Abstract: A component for a gas turbine engine includes an outer surface bounding a hot gas path of the gas turbine engine, and a cooling passage configured to deliver a cooling airflow therethrough. The cooling passage includes a passage wall located opposite the outer surface to define a component thickness and a plurality of protrusions located along the passage wall. Each protrusion has a protrusion height extending from the passage wall and a protrusion streamwise width extending along the passage wall in a flow direction of the cooling airflow through the cooling passage. One or more cooling holes extend from the passage wall to the outer surface. A cooling hole inlet of a cooling hole is located at the passage wall, in a protrusion wake region downstream of a protrusion of the plurality of protrusions.

Abstract: An airfoil, a turbine, and a gas turbine having enhanced cooling performance are provided. The airfoil including a leading edge and a trailing edge may include: a first cooling passage connected to the leading edge; a second cooling passage connected to the trailing edge; a third cooling passage formed between the first cooling passage and the second cooling passage; a plurality of partitions provided in the second cooling passage and configured to partition the second cooling passage into a plurality of portions in a height direction of the second cooling passage; and a perforated plate extending in the height direction of the second cooling passage, and coupled with the partitions to support the partitions.

Abstract: A structure for a trailing edge portion of a rotor blade, wherein the rotor blade has a leading edge, a trailing edge, and opposed upper and lower airfoil profiles each beginning at the leading edge and terminating at the trailing edge. The structure includes an inner core having a generally caret-shaped cross-sectional profile and upper and lower skins adhered to the inner core. The upper and lower skins have respective first and second portions adhered to the inner core, and respective third portions which are adhered to each other and which extend aftward to proximate the trailing edge. An upper pocket is defined by the second and third upper skin portions and the upper airfoil profile, and a lower pocket is defined by the second and third lower skin portions and the lower airfoil profile. The upper and lower pockets are filled with a fairing compound and/or an expandable adhesive.

Abstract: A rotor assembly comprises a first body and a second body extending about a rotation axis. The first body has an inner surface, a seat surrounded by the inner surface, and a groove extending circumferentially into the inner surface. The second body has an outer surface surrounded by the inner surface. An annular gap is defined radially between the inner surface and the outer surface and axially between the seat and the groove. A locking washer is mounted in anti-rotational engagement with the inner surface and the outer surface relative to the rotation axis. A split ring is disposed in the annular gap. The split ring is resiliently expandable radially outwardly under centrifugal load such that expanding the split ring radially against the groove axially deflects the split ring toward the seat relative to the first body and to the second body so as to axially load the locking washer against the seat.

Abstract: A fan having a housing including a front piece that is separable but connectable to a back piece is disclosed. The front piece has a first connecting edge and a downstream edge, and the back piece has a second connecting edge and an upstream edge. The second connecting edge is configured to be connected to the first connecting edge. The fan may include a handle, the handle having a first portion integral with the front piece and a second portion integral with the back piece, the first portion configured to be connected to the second portion. The fan may further include air guide ribs provided on an interior surface of the housing and/or a ramp that starts at a location downstream of the upstream edge of the housing and ends at the downstream edge of the housing.

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: An airfoil piece includes at least one inner ceramic matrix composite ply which defines an internal cavity of an airfoil section and first and second collar projections. At least one inner ceramic matrix composite ply is continuous through the airfoil section and first and second collar projections, first and second platforms at the first and second ends of the airfoil section. The first and second collar projections extend radially past the first and second platforms, respectively. A vane for a gas turbine engine and a method of assembling a vane are also disclosed.

Abstract: Modular assemblies for gas turbine engines such as modular vane assemblies and methods of manufacturing the same. The modular assembly includes a first modular component such as a vane platform having a first mating pocket, and a second modular such as an airfoil. The second modular component includes circumferentially extending first and second surfaces at first and second distal ends thereof, respectively, with the first surface being received within the first pocket when the modular assembly is in the assembled state. The second modular component also includes a coating pocket extending from the first surface to the second surface. The coating pocket is recessed towards an interior of the second modular component with respect to first surface and the second surface, and a thermal barrier coating is included within the coating pocket and not included on the first surface or the surface.

Abstract: The gas turbine engine can have a rotary shaft mounted to a casing via a bearing housed in a bearing housing, for rotation around a rotation axis, a gas path provided radially externally to the bearing housing, a feed pipe having a radial portion extending from an inlet end, radially inwardly across the gas path and then turning axially to an axial portion leading to an outlet configured to feed the bearing housing, the axial portion of the feed pipe broadening laterally toward the outlet.

Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

Abstract: A radial fan (1) or centrifugal blower is provided having a fan housing (2) with a spiral pressure chamber (D) and a rotor assembly (10) comprising an internally axially open bearing tube (20), in which a shaft (40) carrying a fan wheel (30) is mounted with a rotor (50) of a canned motor. An air-guiding channel (L) between a first pressure-chamber region (2a) and a second pressure-chamber region (2b) of the spiral pressure chamber (D) is formed between the bearing tube (20) and the wall (W) of the canned motor, so that an air flow flows through the air-guiding channel (L) from one pressure-chamber region (2a, 2b) to the other and in the process dissipates heat from the bearing tube (20) into the pressure chamber (D).

Abstract: An airfoil for a turbine engine includes an array of pins positioned in an internal cavity of the airfoil, such that cooling channels are defined in the interspaces between adjacent pins. Each pin extends lengthwise from a first airfoil wall to a second airfoil wall and is connected thereto at a first intersection and at a second intersection respectively. The pin has a first cross-sectional shape at a respective intersection and a second cross-sectional shape at an intermediate plane located between the first and second intersections. The first cross-sectional shape includes a closed shape defined by relatively sharp corners and the second cross-sectional shape includes a closed shape defined by relatively rounded corners. A cross-sectional area of the pin at the intermediate plane is greater than a cross-sectional area of the pin at the respective intersection.

Abstract: A wind turbine blade comprises a flexible external skin and an internal support structure, together defining an aerodynamic profile of the wind turbine blade. At least a portion of the internal support structure is adjustable to thereby vary the aerodynamic profile.

Abstract: A blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.

Abstract: A turbine rotor blade includes: a blade body including a pressure surface and a suction surface; and a tip shroud on a tip portion of the blade body, the tip shroud being inclined outward in a radial direction from the pressure surface to the suction surface in an axial direction. The tip shroud includes a fin at a center portion in a circumferential direction, the fin extending radially outward, a pressure-side tip shroud on the pressure surface side, and a suction-side tip shroud. The suction-side tip shroud includes a suction-side contact block at a front edge end of the tip shroud. The pressure-side tip shroud includes a pressure-side contact block at a rear edge end of the tip shroud, the suction-side contact block includes a first surface facing in the circumferential direction, and the pressure-side contact block includes a second surface facing in a direction opposite to the circumferential direction.

Abstract: A shaft seal for an exhaust fan. The seal limits leakage from within an exhaust fan housing around an exhaust fan drive shaft that extends between a rotational power source exterior to the exhaust fan housing and a position within the exhaust fan housing. The seal comprises a plenum generally positioned about the exhaust fan drive shaft at the point where the shaft extends into the fan housing; an auxiliary blower comprising a housing, an internal blade driven by an auxiliary blower drive shaft, and an auxiliary blower drive to rotate the drive shaft where the auxiliary blower drive is operatively associated with the rotational power source such that operation of the rotational power sources causes a rotation of the exhaust fan drive shaft and the auxiliary blower drive shaft; and a duct fluidly connecting the auxiliary blower housing to the plenum.

Abstract: A turbine support structure supports a turbine casing and is configured to be movable when the turbine casing is thermally deformed while a gas turbine is operated, thus preventing a fatigue fracture of the turbine casing from occurring. The turbine support structure includes a pair of supports, each having an upper and lower end, for supporting respective opposite side surfaces of the turbine casing at the upper end of either support; and a movable unit installed at the lower end of each support and configured to movably support the lower end of the support. The movable unit is spaced outwardly from the corresponding opposite side surface of the turbine casing, so that the corresponding support inclines toward the turbine casing and is rotatable. The lower end of each support is rotatably coupled to the corresponding movable unit so that the support is rotatable toward an axis of the turbine casing.

Abstract: A blower assembly includes a fan assembly configured to rotate about an axis and having a fan inlet ring that at least partially defines a fan inlet and a fan outlet. The blower assembly also includes a frame assembly coupled to the fan assembly and a recirculation damper coupled to the frame assembly. The recirculation damper and the fan inlet ring define an axial gap therebetween to reduce recirculation of an airflow discharged from the fan outlet.

Abstract: Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Abstract: Gas turbine unit having an axis parallel to the main gas flow, the gas turbine unit comprising: a blade having a tip; a stator heat shield having an inner surface facing the blade tip; wherein the inner surface of the stator heat shield and the blade tip define a variable clearance depending on the applied thermal condition; wherein the blade tip is configured to have a cylindrical shape along the axial direction in a hot running condition starting from a conical shape along the axial direction in a cold starting condition.