United Technologies Corporation

Kurt M Dembeck

David H Hibner

Dennis F Buono

Roy D Franceschet

Robert F Kasprow

Grant Eckfeldt

Michael A Weisse

Herbert J Lillibridge

Richard T White

Andrew C Kulak

Woven fiber ballistic fabric (22) of multiple layers surrounds an isogrid support structure (20). A cuff portion (38) has shorter warp threads than the major portion (3) and also is impregnated with epoxy resin. A diameter restrains the fabric from aft movement during a blade ejection event.

Aircraft fan containment structure restraint

Isogrid structure (20) forms case (14) surrounding the fan blades. In the zones where blade penetration is anticipated, the ribs (38) of the lattice do not run circumferentially. The skin segments (48) are of different thickness in different zones, but do not differ more than 30% from the thickness of an adjoining segment.

Aircraft fan containment structure

An axial flow turbomachine's engine core (16) and radially outwardly disposed fan case (18) are joined together with a radially extending segmented fan case strut (10). The strut (10) is segmented into a radially inner portion (20) and a radially outer portion (20) at a midspanly disposed strut joint (14). The strut joint (14) has an axially extending tapered tongue (26) which slidably engages with a mating axially extending groove (46). A radially extending flange (36) disposed proximate to the trailing edge (35) of the inner portion (20) is bolted to the radially extending flange (56) disposed proximate to the trailing edge (55) of the outward portion (40) when the tongue (26) is fully engaged with the groove (46) to releasably secure the strut joint (14). Another embodiment shows a pair of interlocked axially extending channels (60) each having a U-shaped cross-section replacing the interlocked tongue and groove (26,46) of the first embodiment. Radially extending flanges (36,56) disposed proximate to the portions' (20,40) trailing edges 935,55) are likewise bolted together to releasably secure the strut joint (14) when the channels' three corresponding pairs of contact surfaces (62) are fully slidably engaged.

Fan case strut for turbomachine

A rotary machine 10 includes a rotor shaft 40 and a support system 63 for the shaft. The support system includes a spring 68 and viscous damper 70. Apparatus for removing oil from the damper at preselected rotor speeds is provided and in one embodiment permits operating the engine over a rotor speed range which avoids critical speeds.

Apparatus for supporting a rotating shaft in a rotary machine

A rotary machine 10 includes a rotor shaft 40 and a support system 63 for the shaft. The support system includes a spring 68 and viscous damper 70. Means for removing oil from the damper at preselected rotor speeds is provided and in one embodiment permits operating the engine over a rotor speed range which avoids critical speeds.

Apparatus and method for supporting a rotating shaft in a rotary machine

A fan case 30 which extends circumferentially about a fan rotor assembly 26 in a turbofan gas turbine engine 10 is disclosed. The fan case has a shell 66 outwardly of the rotor assembly for blocking the rotor blade 38 during a blade failure from penetrating the portion of the shell immediately outwardly of the rotor blade. The material of the shell increases in thickness in the axially rearward direction and has a maximum thickness rearward of a reference plane passing through the mid-chord point of the rotor blade.

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Vernon, CT, United States of America

Kurt M Dembeck