Abstract: A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels.

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes a first channel disposed within the body having a first end portion and a second end portion and a second channel disposed within the body having a third end portion and a fourth end portion. The first and second channels are configured to receive the cooling fluid from the cavity to cool the body. The first end portion and the fourth end portion each include a hook-shaped portion having a free end.

Abstract: A method and device for retaining position of a consumable core during composite article manufacturing is taught herein by inserting a consumable core having a consumable core body and a plurality of retention artifacts into a composite precursor hollow feature of a composite precursor structure. Then positioning the consumable core such that the plurality of retention artifacts projecting from the consumable core exterior surface at least partially engage with a substantially spatially replicate surface geometry in the composite precursor hollow feature. The consumable core is then consumed as a soluble infiltrant to form a composite article.

Abstract: A host gas flow path component includes a body including a leading edge, a trailing edge, a first side edge, a second side edge, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid. The hot gas flow path component includes a supply channel disposed within the body and extending from the cavity to adjacent the leading edge or the trailing edge. The hot gas flow path component includes a channel disposed within the body adjacent the trailing edge or the leading edge. The channel extends across the body in a direction from the first side edge toward the second side edge. The channel is configured to receive the cooling fluid from the cavity to cool the trailing edge or the leading edge via an intermediate channel extending between the supply channel and the channel.

Abstract: A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have hook-shaped portions with free ends having a width greater than an adjacent portion coupled to the free end.

Abstract: A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have portions with free ends having a width greater than an adjacent portion coupled to the free end.

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes a first channel disposed within the body having a first end portion and a second end portion and a second channel disposed within the body having a third end portion and a fourth end portion. The first and second channels are configured to receive the cooling fluid from the cavity to cool the body. The first end portion and the fourth end portion each include a hook-shaped portion having a free end.

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.

Abstract: A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels.

Abstract: A turbomachine includes a compressor, a turbine, a combustor operatively coupled to the compressor and the turbine, and an injection nozzle assembly mounted in the combustor. The injection nozzle assembly includes a swirler member provided with a hub portion having an internal surface. The injection nozzle assembly also includes a nozzle section, and a nozzle tip member fluidly coupled to the nozzle section and the swirler member. The nozzle tip member includes a body having a first end section that extends from the nozzle section to a second end section arranged in the hub portion of the swirler member. The nozzle tip member includes an external surface, and a discharge port. At least one of the external surface of the nozzle tip member and the internal surface of the swirler member hub portion is provided with a plurality of grooves.