Abstract: A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

Abstract: A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

Abstract: A turbine rotor blade including an airfoil, tip shroud, and fillet formed therebetween. The fillet defines a fillet profile variable about the intersection for connecting the tip shroud and airfoil and facilitating aerodynamic airflow. The fillet includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per points within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, as set forth in Table I, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth, continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points between and including point 1 and point 50 of each reference plane between and including a reference plane H and a reference plane W, as set forth in Table I.

Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.

Abstract: A turbine rotor blade including an airfoil, tip shroud, and fillet formed therebetween. The fillet defines a fillet profile variable about the intersection for connecting the tip shroud and airfoil and facilitating aerodynamic airflow. The fillet includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per points within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, as set forth in Table I, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth, continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points between and including point 1 and point 50 of each reference plane between and including a reference plane H and a reference plane W, as set forth in Table I.

Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein that extends from a connection with a coolant source at the root to at least the approximate radial height of the platform. The platform cooling arrangement includes a platform slot formed through at least one of a pressure side slashface and a suction side slashface, the platform slot being in fluid communication with a high-pressure coolant region of the turbine rotor blade. An insert inserted in the platform slot, the insert having a blind channel extending inside the insert. The insert aligns with the platform slot to fluidly connect the channel to the high-pressure coolant region. At least one passage is in fluid communication with the channel and an exterior region of the turbine rotor blade.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein that extends from a connection with a coolant source at the root to at least the approximate radial height of the platform. The platform cooling arrangement includes a platform slot formed through at least one of a pressure side slashface and a suction side slashface, the platform slot being in fluid communication with a high-pressure coolant region of the turbine rotor blade. An insert inserted in the platform slot, the insert having a blind channel extending inside the insert. The insert aligns with the platform slot to fluidly connect the channel to the high-pressure coolant region. At least one passage is in fluid communication with the channel and an exterior region of the turbine rotor blade.

Abstract: A cooling system according to an embodiment includes: a forked passage cooling circuit, the forked passage cooling circuit including a first leg and a second leg; and an air feed cavity for supplying cooling air to the first leg and the second leg of the forked passage cooling circuit; wherein the first leg of the forked passage cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the forked passage cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels in the multi-wall blade.

Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.

Abstract: An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.

Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.

Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.

Abstract: An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.

Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.

Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.

Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.

Abstract: A cooling system according to an embodiment includes: a forked passage cooling circuit, the forked passage cooling circuit including a first leg and a second leg; and an air feed cavity for supplying cooling air to the first leg and the second leg of the forked passage cooling circuit; wherein the first leg of the forked passage cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the forked passage cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels in the multi-wall blade.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side.

Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.