Abstract: Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.

Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.

Abstract: Various methods and systems are provided for an axial turbine including a containment shroud. In one example, an axial turbine for use in an engine system comprises a turbine disc/blisk and a shroud housing the turbine disc/blisk, the shroud including a first region, a second region, and a third region. A thickness of the second region is dependent on a length between the first region and the third region, and the third region has a burst strength that under a burst condition retains one or more fragments of the turbine disc/blisk.

Abstract: A turbocharger includes a turbine disc, a compressor wheel mechanically coupled to the turbine disc, and a single-walled air inlet. Made of ductile iron, the air inlet is configured to admit air to the compressor wheel and to provide clearance for rotation of the compressor wheel.

Abstract: Various methods and systems are provided for an axial turbine including a containment shroud. In one example, an axial turbine for use in an engine system comprises a turbine disc/blisk and a shroud housing the turbine disc/blisk, the shroud including a first region, a second region, and a third region. A thickness of the second region is dependent on a length between the first region and the third region, and the third region has a burst strength that under a burst condition retains one or more fragments of the turbine disc/blisk.