Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a fan case, an intermediate case and a gas generator case integrated with one another.

Abstract: The method comprises flowforming at least one section of the preform and then welding at least one additional element to the at least one flowformed section.

Abstract: The method is used for making an annular gas turbine engine case, the method comprises flowforming a first area of the preform to provide a first annular case portion having a first thickness and a second area having a second thickness, the first and the second average thickness being different.

Abstract: A single oil nozzle unit is mounted in a bearing compartment of a gas turbine engine for providing multiple individual jets for the individual bearing components in the bearing compartment.

Abstract: An oil feed assembly suitable for use in a gas turbine engine having a bearing housing, an outer ring surrounding the bearing housing and a monocase extending therebetween. The assembly provides an oil supply tube for extension within the monocase and between the outer ring and the bearing housing. An oil nozzle support means is employed for selective releasable engagement with one end of the oil supply tube. This is also supported by an oil supply tube support means for selective releasable engagement with a second end of the oil supply tube. A coupling means for coupling said oil supply tube support means and the outer ring completes the assembly.

Abstract: A gas turbine engine has a compressor assembly and a turbine assembly rotationally mounted on a shaft, the turbine assembly being driven by hot gases discharged from a combustion chamber disposed between the compressor and turbine assemblies and an engine case encasing a portion of the engine, the case having an oblong bleed hole having a major axis parallel to a gaspath direction and a minor axis perpendicular to the gaspath direction.

Abstract: An oil shield for an upper tower shaft gear. The shield provides a plurality of shield members for encapsulating the upper tower shaft gear to reduce the amount of displaced oil from contacting surrounding engine components. The shield includes a first shield member adjacent a top surface of the upper tower shaft gear and a second shield member adjacent an under surface of the upper tower shaft gear which is engaged with the first shield member to enclose the upper tower shaft gear. A third shield member is positioned adjacent the second shield member. The shield members permit oil drainage in a predetermined pattern without undesirable dispersion within the engine compartments.

Abstract: A fan case and method of manufacturing a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.