Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.

Abstract: An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

Abstract: An article is disclosed including a manifold, an article wall, a post-impingement cavity and a plurality of post-impingement partitions. The manifold includes an impingement wall defining a plenum and a plurality of impingement apertures. The article wall includes a plurality of external apertures. The post-impingement cavity is disposed between the manifold and the article wall, and is arranged to receive a fluid from the plenum through the plurality of impingement apertures and exhaust the fluid through the plurality of external apertures. The plurality of post-impingement partitions divide the post-impingement cavity into a plurality of sub-cavities, and hermetically separate the plurality of sub-cavities from one another. The impingement wall, article wall and plurality of post-impingement partitions are integrally formed as a single, continuous article. The article may be an airfoil component.

Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.

Abstract: An article and method of forming an article are provided. The article includes a body portion separating an inner region and an outer region, an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and a conduit extending from an outer surface of the body portion at the aperture and being arranged and disposed to controllably direct fluid from the inner region to the outer region. The method includes providing a body portion separating an inner region and an outer region, providing an aperture in the body portion, and forming a conduit over the aperture, the conduit extending from an outer surface of the body portion and being arranged and disposed to controllably direct fluid from the inner region to the outer region. The article is arranged and disposed for insertion within a hot gas path component.

Abstract: A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

Abstract: A turbine airfoil includes a leading edge, a trailing edge, a root and a tip. Also included is a pressure side wall extending between the leading edge and the trailing edge and between the root and the tip. Further included is a suction side wall extending between the leading edge and the trailing edge and between the root and the tip. Yet further included is a non-circular cooling channel defined by the turbine airfoil and extending radially from the root to the tip, the non-circular cooling channel routing a cooling air to an outlet hole formed in the tip. Also included is an exhaust hole defined by the turbine airfoil and extending from the non-circular cooling channel to the suction side wall, the exhaust hole radially located between the root and the tip.

Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

Abstract: A shroud block segment for a gas turbine includes a main body having a leading portion, a trailing portion, a first side portion and an opposing second side portion that extend axially between the leading portion and the trailing portion. The main body further includes an arcuate combustion gas side, an opposing back side and a cooling chamber defined in the back side. A cooling plenum and an exhaust passage are defined within the main body where the exhaust passage provides for fluid communication out of the cooling plenum. An insert opening extends within the main body through the back side towards the cooling plenum. A cooling flow insert is disposed within the insert opening. The cooling flow insert comprises a plurality of cooling flow passages that provide for fluid communication between the cooling chamber and the cooling plenum.

Abstract: A bucket assembly and a method for treating a bucket assembly are disclosed. The bucket assembly includes a platform, the platform defining a platform cooling circuit, and an airfoil extending generally radially outward from the platform, the airfoil defining an airfoil cooling circuit. The bucket assembly additionally includes a lower body portion extending generally radially inward from the platform, the lower body portion defining a root and a cooling passage extending from the root, the cooling passage in fluid communication with the airfoil cooling circuit. The bucket assembly further includes a transfer passage defined between and in fluid communication with the airfoil cooling circuit and the platform cooling circuit such that a cooling medium may flow from the airfoil cooling circuit through the transfer passage to the platform cooling circuit.

Abstract: A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.

Abstract: A system and method for controlling the performance of a gas turbine system is provided. A backflow margin pressure ratio for a component is determined. A modified backflow margin pressure ratio for the component is calculated based on the number of fired hours and starts. Bleed air along a first flow path is controlled based on the modified backflow margin pressure ratio.

Abstract: Turbine components include at least one fluid flow passage at least one aperture disposed on a surface of the turbine component and fluidly connected to the at least one fluid flow passage. The at least one aperture includes a floor extending from the at least one fluid flow passage to the surface; and, a step disposed between an inner portion of the floor and an outer portion of the floor such that the inner portion of the floor and the outer portion of the floor do not comprise a single planar surface.

Abstract: A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.

Abstract: A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.

Abstract: A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area.

Abstract: A system and method for controlling the performance of a gas turbine system is provided. A backflow margin pressure ratio for a component is determined. A modified backflow margin pressure ratio for the component is calculated based on the number of fired hours and starts. Bleed air along a first flow path is controlled based on the modified backflow margin pressure ratio.

Abstract: A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.

Abstract: According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage.

Abstract: A shroud block segment for a gas turbine includes a main body having a leading portion, a trailing portion, a first side portion and an opposing second side portion that extend axially between the leading portion and the trailing portion. The main body further includes an arcuate combustion gas side, an opposing back side and a cooling chamber defined in the back side. A cooling plenum and an exhaust passage are defined within the main body where the exhaust passage provides for fluid communication out of the cooling plenum. An insert opening extends within the main body through the back side towards the cooling plenum. A cooling flow insert is disposed within the insert opening. The cooling flow insert comprises a plurality of cooling flow passages that provide for fluid communication between the cooling chamber and the cooling plenum.