Ducted fan gas turbine engine

The engine is supported from an aircraft wing by a pylon 34 having a beam 36 which projects a relatively long way in front of the pylon and, rather than being thickened to resist the increased bending loads, is supported by a link 38 extending from the pylon 34 to a position near the extremity of th...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	LEONARD JOHN RODGERS
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The engine is supported from an aircraft wing by a pylon 34 having a beam 36 which projects a relatively long way in front of the pylon and, rather than being thickened to resist the increased bending loads, is supported by a link 38 extending from the pylon 34 to a position near the extremity of the beam 36. The latter is connected directly or via link 42 to an annular box structure 40 dividing supporting struts 18 and 28. A peg 46 protruding from beam 36 is received in a socket 48 in the core engine casing 16.