Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

Abstract: A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface; a metallic outer ring positioned in axial alignment with and radially outward of the inner ring; and a conduction cut structure disposed between the inner and outer rings.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

Abstract: A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface; a metallic outer ring positioned in axial alignment with and radially outward of the inner ring; and a conduction cut structure disposed between the inner and outer rings.

Abstract: A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together.

Abstract: A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together.

Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.

Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.

Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.

Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The combustor includes an air swirler, and the one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends circumferentially through the deflector portion for receiving cooling fluid therein. Because the deflector-flare cone assembly receives pre-loaded braze tape and braze rope, a single braze operation secures the deflector-flare cone assembly within the combustor and to a combustor air swirler.