests with different rejuvenation treatments, including hot isostatic pressing and/or heat treatment, are discussed briefly.</description><subject>330103 - Internal Combustion Engines- Turbine</subject><subject>360102 - Metals & Alloys- Structure & Phase Studies</subject><subject>360103 - Metals & Alloys- Mechanical Properties</subject><subject>ADVANCED PROPULSION SYSTEMS</subject><subject>Aircraft industry. Spacecraft</subject><subject>AIRFOILS</subject><subject>ALLOY-NI53CR19FE19NB5MO3</subject><subject>ALLOYS</subject><subject>ALUMINIUM ADDITIONS</subject><subject>ALUMINIUM ALLOYS</subject><subject>Applications</subject><subject>Applied sciences</subject><subject>CHROMIUM ALLOYS</subject><subject>CORROSION RESISTANT ALLOYS</subject><subject>CREEP</subject><subject>DATA</subject><subject>Engineering techniques in metallurgy. Applications. Other aspects</subject><subject>ENGINES</subject><subject>Exact sciences and technology</subject><subject>EXPERIMENTAL DATA</subject><subject>GAS TURBINE ENGINES</subject><subject>HEAT ENGINES</subject><subject>HEAT RESISTANT MATERIALS</subject><subject>HEAT RESISTING ALLOYS</subject><subject>INCONEL 718</subject><subject>INCONEL ALLOYS</subject><subject>INFORMATION</subject><subject>INTERNAL COMBUSTION ENGINES</subject><subject>IRON ALLOYS</subject><subject>LIFETIME</subject><subject>MATERIALS</subject><subject>MATERIALS SCIENCE</subject><subject>MECHANICAL PROPERTIES</subject><subject>Metals. Metallurgy</subject><subject>MICROSTRUCTURE</subject><subject>MOLYBDENUM ALLOYS</subject><subject>NICKEL ALLOYS</subject><subject>NICKEL BASE ALLOYS</subject><subject>NIOBIUM A</subject><subject>NUMERICAL DATA</subject><subject>SERVICE LIFE</subject><subject>TURBINE BLADES</subject><issn>1059-9495</issn><issn>1544-1024</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1993</creationdate><recordtype>article</recordtype><recordid>eNpF0E1Lw0AQBuBFFKzVi78giCchut-bHLW0Kha86DlMdmd1JU3K7rbgvzcSqacZmOedw0vIJaO3jFJz97CiXGtmJD8iM6akLBnl8njcqarLWtbqlJyl9EVHzLmckZflHrod5DD0xeCLhHEfLJahdzuLrnCwgQ8soHdFxJSHeJAWUi7yLrahx6LtwGE6JyceuoQXf3NO3lfLt8VTuX59fF7cr0sruM4lCCW1dr52KCrkilNnnNJ-PPpK0sp45SigRzTcO6Vkq8HU0nhhW6NaJubkavo7pByaZENG-2mHvkebGyWoUVqM6GZCNg4pRfTNNoYNxO-G0ea3q-a_qxFfT3gLyULnI_Q2pENCVExVjIsfP0VoFw</recordid><startdate>19930801</startdate><enddate>19930801</enddate><creator>PERSSON, C</creator><creator>PERSSON, P.-O</creator><general>Springer</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>OTOTI</scope></search><sort><creationdate>19930801</creationdate><title>Evaluation of service-induced damage and restoration of cast turbine blades</title><author>PERSSON, C ; PERSSON, P.-O</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c326t-a35466df9de38e2520d7d56f326f84087f5d0aefee72fd554b6a7947f3cb75b13</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1993</creationdate><topic>330103 - Internal Combustion Engines- Turbine</topic><topic>360102 - Metals & Alloys- Structure & Phase Studies</topic><topic>360103 - Metals & Alloys- Mechanical Properties</topic><topic>ADVANCED PROPULSION SYSTEMS</topic><topic>Aircraft industry. Spacecraft</topic><topic>AIRFOILS</topic><topic>ALLOY-NI53CR19FE19NB5MO3</topic><topic>ALLOYS</topic><topic>ALUMINIUM ADDITIONS</topic><topic>ALUMINIUM ALLOYS</topic><topic>Applications</topic><topic>Applied sciences</topic><topic>CHROMIUM ALLOYS</topic><topic>CORROSION RESISTANT ALLOYS</topic><topic>CREEP</topic><topic>DATA</topic><topic>Engineering techniques in metallurgy. Applications. Other aspects</topic><topic>ENGINES</topic><topic>Exact sciences and technology</topic><topic>EXPERIMENTAL DATA</topic><topic>GAS TURBINE ENGINES</topic><topic>HEAT ENGINES</topic><topic>HEAT RESISTANT MATERIALS</topic><topic>HEAT RESISTING ALLOYS</topic><topic>INCONEL 718</topic><topic>INCONEL ALLOYS</topic><topic>INFORMATION</topic><topic>INTERNAL COMBUSTION ENGINES</topic><topic>IRON ALLOYS</topic><topic>LIFETIME</topic><topic>MATERIALS</topic><topic>MATERIALS SCIENCE</topic><topic>MECHANICAL PROPERTIES</topic><topic>Metals. Metallurgy</topic><topic>MICROSTRUCTURE</topic><topic>MOLYBDENUM ALLOYS</topic><topic>NICKEL ALLOYS</topic><topic>NICKEL BASE ALLOYS</topic><topic>NIOBIUM A</topic><topic>NUMERICAL DATA</topic><topic>SERVICE LIFE</topic><topic>TURBINE BLADES</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>PERSSON, C</creatorcontrib><creatorcontrib>PERSSON, P.