Methods and apparatus for joining gas turbine parts together

A method enables a gas turbine engine to be assembled. The method comprises forming at least one substantially elliptically-shaped opening within a flange (72) extending from a fan disk (40), inserting a fastener (120) including a first body portion (122), a second body portion (124), and an anti-ro...

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Bibliographische Detailangaben
Hauptverfasser:	TAKEHARA, JOANN MARI, DIX, BRIAN EDWARD, GARRISON, MICHAEL RAY
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS ORMACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS,CLIPS, WEDGES, JOINTS OR JOINTING ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A method enables a gas turbine engine to be assembled. The method comprises forming at least one substantially elliptically-shaped opening within a flange (72) extending from a fan disk (40), inserting a fastener (120) including a first body portion (122), a second body portion (124), and an anti-rotation stop (126) extending therebetween, at least partially through the at least one flange opening, and coupling the fastener to the flange such that the fastener stop is positioned within the at least one flange opening.