Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Abstract: An aircraft including at least one unducted turbine engine for the propulsion of the aircraft. The turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with respect to the longitudinal axis, each stator blade being defined, in a plane transverse to the longitudinal axis, by an angular position; and at least one aerodynamic obstruction positioned close to the turbine engine. The stator of the turbine engine comprises stator blades having a first chord, referred to as conventional blades, and at least one stator blade having a second chord larger than the first chord, referred to as the elongate blade, said at least one elongate blade being positioned in an interference angular range defined opposite the aerodynamic obstacle, so as to increase the straightening of the airflow from the rotor in the interference angular range.

Abstract: An assembly is provided for a turbine engine. This assembly includes a nozzle structure and a combustor wall. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The nozzle vanes extends radially between and are connected to the first platform and the second platform. The combustor wall includes a plurality of apertures. An upstream portion of the combustor wall is radially between and borders a plenum and a combustion chamber. A downstream portion of the combustor wall is radially between and borders the plenum and a gap. The downstream portion of the combustor wall axially overlaps the nozzle structure with the gap formed by and extending between the combustor wall and the first platform. The apertures extends through the downstream portion of the combustor wall and are aligned with the nozzle vanes.

Abstract: A turbine blade includes a platform, a root section, and an airfoil section extending from the platform to a tip. The airfoil section includes a leading edge and a trailing edge extending from the platform to the tip. A tip wall is at the tip and extends from the leading edge to the trailing edge. A first core passage extends from the root section to the tip wall between the leading edge and the trailing edge. A first tip flag passage extends adjacent to the tip wall from the first core passage to a first flag outlet on the trailing edge. A second tip flag passage extends toward the leading edge from a second flag outlet on the trailing edge and is between the first tip flag passage and the root section. A second core passage extends from the root section to the second tip flag passage.

Abstract: A method of reducing depletion of elements from an airfoil includes disposing a bond coating on the airfoil, where the airfoil comprises cooling channels. The airfoil includes a material that has an initial composition. A cooling hole is machined in the airfoil to contact the cooling channels such that a fluid travelling in the cooling channel may be discharged via the cooling hole. The machining of the cooling hole results in a formation of a depleted region around the cooling hole. The depleted region is depleted of a portion of the initial composition of the airfoil. A top coat is disposed on the bond coat. The airfoil is subjected to a heat treatment at a temperature effective to promote diffusion of elements from a non-depleted region to the depleted region around the cooling hole.

Abstract: A method for redirection of coolant flow is provided. The method includes an identifying step that identifies a hot spot on an exterior surface of a body of a component of a turbine system. A first parameter of the component indicates that a temperature of the exterior surface in the hot spot exceeds a threshold value. Another identifying step identifies a cool spot on the exterior surface. A second parameter of the component indicates that the temperature of the exterior surface in the cool spot is below the threshold value. A reconfiguring step reconfigures a plurality of cooling passages of the component to direct a portion of a coolant from the cool spot to the hot spot.

Abstract: A steam turbine according to at least one embodiment of the present disclosure includes an outer casing. The steam turbine according to at least one embodiment of the present disclosure includes an annular member, which is a single member provided radially inward of the outer casing, and formed in the annular member are a seal region in which a sealing device for sealing a gap between said member and the outer peripheral surface of a rotor is located, a rear-stage-stator-vane-holding region where a rear-stage stator vane is held, and an inner casing region connecting the seal region and the rear-stage-stator-vane-holding region. The steam turbine according to at least one embodiment of the present disclosure includes a front-stage vane ring that is attached to the annular member and that holds a front-stage stator vane.

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

Abstract: An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (?) and a layback surface defining a second angle (?).

Abstract: The present invention is directed to axial-centrifugal contra-rotating compressor system comprising combination of contra-rotating axial compressor stage with a back end centrifugal compressor stage, eliminating stator blades, an inter-stage connecting duct at the entry of the centrifugal compressor and an discharge 5 diffuser at the exit of centrifugal compressor rotor characterized by radial to axial turning annular passage as per the gas turbine engine requirement, favouring reduction in engine size, weight, number of parts, overall engine length and produces a higher-pressure rise and swirl-free discharge towards the combustion chamber. The first low-pressure rotor having at least one axial blading assembly 10 rotates in the direction opposite to the second high-pressure rotor blading assembly comprising of at least one axial rotor and one centrifugal rotor. The blades for axial compressor are adopted of low-aspect ratio configuration for reliable high load stall free operation.

Abstract: A seal of a gas turbine engine includes a rotationally stationary seal element secured to a rotationally fixed component of the gas turbine engine, and a labyrinth seal element secured to and rotatable with a rotational component of the gas turbine engine. The labyrinth seal element includes a seal base, and a plurality of seal fins extending outwardly from the seal base, the plurality of seal fins configured to define a seal interface between the plurality of seal fins and the rotationally stationary seal element to prevent airflow therethrough. A removal face is defined integral to an end fin of the plurality of seal fins. The removal face is configured for application of a removal force thereto to remove the labyrinth seal from an installed position in the gas turbine engine.