-O</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>OSTI.GOV</collection><jtitle>Journal of materials engineering and performance</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>PERSSON, C</au><au>PERSSON, P.-O</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Evaluation of service-induced damage and restoration of cast turbine blades</atitle><jtitle>Journal of materials engineering and performance</jtitle><date>1993-08-01</date><risdate>1993</risdate><volume>2</volume><issue>4</issue><spage>565</spage><epage>569</epage><pages>565-569</pages><issn>1059-9495</issn><eissn>1544-1024</eissn><abstract>Conventionally cast turbine blades of Inconel 713C, from a military gas turbine aircraft engine, have been investigated with regard to service-induced microstructural damage and residual creep life time. For cast turbine blades, service life is defined by statistical values. The statistical methods can prove to be uneconomical, because safe limits must be stated with regard to the statistical probability that some blades will have higher damage than normal. An alternative approach is to determine the service-induced microstructural damage on each blade, or a representative number of blades, to better optimize blade usage. Ways to use service-induced [gamma][prime] rafting and void formation as quantified microstructural damage parameters in a service lifetime prediction model are suggested. The damage parameters were quantified, in blades with different service exposure levels, and correlated to remaining creep life evaluated from creep test specimens taken from different positions of serviced blades. Results from tests with different rejuvenation treatments, including hot isostatic pressing and/or heat treatment, are discussed briefly.</abstract><cop>New York, NY</cop><pub>Springer</pub><doi>10.1007/BF02661742</doi><tpages>5</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 1059-9495 |
| ispartof | Journal of materials engineering and performance, 1993-08, Vol.2 (4), p.565-569 |
| issn | 1059-9495 1544-1024 |
| language | eng |
| recordid | cdi_osti_scitechconnect_5307563 |
| source | SpringerLink Journals |
| subjects | 330103 - Internal Combustion Engines- Turbine 360102 - Metals & Alloys- Structure & Phase Studies 360103 - Metals & Alloys- Mechanical Properties ADVANCED PROPULSION SYSTEMS Aircraft industry. Spacecraft AIRFOILS ALLOY-NI53CR19FE19NB5MO3 ALLOYS ALUMINIUM ADDITIONS ALUMINIUM ALLOYS Applications Applied sciences CHROMIUM ALLOYS CORROSION RESISTANT ALLOYS CREEP DATA Engineering techniques in metallurgy. Applications. Other aspects ENGINES Exact sciences and technology EXPERIMENTAL DATA GAS TURBINE ENGINES HEAT ENGINES HEAT RESISTANT MATERIALS HEAT RESISTING ALLOYS INCONEL 718 INCONEL ALLOYS INFORMATION INTERNAL COMBUSTION ENGINES IRON ALLOYS LIFETIME MATERIALS MATERIALS SCIENCE MECHANICAL PROPERTIES Metals. Metallurgy MICROSTRUCTURE MOLYBDENUM ALLOYS NICKEL ALLOYS NICKEL BASE ALLOYS NIOBIUM A NUMERICAL DATA SERVICE LIFE TURBINE BLADES |
| title | Evaluation of service-induced damage and restoration of cast turbine blades |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-21T04%3A36%3A20IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-pascalfrancis_osti_&rft_val_fmt=info:ofi/fmt:kev:mtx:journal&rft.genre=article&rft.atitle=Evaluation%20of%20service-induced%20damage%20and%20restoration%20of%20cast%20turbine%20blades&rft.jtitle=Journal%20of%20materials%20engineering%20and%20performance&rft.au=PERSSON,%20C&rft.date=1993-08-01&rft.volume=2&rft.issue=4&rft.spage=565&rft.epage=569&rft.pages=565-569&rft.issn=1059-9495&rft.eissn=1544-1024&rft_id=info:doi/10.1007/BF02661742&rft_dat=%3Cpascalfrancis_osti_%3E3815812%3C/pascalfrancis_osti_%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |