Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge, wherein the pressure tip wall and the suction tip wall define a trailing edge tip thickness. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall, the squealer cavity including a trench extending fully to the tip trailing edge to form an open flow path out of the tip trailing edge. Further included is a suction side wall and a pressure side wall extending from a root portion of the turbine rotor blade to the tip portion, wherein the suction side wall and the pressure side wall define a trailing edge blade thickness, the trailing edge tip thickness being greater than the trailing edge blade thickness.

Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion having a plurality of radial cooling passages extending longitudinally therein, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises at least one hollow passage fluidly connected to at least one radial cooling passage of the plurality of radial cooling passages.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge flow in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion; a platform lip extending axially from the platform portion, the platform lip disposed radially outward from the at least one angel wing; and a plurality of turbulators disposed along and extending outward from the face of the shank portion between the platform lip and the at least one angel wing.

Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises a hollow portion, wherein the hollow portion is devoid of any coupling structure therein.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion, the at least one angel wing including an angel wing rim extending radially upward toward the airfoil; and a plurality of voids disposed along the angel wing rim.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; an angel wing extending axially from a face of the shank portion; and a plurality of voids disposed along a length of the angel wing, each of the plurality of voids extending radially through the angel wing.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.

Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises a hollow portion.

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Abstract: Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket extending radially about a longitudinal axis of the gas turbine engine, a shroud facing the bucket, the shroud including a fore end portion including a radially inner surface spaced a first distance from the longitudinal axis, and a forward step honeycomb seal positioned on the shroud downstream of the fore end portion and facing the bucket. The forward step honeycomb seal may include a first linear portion including a radially inner surface spaced a second distance from the longitudinal axis, and a forward step portion positioned adjacent to and downstream of the first linear portion, the forward step portion including a radially inner surface spaced a third distance from the longitudinal axis, wherein the second distance is greater than the third distance, and wherein the third distance is greater than the first distance.

Abstract: A sealing assembly for use with a rotary machine is described herein. The sealing assembly includes a stator shroud coupled to the casing. The stator shroud includes an inner surface that at least partially defines the cavity within the casing. At least one stator labyrinth tooth extends outwardly from the stator shroud inner surface towards a rotor assembly positioned within the casing. At least one protective member is coupled to the stator shroud upstream from the at least one stator labyrinth tooth to facilitate reducing a flow of combustion gas across the at least one stator labyrinth tooth.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: The present application provides a stage of a turbine engine. The stage may include a bucket, a shroud facing the bucket, and a contoured honeycomb seal on the shroud. The contoured honeycomb seal may include a first step with a first shape and a second step with a contoured shape.

Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, and a forward step honeycomb seal on the shroud. The forward step honeycomb seal may include a forward step portion and one or more linear portions.

Abstract: A method of manufacturing a blade for use with a rotary machine includes coupling a suction-side section of a part-span shroud to a suction-side surface of an airfoil of the blade. A first point of the airfoil suction-side surface, defined where a trailing edge of the suction-side section intersects the airfoil suction-side surface, is upstream from a second point, defined where a throat intersects the airfoil suction-side surface. A third point, defined where a leading edge of the suction-side section intersects the airfoil suction-side surface, is downstream from a fourth point, defined at a leading edge of the blade. The method also includes coupling a pressure-side section of the part-span shroud to a pressure-side surface of the airfoil. A fifth point of the airfoil pressure-side surface, defined where a trailing edge of the pressure-side section intersects the airfoil pressure-side surface, is downstream from the first point.

Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.

Abstract: A flow control assembly is provided, including a member and a wall. The member has a surface, a flow diverting member and a rail member. The rail member is situated upstream of the flow diverting member. The flow diverting member and the rail member each project from the surface of the member. The flow diverting member has a distal end. The wall is disposed in relation to the member to create a clearance gap between the distal end of the flow diverting member and the wall. A fluid path is created between the member and the wall, and flows from an upstream section and through the clearance gap. A first chamber and a second chamber are defined by the wall and located upstream of the clearance gap.