Method for modifying an airfoil shroud and airfoil

According to one aspect of the invention, a method is provided for modifying an airfoil shroud 400 located at a tip of an airfoil, the airfoil shroud 400 having a first end edge 406, a second end edge 408, a leading edge 402 and a trailing edge hundred and 4. The method includes locating a reference...

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Bibliographische Detailangaben
Hauptverfasser:	WARD, JOHN DAVID, MYERS, MELBOURNE JAMES, AARON, KELVIN RONO, CONNOR, JAMES RYAN, VAN TASSEL, BRAD WILSON
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS WEAPONS
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Beschreibung
Zusammenfassung:	According to one aspect of the invention, a method is provided for modifying an airfoil shroud 400 located at a tip of an airfoil, the airfoil shroud 400 having a first end edge 406, a second end edge 408, a leading edge 402 and a trailing edge hundred and 4. The method includes locating a reference location 410 in the first end edge 406 of the airfoil shroud 400, the reference location 410 being proximate a seal rail 412 extending circumferentially from the substantially horizontal surface and forming a relief cut 500 in the airfoil shroud 400 to remove the reference location 410, wherein a modifying of the airfoil shroud 400 is complete following forming of the relief cut 500.