A rotor of an aircraft engine has a plurality of blades extending radially from a disc. At least one of the blades has an airfoil, a root and a tip. The airfoil has a crack-mitigating rib extending chordwise along the airfoil. The crack-mitigating rib is disposed radially closer to the root than to the tip.

A centrifugal slurry pump impeller including: a back shroud with opposed inner and outer faces and an outer peripheral edge, a central axis, a plurality of pumping vanes extending from the inner main face of the back shroud, the pumping vanes being disposed in spaced apart relation, each pumping vane including opposed main side faces, a leading edge in the region of the central axis and a trailing edge in the region of the outer peripheral edge of the back shroud with passageways between adjacent pumping vanes, wherein the inner main face of the back shroud along the length of the passageways, leading from the leading edge to the trailing edge, includes a generally planar inner region beginning adjacent the leading edge of the plurality of pumping vanes, and an outer region ending at the outer peripheral edge of the back shroud, wherein the outer region of the inner face of the back shroud includes a lip formation with an apex including a convex surface.

An aerodynamic component having an aerodynamic surface having a first side facing a fluid flow in a flow direction, and a second side opposed to the first side; at least one resonant cavity on the second side of the surface; at least one rib on the first side of the surface and aligned in the flow direction, the at least one rib extending away from the first side of the surface and defining channels on either side of the at least one rib; and at least one perforation connecting a channel on the surface with the at least one resonant cavity.

An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.

A method for processing a seal for a gas turbine engine includes providing a carbon fiber preform, densifying the carbon fiber preform with a carbon matrix to form a carbon/carbon composite ring, and forming a seal by cutting the carbon/carbon composite ring to form at least one seam at which opposed ends of the carbon/carbon composite ring meet.

A cryogenic pump may include a housing and a drive shaft positioned in the housing. The cryogenic pump may include at least one pump stage positioned in the housing, the at least one pump stage comprising an impeller coupled to the drive shaft. The cryogenic pump may include a balance drum coupled to the drive shaft and positioned in the housing. The cryogenic pump may additionally include a motor comprising a rotor slidably coupled to the drive shaft, the drive shaft configured to rotate with the rotor and move in an axial direction relative to the rotor and the housing during operation of the cryogenic pump.

A pump side part for use with a centrifugal slurry pump for pumping a fluid mixture containing particulate matter, the pump side part comprising a main body having a main axis, the main body including a side wall section which extends laterally with respect to the main axis and has opposite facing first and second sides, a plurality of formations on a surface of the second side including an inner formation and an outer formation in spaced relation to the inner formation, the formations being configured so that in use the formations generate a flow of the fluid mixture across the surface which detaches from the surface the particulate matter adjacent thereto.

A device to reduce turbulent flow skin friction uses carbon dioxide, riblets, and suction holes to reduce the overall drag of a body moving in a fluid. A deflector (2) pushes up the boundary layer of the incoming flow on a surface (1). Carbon dioxide is injected into a plenum (3) and ejected through an exhaust slot (4). Riblets of specific dimensions (5) are placed to interact with the carbon dioxide flow that is now the sublayer viscous flow. After passing the riblets, the flow is sucked partly through suction holes (6), preventing flow separation that could increase the form and wave drag.

A pump side part for use with a centrifugal slurry pump for pumping a fluid mixture containing particulate matter, the pump side part comprising a main body having a main axis, the main body including a side wall section which extends laterally with respect to the main axis and has opposite facing first and second sides, a plurality of formations on a surface of the second side including an inner formation and an outer formation in spaced relation to the inner formation, the formations being configured so that in use the formations generate a flow of the fluid mixture across the surface which detaches from the surface the particulate matter adjacent thereto.

A sealing strip element for sealing a gap between two components of a gas-turbine installation, and extends along a longitudinal direction and has a contoured cross section in a ribbed central region. The sealing strip element extends along the longitudinal direction, wherein at least one of the first main surface and the second main surface includes a riffle structure, wherein the riffle structure has multiple teeth extending substantially from the first strip end to the second strip end along a substantially straight line while establishing chutes between them, wherein at least one dam is provided at at least one strip end of the sealing strip element.