Abstract: A sealing assembly for a gas turbine engine includes a case, a support arm, a carrier, a vane, a seal, and a gasket. The support arm is connected to and extending radially inward from the case. The carrier is connected to an end of the support arm. A portion of the vane is disposed downstream of the carrier. A portion of the seal is disposed within the carrier. The gasket is disposed adjacent to and abutting the seal. The gasket is also positioned partially between the seal and the carrier and partially between the seal and the vane.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes and inner shell and an outer shell. The inner shell includes an inner base portion defining an inlet and a volute portion defining an outer contour of a volute in fluid communication with the inlet. The outer shell circumscribing the volute portion in a radial plane and includes an outer base portion circumscribing the inner base portion. The inner shell includes a first plurality of sheet metal structures joined to one another in the radial plane, the outer shell includes a second plurality of sheet metal structures, and first portions of the second plurality of sheet metal structures surrounding the volute portion are joined to one another in an axial plane transverse to the radial plane.

Abstract: An article includes a ceramic wall that defines at least a side of a passage. The ceramic wall includes a flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. A gas turbine engine is also disclosed. The gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. At least one of the turbine section or the compressor section including the article.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A centrifugal pump including a pump chamber, a wear plate, and a rotatable impeller is disclosed. The wear plate has a suction inlet. The pump chamber includes a high pressure region around the impeller within the pump chamber. The impeller's front face has portion located adjacent the wear plate to form a recirculation zone in fluid communication with the high pressure region. Another portion of the impeller's front face forms a small running clearance between it and a portion of the wear plate. That running clearance is interposed between the recirculation zone and the suction inlet. The wear plate includes plural deflector vanes projecting into the recirculation zone. A portion of the front face of the impeller includes plural pump-out vanes in the recirculation zone. The deflector vanes cooperate with the pump-out vanes to expel abrasive particles and prevent them from collecting and eroding the running clearance.

Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform has an attachment side facing the root and a gas path side facing the airfoil. The platform is arranged between the root and the airfoil and shaped to extend outwardly from the root and the airfoil in order to block migration of gasses from the gas path toward the root when the turbine blade is used in a gas turbine engine.

Abstract: A centrifugal pump for pumping blood includes a housing 2 with a housing main body 20, a blood inlet port 25, and a blood outlet port 26. A rotary body 3 is rotatably accommodated inside the housing main body 20, and a support mechanism 4 supports the rotary body 3. The support mechanism 4 is provided with a rod-like shaft member 5, and a first bearing 6 and a second bearing 7 which respectively and rotatably support end portions of the shaft member 5. The first bearing 6 is provided with a protruding portion 62 which protrudes in an eccentric manner with respect to a rotation center O when viewed from an upstream side of a blood flow, so that the protruding portion shields a counter-rotating, longitudinal side of the shaft member from exposure to the main flow of blood.

Abstract: A turbine wheel assembly adapted for use in a gas turbine engine is disclosed. The turbine wheel assembly includes a disk configured to rotate about an axis during operation of the gas turbine engine, turbine blades coupled with the disk, and heat shields arranged between turbine blades. The turbine wheel assembly includes components optionally made from ceramic matrix composite materials such as the turbine blades and/or heat shields.

Abstract: A submersible well pump assembly has a motor that rotates a drive shaft within the pump. The pump has a number of pump stages, each stage having a diffuser and an impeller. A bushing is fixed for non-rotation within the diffuser. A thrust runner sleeve mounted to the drive shaft has an outer diameter surface in sliding rotating engagement with an inner diameter surface of the bushing. At least one seal ring is mounted to the sleeve in sealing engagement with the drive shaft to block the entry of well fluid particulates between the sleeve and the drive shaft.

Abstract: A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.

Abstract: An apparatus for chordwise folding and locking of rotor systems includes a grip assembly and a harness disposed at least partially within and coupled to the grip assembly. A rotor blade is rotatably coupled to the grip assembly and the harness. The rotor blade has a radially extended orientation and a stowed orientation. A linkage assembly has a first end, a second end and a pivot joint therebetween. The first end of the linkage assembly is rotatably coupled to the harness and the second end of the linkage assembly is rotatably coupled to the rotor blade. A first lock assembly selectively secures the rotor blade to the grip assembly and the harness when the rotor blade is in the radially extended orientation. A second lock assembly selectively secures the rotor blade relative to the harness when the rotor blade is in the stowed orientation.