Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: A mixing joint for adjacent can combustors may include a first can combustor with a first combustion flow and a first wall, a second can combustor with a second combustion flow and a second wall, and a flow disruption surface positioned about the first wall and the second wall to promote mixing of the first combustion flow and the second combustion flow.

Abstract: The present application provides a doubly-fed induction generator system for a multi-shaft gas turbine engine. The doubly-fed induction generator system may include a first doubly-fed induction generator in communication with a first shaft of the multi-shaft gas turbine engine, a first rotor of the first doubly-fed induction generator in communication with a converter via a first rotor bus, and a first breaker on the first rotor bus. The first doubly-fed induction generator acts as a generator or a motor depending in part upon the position of the first breaker.

Abstract: The present application provides a doubly-fed induction generator system for a multi-shaft gas turbine engine. The doubly-fed induction generator system may include a first doubly-fed induction generator in communication with a first shaft of the multi-shaft gas turbine engine, a first rotor of the first doubly-fed induction generator in communication with a converter via a first rotor bus, and a first breaker on the first rotor bus. The first doubly-fed induction generator acts as a generator or a motor depending in part upon the position of the first breaker.

Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine includes opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.

Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine includes opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.

Abstract: A gas turbine includes a turbine and an axial-radial diffuser. The turbine includes a last stage airfoil section, which includes a first inner annular wall, a plurality of airfoils, a tip shroud including a first outer annular wall, and a stationary shroud including a second outer annular wall. The first inner annular wall is angled at a first inner angle average, the first outer annular wall is angled at a first outer angle average, and the second outer annular wall is angled at a second outer angle average. The axial-radial diffuser includes a third inner annular wall and a third outer annular wall, wherein the first diffuser section is disposed immediately downstream from the last stage airfoil section, wherein the third inner annular wall is angled at a third inner angle average, and the third outer annular wall is angled at a third outer angle average.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.

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: A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.

Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.

Abstract: An airfoil includes a leading edge, a trailing edge downstream from the leading edge, a pressure surface between the leading and trailing edges, and a suction surface between the leading and trailing edges and opposite the pressure surface. A first convex section on the suction surface decreases in curvature downstream from the leading edge, and a throat on the suction surface is downstream from the first convex section. A second convex section is on the suction surface downstream from the throat, and a first convex segment of the second convex section increases in curvature.

Abstract: The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine. For example, in one embodiment, a gas turbine engine may include a combustor having a combustion flow. The gas turbine engine also may include one or more airfoils forming a first stage nozzle or s transition nozzle disposed downstream of the combustor. Moreover, the gas turbine engine may include a flow disruption surface positioned about a trailing edge of the one or more airfoils to promote mixing of the combustion flow.

Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.

Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.

Abstract: A transition nozzle is provided and includes a liner in which combustion occurs and through which products of the combustion flow toward a turbine bucket stage. The liner includes opposing endwalls and opposing sidewalls extending between the opposing endwalls. The opposing sidewalls are oriented to tangentially direct the flow of the combustion products toward the turbine bucket stage. At least one of the opposing endwalls and the opposing sidewalls including a flow contouring feature to guide the flow of the combustion products.

Abstract: An airfoil includes a leading edge, a trailing edge downstream from the leading edge, a pressure surface between the leading and trailing edges, and a suction surface between the leading and trailing edges and opposite the pressure surface. A first convex section on the suction surface decreases in curvature downstream from the leading edge, and a throat on the suction surface is downstream from the first convex section. A second convex section is on the suction surface downstream from the throat, and a first convex segment of the second convex section increases in curvature.