A shroud for a compressor is provided. The shroud may include a first annular portion constructed of a first material, a second annular portion coupled to the first annular portion and constructed of a second material, and a first coating disposed on the first annular portion and constructed of a third material. At least one of the first material, the second material, and the third material may be a different material from at least one other of the first material, the second material, and the third material.

Provided are an impeller and a centrifugal pump that can be simplified in structure and reduced in weight and cost, and that can be integrally molded by a mold or the like. In a centrifugal pump including a housing having an inlet, an outlet and an impeller chamber, an impeller is disposed in the impeller chamber and is rotationally driven by a driving shaft. The impeller includes: a shaft part connected to the driving shaft to rotate about an axis line extending toward the inlet; blades protruding radially outward from an outer periphery of the shaft part; and an annular shroud plate continuous with the blades so as to cover a tip side area of the blades in order to be disposed adjacent to an inner wall of the housing on the inlet side.

A jacket ring assembly for a turbomachine, the jacket ring assembly including a casing part, a jacket ring segment which is adapted to radially outwardly surround a rotor blade ring and to this end is disposed radially inwardly of the casing part, as considered with respect to a longitudinal axis of the turbomachine, and a segmented ring which is circumferentially divided into segments and by which the jacket ring segment is mounted to the casing part, the segmented ring being axially form-fittingly disposed on a form-fitting element of the casing part, for which purpose each of the respective segments of the segmented ring is radially outwardly assembled with the form-fitting element, and the segmented ring forming a supporting seat on which the jacket ring segment is seated and radially inwardly supported with an axially forward end.

Provided is a steam turbine in which, among a plurality of stages thereof, a stage that is disposed furthest upstream is a speed-adjusting stage, at least one stage that is disposed downstream of the speed-adjusting stage is a medium-pressure stage, and at least one stage that is disposed downstream of the medium-pressure stage is a low-pressure stage. The speed-adjusting stage is an impulse stage. The medium-pressure stage is a medium reaction degree impulse stage in which the degree of reaction is a medium degree of reaction of 10-40%. The low-pressure stage is a reaction stage having a higher degree of reaction than the medium-pressure stage.

Provided are an impeller and a centrifugal pump that can be simplified in structure and reduced in weight and cost, and that can be integrally molded by a mold or the like. In a centrifugal pump including a housing having an inlet, an outlet and an impeller chamber, an impeller is disposed in the impeller chamber and is rotationally driven by a driving shaft. The impeller includes: a shaft part connected to the driving shaft to rotate about an axis line extending toward the inlet; blades protruding radially outward from an outer periphery of the shaft part; and an annular shroud plate continuous with the blades so as to cover a tip side area of the blades in order to be disposed adjacent to an inner wall of the housing on the inlet side.

Various embodiments include honeycomb structures including an abradable material, and a method of applying such honeycomb structures to steel components of a gas turbine engine in order to reduce rub damage. Particular embodiments include a honeycomb structure having a plurality of cells, each cell of the plurality of cells including a cell wall surrounding a void, and an abradable material within the void of each cell of the plurality of cells, the abradable material including a metallic alloy and hollow particles.

A jacket ring assembly for a turbomachine, the jacket ring assembly including a casing part, a jacket ring segment which is adapted to radially outwardly surround a rotor blade ring and to this end is disposed radially inwardly of the casing part, as considered with respect to a longitudinal axis of the turbomachine, and a segmented ring which is circumferentially divided into segments and by which the jacket ring segment is mounted to the casing part, the segmented ring being axially form-fittingly disposed on a form-fitting element of the casing part, for which purpose each of the respective segments of the segmented ring is radially outwardly assembled with the form-fitting element, and the segmented ring forming a supporting seat on which the jacket ring segment is seated and radially inwardly supported with an axially forward end.

A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud plate that includes a pressure side edge. The pressure side edge includes a primary contact surface configured to couple against an adjacent tip shroud, and a notch extending at least partially downstream from the primary contact surface.

An axial flow fan includes a generally hollow casing defining an inlet end and an outlet end of the axial flow fan. A diameter of the casing increases from the inlet end to the outlet end. An impeller is rotatably mounted within the casing. The impeller includes a hub and a plurality of fan blades extending from a root located at the hub to a blade tip. A diameter of the blade tip of each of the plurality of fan blades increases from the inlet end to the outlet end. A tip fence is located at the blade tip of at least one of the plurality of fan blades and a length of the tip fence measured perpendicular to the fan blades is greater than a thickness of the at least one of the plurality of fan blades.

A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud plate that includes a pressure side edge. The pressure side edge includes a primary contact surface configured to couple against an adjacent tip shroud, and a notch extending at least partially downstream from the primary contact surface.