An impingement insert for HGP component may include a hollow body having a longitudinal extent, an exterior surface and an interior surface. The hollow body may include a first side wall, a second side wall contiguous with the first side wall at a first end of each, the second side wall is flexibly movable relative to the first side wall. A spring element is contiguous with a second end of each of the first side wall and the second side wall, and extends along at least a portion of the longitudinal extent of the hollow body and into the hollow body between the first side wall and the second side wall. The spring element biases the side walls to an expanded position from a compressed position of the hollow body. Cooling passages pass between the exterior surface and the interior surface of the hollow body in both side walls.

A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.

A seal device is configured so that seal properties can be held over a long period of time. A seal device 1 inserted into and disposed between grooves each formed at first and second components which are adjacent to each other and collectively form a housing structure includes a first seal member inserted into the groove of the first component, a second seal member inserted into the groove of the second component, and a partitioning member extending between the first and second seal members to partition a space between the grooves of the first and second components and arranged movably relative to the first and second seal members.

A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.

A manufacturing method of a casing, the manufacturing method includes a step of manufacturing a plurality of metal members which are components constituting the casing including a casing body having a tubular shape that extends with an axis as a center; a step of arranging the plurality of metal members according to the casing to be formed; and a step of forming the casing by welding the plurality of metal members to each other, in which in the step of manufacturing the metal members, the plurality of metal members are manufactured by at least two kinds of manufacturing methods among forging, steel plate processing, casting, and a fused metal deposition method.

A gas turbine engine exhaust case assembly comprises: an exhaust case having an axis and defining an annular gas path; a bearing housing coaxially supported within the exhaust case; an exhaust cone coaxial and rearward of the exhaust case; a heat shield joined to the exhaust cone, the heat shield being disposed radially between the exhaust cone and the bearing housing; and a mounting bracket extending from the exhaust case and joining the exhaust case and the exhaust cone together.

A rotor blade is provided for a turbine engine. This rotor blade includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise to a tip. The airfoil is configured with a plurality of projections arranged longitudinally along the tip.

A gas turbine engine exhaust case assembly comprises: an exhaust case having an axis and defining an annular gas path; a bearing housing coaxially supported within the exhaust case; an exhaust cone coaxial and rearward of the exhaust case; a heat shield joined to the exhaust cone, the heat shield being disposed radially between the exhaust cone and the bearing housing; and a mounting bracket extending from the exhaust case and joining the exhaust case and the exhaust cone together.

A heat shield may include a base portion, wherein the base portion bounds a triangular void, a top portion, wherein the top portion bounds an ovular void, and a tapered portion, wherein the tapered portion extends between the base portion and the top portion, the top portion having a smaller cross-sectional area than the base portion.