A strut cover for a gas turbine includes: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.

The invention concerns a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear and a plurality of plain bearing pins. Here, a plain bearing pin is arranged in each planet gear, wherein the plain bearing pin and the planet gear form a lubricated plain bearing, and the plain bearing pin forms a crowning at its contact face, wherein the outer diameter of the contact face decreases from a maximum outer diameter towards at least one axial end of the contact face. The crowning of the contact face is configured such that the contact face is concavely shaped adjacent to at least one axial end of the contact face or to a cylindrical region adjoining the axial end.

To provide an axial flow turbine that can reduce circumferential pressure differences to reduce loss. The axial flow turbine includes: stator blades arrayed in the circumferential direction; and a diaphragm inner ring having an outer circumferential surface that interconnects the stator blades on their inner-circumference side and constitutes a wall surface of a main flow path. The outer circumferential surface of the diaphragm inner ring has depressed portions. Each depressed portion is formed in an area that is on the downstream side of a throat where the distance between a suction surface of one stator blade of a pair of adjacent blades and a pressure surface of other stator blade of the pair of adjacent blades becomes the shortest, and that lies in the circumferential direction within a range of a throat position on the suction surface of the one stator blade to a downstream edge position of the one stator blade. The area includes a downstream edge position of the outer circumferential surface in the axial direction.

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.

A rotor, a turbine, and a gas turbine including the same are provided. The rotor includes a pair of disks rotating about an imaginary central axis and arranged parallel to each other in an axial direction, a replaceable self-locking sealing assembly interposed between the pair of disks, and a fastening section disposed on the sealing assembly to fasten the sealing assembly to the disks. The disk includes a sealing slot disposed on an opposite surface to another adjacent disk and a head slot disposed outward from the sealing slot with respect to a radial direction of the to disk. The sealing assembly includes a main body with one end inserted into the sealing slot through the head slot from an outside of the disk and a sealing head disposed on another end of the main body to be seated on an inner wall of the head slot to restrict the main body from being moved.

A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec).sup.1/2 and three hundred (ft/sec).sup.1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec).sup.1/2 and three hundred (ft/sec).sup.1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

An impingement cooling structure is provided. The impingement cooling structure includes a flow channel formed between a first wall and a second wall facing the first wall, a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the flow channel, and a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes.

Provided is a labyrinth seal including a first structure; and a second structure opposing the first structure. The first structure includes seal fins located at intervals in an axial direction and extending toward the second structure; a downstream wall surface located most downstream one of the seal fins and extending toward the second structure. A tip of the downstream wall surface located at a side of a tip of the most downstream seal fin, the side being close to the second structure in a radial direction and having a first outlet surface extending from the tip of the downstream wall surface toward a downstream side. The second structure includes a second outlet surface opposing the first outlet surface, a radial gap between the first outlet surface and the second outlet surface; and a cavity surface located upstream of the second outlet surface recessed away from the first structure.