Abstract: A sealing assembly for achieving a fluid seal between a rotatable shaft and a housing circumscribing the rotatable shaft to inhibit fluid leakage therebetween a high pressure fluid region and a relatively lower pressure fluid region. The sealing assembly includes at least one primary seal, comprising an axial stack of a plurality of diaphragm members, including an upstream diaphragm and a downstream diaphragm. A plurality of finger seal plates are positioned between the upstream diaphragm and the downstream diaphragm. The plurality of diaphragm members define a passageway in fluid communication with the high pressure fluid region and a low pressure fluid region. The sealing assembly includes at least one secondary seal positioned within the passageway and configured to convert fluid from a high pressure axial pressure balance to a low pressure axial pressure balance thereby reducing a radially inward pressure load.

Abstract: The complex mechanical gear trains and lubrication systems of conventional engine configurations are eliminated by using combinations of hydrodynamic air foil bearings, hydrodynamic solid geometry carbon seals/bearings, magnetic bearings, and electrical starter/generators that can also act as bearings to support the high speed shafts of gas turbine engines. The various bearing types and the starter/generators are arranged in such a way as to share peak loads experienced by the engine shaft during maximum aircraft maneuvers. This results in a minimal bearing and engine size.

Abstract: The complex mechanical gear trains and lubrication systems of conventional engine configurations are eliminated by using combinations of hydrodynamic air foil bearings, hydrodynamic solid geometry carbon seals/bearings, magnetic bearings, and electrical starter/generators that can also act as bearings to support the high speed shafts of gas turbine engines. The various bearing types and the starter/generators are arranged in such a way as to share peak loads experienced by the engine shaft during maximum aircraft maneuvers. This results in a minimal bearing and engine size.

Abstract: An aircraft thrust reverser mechanism comprises a thrust reverser moveable between a deployed position in which at least a portion of gas flowing through the aircraft engine is redirected in a non-rearward direction and a stowed position in which gas flowing through the engine is not redirected. A thrust reverser lock is provided to prevent inadvertent deployment of the thrust reverser. The thrust reverser lock comprises a locking element rotatable about a pivot between a closed position in which the locking element prevents deployment of the thrust reverser and an open position in which the locking element permits the thrust reverser to be deployed. A retractable blocking element prevents the locking element from moving to the second position unless the blocking element is first withdrawn.