Method of reassembling a gas turbine engine

A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the ba...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Taylor, Jonathan Paul, Hallam, Christopher Richard
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT AVIATION BLASTING COMBINED OPERATIONS COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS FRAMES, CASINGS, OR BEDS OF ENGINES OR OTHER MACHINES ORAPPARATUS NOT SPECIFIC TO AN ENGINE, MACHINE, OR APPARATUSPROVIDED FOR ELSEWHERE GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS STANDS OR SUPPORTS STEAM ENGINES THERMAL INSULATION IN GENERAL TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.