Abstract: A pump for transferring molten metal is provided. The pump includes a motor, a base having an impeller chamber, a shaft connected to the motor at one end, an impeller connected to the other end of the shaft and rotatable in the impeller chamber, and a riser disposed on an upper surface of the base. The base includes a shaft opening and an outlet opening in a top surface. The riser assembly has a first open end facing the base. The first open end is dimensioned to encompass the shaft opening and the outlet opening.

Abstract: A centrifugal pump for conveying a fluid is proposed includes a pump housing and a bearing housing fixedly connected with the pump housing. The pump housing includes an inlet nozzle for receiving the fluid, a volute for accommodating an impeller, and an outlet nozzle for discharging the fluid. A shaft is arranged in the pump housing and rotates the impeller about an axial direction. The centrifugal pump is a foot mounted, horizontal overhung pump having two support legs fixedly connected to the volute of the pump housing, and mount the centrifugal pump to a base. A third support leg is fixedly connected to the inlet nozzle and is to be mounted to the base.

Abstract: A turbine vane assembly for a gas turbine engine is disclosed herein. The turbine vane assembly includes a turbine vane including a leading edge, a pressure edge, a suction edge, and a trailing edge, a core defined by the turbine vane, an outer platform end wall connected to the turbine vane, the outer platform end wall defining an interior space, the interior space being in fluid communication with the core, and a plurality of cooling holes formed in the turbine vane, the plurality of cooling holes being in fluid communication with the core.

Abstract: This disclosure describes a tension torsion strap for part of rotor head of a rotary wing aircraft. The tension torsion strap includes, in a direction of a longitudinal axis, a first peripheral area with a connection eye, a central section, and a second peripheral area with a connection eye. The tension torsion strap may be of one-piece made of a multiplicity of joined layers. Improved production and installation is of the tension torsion strap may be achieved by that disclosed in this disclosure, resulting in, among other advantages, more simplified maintenance because the tension torsion strap has an overall asymmetric shape relatively to a transverse axis due to two unequally shaped peripheral areas which cannot be brought into alignment when folding around the transverse axis.

Abstract: An electric water pump includes: a housing in which a cooling water inlet and a plurality of cooling water outlets are formed; a stator provided inside the housing; a rotor that is provided inside the housing and spaced apart from the stator at a predetermined interval in a radial direction; and an impeller provided integrally with an upper portion of the rotor. The electric water pump further includes: a pump body provided between the stator and the rotor, and having a first middle outlet; and a driving device selectively fluidly communicating any one of the plurality of cooling water outlets, and the first middle outlet by rotating the pump body at a predetermined angle.

Abstract: An outer platform leading edge cooling system includes a radially outer platform having a platform leading edge; a hollow cooling channel is defined extending generally longitudinally along the platform leading edge of the radially outer platform; an inlet port located in a radially outer end region of the platform leading edge being fluidly coupled with the hollow cooling channel; and the hollow cooling channel comprising an outlet conduit extending from a cooling channel exit, the outlet conduit being connected in fluid flow communication with a trailing edge cavity.

Abstract: An assembly for an aircraft powerplant includes a first component, a second component, an annular seal element and a third component. The first component includes a first land surface which extends axially along and circumferentially about an axis. The second component includes a second land surface radially opposite the first land surface. The second land surface extends axially along and circumferentially about the axis. The annular seal element extends radially between a first side and a second side. The annular seal element includes a base, a plurality of ribs and a groove. The base includes a seal element surface disposed at the first side that radially engages the first land surface. The ribs are disposed at the second side. Each rib projects out from the base and radially engages the second land surface. The groove projects partially axially into the base. The third component projects axially into the groove.

Abstract: A blade or vane has: an airfoil having an inner diameter (ID) end and an outer diameter (OD) end and having a suction side and a pressure side and a leading edge and a trailing edge; and an inner platform and/or attachment root at the ID end and/or an outer platform at the OD end. At least one of the inner platform, root, and/or outer platform comprises one or more pieces of a first alloy. One or more pieces of a second alloy form a leading edge section of the airfoil. One or more pieces of a third alloy form a trailing edge section of the airfoil. One or more pieces of a fourth alloy form a spar of the airfoil between the leading edge section and trailing edge section and extending into said at least one of the inner platform, root, and/or outer platform.

Abstract: An impeller (1) of a fluid pump according to the present invention comprises: an impeller body (10) having a first shroud (20) and a plurality of vanes (30) provided on the first shroud (20); and a second shroud (50) bonded to the impeller body (10) and arranged opposed to the first shroud (20) in a central axis direction across the plurality of vanes (30). The first shroud (20) has a boss part (40) protruding in the central axis direction. The second shroud (50) has a central hole (53) through which the boss part (40) is inserted in the central axis direction. By a combination of a recessed first groove part (41) formed on an outer circumferential surface of the boss part (40) and a recessed second groove part (54) formed on an inner circumferential surface of the central hole (53), a balance hole (B) penetrating in the central axis direction is constituted.