Abstract: A system for asymmetric flow extraction is described and claimed, the system comprising a flow path, a bleed slot in the flow path, a bleed cavity for receiving at least a portion of the fluid extracted from the flow path and a bleed passage in flow communication with the bleed slot and the bleed cavity wherein the bleed passage has at least one deflector having a shape such that the width of the bleed passage cross section varies in a direction normal to the direction of fluid flow in the bleed passage. In another embodiment, the deflector has an aerodynamic surface having a shape such that the flow passage between the aerodynamic surface and a surface located away from it has a cross sectional shape that is non-axisymmetric. In another embodiment, the bleed passage comprises an assembly of a plurality deflectors, arranged circumferentially.

Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.

Abstract: A system for asymmetric flow extraction is described and claimed, the system comprising a flow path, a bleed slot in the flow path, a bleed cavity for receiving at least a portion of the fluid extracted from the flow path and a bleed passage in flow communication with the bleed slot and the bleed cavity wherein the bleed passage has at least one deflector having a shape such that the width of the bleed passage cross section varies in a direction normal to the direction of fluid flow in the bleed passage. In another embodiment, the deflector has an aerodynamic surface having a shape such that the flow passage between the aerodynamic surface and a surface located away from it has a cross sectional shape that is non-axisymmetric. In another embodiment, the bleed passage comprises an assembly of a plurality deflectors, arranged circumferentially.

Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.