Gas turbine engine stand with slide rail and lock mechanism

Gas turbine engine stand 38 having engine frame 48, base frame 46 with slide rail 51 enabling relative axial movement between engine frame 48 and base frame 46, load transfer arrangement 54 with first 56 and second 58 features engaging with engine frame 48 part 50 and slide rail 51, locking mechanis...

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Bibliographische Detailangaben
Hauptverfasser:	CHRISTOPHER RICHARD HALLAM, JONATHAN PAUL TAYLOR
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT AVIATION BLASTING 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 MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS STANDS OR SUPPORTS STEAM ENGINES THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	Gas turbine engine stand 38 having engine frame 48, base frame 46 with slide rail 51 enabling relative axial movement between engine frame 48 and base frame 46, load transfer arrangement 54 with first 56 and second 58 features engaging with engine frame 48 part 50 and slide rail 51, locking mechanism 62 locking engine frame 48 to base frame 46, and load path selection mechanism to engage either the locking mechanism 62 or load transfer arrangement 54. Stand 38 may have intermediate frame 50 in fixed axial alignment with engine frame 48. Engine frame 48 or intermediate frame 50 may have load transfer flange 60. Load transfer arrangement 54 may be a jack providing vertical movement with two defined positions. Height adjustment arrangement 66 may move engine frame 48 vertically providing engine split and transportation positions. Axial drive mechanism 78 may axially move engine frame 48 relative to base frame 46. Alignment features 92 may mate with a gas turbine engine fan stand.