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dc.creatorDas, Suman
dc.creatorP. Fuesting, Timothy
dc.creatorDanyo, Gregory
dc.creatorE. Brown, Lawrence
dc.creatorBeaman, Joseph J.
dc.creatorBourell, David L.
dc.creatorSargent, Kathleen
dc.date.accessioned2019-02-18T17:30:09Z
dc.date.available2019-02-18T17:30:09Z
dc.date.issued1998
dc.identifier.urihttps://hdl.handle.net/2152/73391
dc.identifier.urihttp://dx.doi.org/10.26153/tsw/543
dc.description.abstractThis paper presents the development of a new technique for the production of abrasive turbine blade tips by direct laser processing. This superalloy cermet component is an integral part of the low pressure turbine sealing system in a demonstrator engine. Direct laser fabrication of this component fiom a bed a loose powder results in significant cost savings and improved performance over the currently employed production technique. The technology has been demonstrated by fabricating a prototype lot of 100 blade tips, which will be subjected to an engine test. This is the first instance of a direct fabrication method applied to the production of functional engine hardware. This research was funded by the United States Air Force contract F33615-94- C-2424 titled "Affordable Turbine Blade Tips".en_US
dc.language.isoengen_US
dc.relation.ispartof1998 International Solid Freeform Fabrication Symposiumen_US
dc.subjectaffordabilityen_US
dc.subjecttechniqueen_US
dc.titleDirect Laser Fabrication of a Gas Turbine Engine Component - Microstructure and Properties - Part Ien_US
dc.typeConference paperen_US
dc.description.departmentMechanical Engineeringen_US
dc.rights.restrictionOpenen_US


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