Abstract: Various aspects include a turbomachine component, along with a turbomachine and related storage medium. In some cases, the turbomachine component includes: a body defining an inner cavity, the body having an outer surface and an inner surface opposing the outer surface, the inner surface facing the inner cavity; and a mount coupled with the inner surface of the body, the mount including: an impingement baffle coupled with and separated from the inner surface of the body, the impingement baffle including a set of apertures configured to permit flow of a heat transfer fluid therethrough to contact the inner surface of the body; and a reclamation channel connected with the impingement baffle for reclaiming the heat transfer fluid.

Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more corner regions. The intersegment seal disposed in a slot defining a high-pressure slot side and a low-pressure slot side, wherein the slot includes a plurality of slot segments. Each of the plurality of seal segments including at least one extended portion to either seal the one or more corner regions on a low-pressure slot side, form a recess in the intersegment seal, or both.

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 turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

Abstract: The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures. A duct plate encloses the first portion of the impingement plate. The duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures. Compressed air from the outer chamber flows through the one or more impingement apertures into the inner chamber and exits the inner chamber through the one or more post-impingement apertures.

Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more corner regions. The intersegment seal disposed in a slot defining a high-pressure slot side and a low-pressure slot side, wherein the slot includes a plurality of slot segments. Each of the plurality of seal segments including at least one extended portion to either seal the one or more corner regions on a low-pressure slot side, form a recess in the intersegment seal, or both.

Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.

Abstract: A gas turbine seal assembly includes a gas turbine component and a gas turbine seal component contacting the gas turbine component to form a seal between the two components. The gas turbine seal component includes ceramic matrix composite plies bonded together to form the ceramic matrix composite component. A bond-inhibiting coating on a non-bonding portion of a first surface of one of the ceramic matrix composite plies prevents bonding between the non-bonding portion of the first surface and a second surface of a neighboring ceramic matrix composite ply. At least one bonding portion of the first surface lacking the bond-inhibiting coating is bonded to the second surface. A method of forming a ceramic matrix composite component includes selectively applying a bond-inhibiting coating to a non-bonding portion of a first surface of a ceramic matrix composite ply and bonding the ceramic matrix composite plies together.

Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.

Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A connection portion extends radially inwardly from the radially inner surface of the platform. An airfoil extends radially outwardly from the radially outer surface of the platform to an airfoil tip. The airfoil includes a leading edge portion and a trailing edge portion. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet defined by the connection portion to one or more outlet passages at least partially defined by the trailing edge portion of the airfoil. At least one of the one or more outlet passages include an entrance and an exit radially inwardly offset from the entrance.

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

Abstract: An article and method of forming an article are provided. The article includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, and at least one cooling feature positioned within the inner region. The body portion includes a first material and the at least one cooling feature includes a second material, the second material having a higher thermal conductivity than the first material. The method includes manufacturing a body portion by an additive manufacturing technique and manufacturing at least one cooling feature by the additive manufacturing technique. The body portion includes a first material and the at least one cooling feature includes a second material, the second material having a higher thermal conductivity than the first material.

Abstract: An article and method of cooling an article are provided. The article includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, and at least one cooling feature positioned within the inner region. At least one of the inner surface of the body portion and the at least one cooling feature has a surface roughness of between about 100 microinches (about 2.54 microns) and about 3,000 microinches (about 76.2 microns). The method of forming an article includes manufacturing a body portion by an additive manufacturing technique, and manufacturing at least one cooling feature by the additive manufacturing technique. The additive manufacturing integrally forms a surface roughness of between about 100 microinches (about 2.54 microns) and about 3,000 microinches (about 76.2 microns) on at least one of an inner surface of the body portion and the at least one cooling feature.

Abstract: An article and method of cooling an article are provided. The article includes a body portion, a plurality of partitions within the body portion, and at least one aperture in each of the partitions, the at least one aperture arranged and disposed to direct fluid towards an inner surface of the body portion. The plurality of partitions form at least one up-pass cavity and at least one re-use cavity arranged and disposed to receive the fluid from the at least one aperture in one of the partitions. The method includes providing the article having an up-pass partition and a re-use partition, generating a first fluid flow through the at least one aperture in the up-pass partition, receiving a post-impingement fluid within the re-use cavity, and generating a re-use fluid flow through the at least one aperture in the re-use partition, the re-use fluid flow being generated from the post-impingement fluid.

Abstract: An article and a component are provided. The article includes a base portion arranged and disposed to be positioned within a component, and an arrangement of apertures formed in the base portion, each of the apertures extending through the base portion. The arrangement of apertures is arranged and disposed to provide shadowless cooling of an inner surface of the component. The component includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, and an article positioned within the inner region, the article comprising a base portion and an arrangement of apertures formed in the base portion, each of the apertures extending through the base portion. The arrangement of apertures is arranged and disposed to provide shadowless cooling of the inner surface of the body portion. Also provided is a method of cooling a component including an article positioned therein.

Abstract: An article and method of cooling an article are provided. The article includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, at least one up-pass cavity formed within the inner region and extending from a base of the body portion towards a tip of the body portion, and a cap formed in each up-pass cavity, each cap being adjacent to the tip of the body portion, having at least one aperture formed therein, and being arranged and disposed to direct fluid towards the tip of the body potion. The method includes directing a fluid into the first up-pass cavity, passing the fluid through at least one aperture in the cap, contacting the tip of the article with the fluid, receiving the post-impingement fluid within a down-pass cavity, and directing the post-impingement fluid through the down-pass cavity.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band define a first set of cooling channels and a second set of cooling channels formed beneath a gas side surface of the corresponding inner band or outer band. The inner band or the outer band further define a coolant distribution plenum that is in fluid communication with the first and second sets of cooling channels. The coolant distribution plenum provides a stream of coolant to at least one of the first set of cooling channels and the second set of cooling channels.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.