Abstract: Hydraulic pitch actuation mechanism includes vaned rotor within timing chamber surrounded by annular timing chamber wall within fan hub and variable area and volume retarding and advancing chambers within timing chamber. Timing pocket walls extend inwardly from timing chamber wall and interdigitated with timing vanes extending outwardly from vane shaft of vaned rotor. Hydraulic retarding and advancing fluid passages extend through fan drive shaft and through the fan hub to the retarding and advancing chambers respectively. Fluid passages include annular axially spaced apart retarding and advancing passage discharge sections, annular and axially spaced apart retarding and advancing passage entry sections spaced apart from and aft of retarding and advancing passage discharge sections respectively. Retarding and advancing connecting passage sections extend through fan drive shaft and fluidly connect retarding and advancing passage entry sections to retarding and advancing passage discharge sections.

Abstract: A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

Abstract: A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.

Abstract: A system for controlling the pitch of fan blades of a turbine engine propeller, the system including an actuator secured to a casing of the turbine engine, having a movable portion that is movable in translation relative to the casing, the movable portion being mechanically coupled to a load transfer bearing having an outer ring that is coupled to fan blade pivots so that a movement in translation of the movable portion of the actuator leads to a change in the pitch angle of the fan blades, and at least one locking peg secured to the casing of the turbine engine and suitable, in the event of the actuator malfunctioning, for mechanically locking the load transfer bearing in a position wherein the fan blades are feathered.

Abstract: A system is provided. The system includes a dual piston actuator and valves. The dual piston actuator includes a primary actuator and a protection actuator. The primary and protection actuators move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums. The valves include a first check valve, a second check valve, and a third valve. The third valve operates between a first mode and a protection mode. The second medium is directed to the primary and protection actuators through the first and second check valves by the third valve when the third valve is operating in a protection mode.

Abstract: A bleed valve system comprises a duct, featuring a central longitudinal axis and allowing a main flow of fluid to pass from a first environment at a first static pressure to a second environment at a second static pressure along a bleed direction, a valve comprising a valve member arranged within the duct between the first and second environments and movable to partially obstruct the duct and deviate the main flow of fluid to direct at least a part of it towards a portion of an internal wall of the duct; and an ejector, arranged within the duct, downstream of the valve member and offset from the central longitudinal axis in correspondence of said portion of the internal wall, adapted to supply an additional flow of fluid within the duct to accelerate the main flow of fluid and reduce the second static pressure.

Abstract: A steam turbine includes an inner casing which has an inner casing body in which a first main flow path to which steam is to be supplied from an inner introduction port is defined, an outer casing which has an outer casing body which defines a second main flow path between the inner casing body and the outer casing body and an upper discharge port and a lower discharge port which are in the outer casing body and through which exhaust steam is to be discharged, an upper valve and a lower valve configured to adjust a flow rate of the exhaust steam which has been discharged, and a control unit which can independently control the upper valve and the lower valve.

Abstract: A turbocharger includes a turbine with a housing and a rotor for expanding a first medium; a compressor with a housing and a rotor for compressing a second medium utilizing energy extracted in the turbine during expansion of the first medium. A housing surrounds the turbine housing and/or the compressor housing and/or the bearing housing at least in sections, which housing is at least formed from a first housing section and a second housing section, which are connected to one another via screw connections. On the first housing section, shearing force absorption elements are formed or fastened which extend through the second housing section and in the event that shearing forces occur, absorb the shearing forces and thus relieve the screw connections of the shearing forces.

Abstract: A strut includes a strut passage extending through the strut along a radial length of the strut. A tube is disposed within the strut passage and is spaced from an interior surface of the strut passage. A grommet is disposed about the tube and is in communication with the interior surface of the strut passage. The grommet defines a compressible zone including a hollow space extending radially through the grommet. The compressible zone is disposed between the tube and the interior surface of the strut passage.

Abstract: A gas turbine includes a housing in which combustion gas flows; a rotor section rotatably installed in the housing; and a turbine blade configured to rotate the rotor section by receiving a rotational force from the combustion gas and to be cooled by a cooling fluid flowing in a cooling path, the turbine blade including a tip side provided with tip cooling holes through which a portion of the cooling fluid in the cooling path is discharged from the turbine blade. The tip cooling holes include a first tip cooling hole formed in a pressure surface of the turbine blade, and a second tip cooling hole formed in a suction surface of the turbine blade. The gas turbine can easily maintain a gap between the tip side of the turbine blade and an inner circumferential surface of the housing, preventing degradation of the turbine blade efficiency.

Abstract: An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf.

Abstract: There is provided a fan assembly comprising a motor-driven impeller for creating an airflow and a nozzle comprising a first air outlet. The nozzle defines a bore through which air from outside the fan assembly is drawn by any portion of the airflow that is emitted from the first outlet and which combines with the airflow emitted from the first air outlet to produce an amplified airflow. The fan assembly further comprises a second air outlet arranged such that any portion of the airflow that is emitted from the second air outlet does not draw air through the bore defined by the nozzle thereby producing a non-amplified airflow.

Abstract: A recirculation stage of a radial turbomachine, the recirculation stage has an inner delimiting contour and an outer delimiting contour. The stator vane stage has stator vanes, wherein a difference between a vane construction angle at the leading edge and a vane construction angle at a downstream position defines a redirection angle for each point on the camber line of a respective profile cross section, wherein the stator vanes extend at least along part of the third section, wherein the trailing edges are arranged in the third section, wherein at the trailing edges in the center of the span width the redirection angle is in each case greater than the average overall redirection angle, wherein at both ends of the span width at in each case at least 10% of the span width in each case the redirection angle is smaller than the average overall redirection angle.

Abstract: The disclosure provides a centrifugal fan, including an enclosure, a spacer, and a fan blade rotor. The enclosure includes a top panel, a bottom panel, and a side wall connected between the bottom panel and the top panel. The top panel, the bottom panel, and the side wall together form a first air exhaust vent and a second air exhaust vent. The spacer is disposed in the enclosure, is connected between the bottom panel and the top panel, and spaces a first space in communication with the first air exhaust vent and a second space in communication with the second air exhaust vent in the enclosure. The spacer includes a first opening. The first opening is in communication with the first space and the second space. The fan blade rotor is rotatably disposed in the second space.

Abstract: A turbine vane includes a platform, an airfoil, and a cooling arrangement. The platform has a first surface and a second surface. The first surface and the second surface each axially between a first platform end and a second platform end and each circumferentially extend between a first platform side and a second platform side. The airfoil is connected to the platform and defines a passage outlet that extends through the second surface. The cooling arrangement includes a third wall that is connected to the second surface of the platform. The third wall defines a first outlet and a second outlet.

Abstract: The invention is directed to a turbine having a turbine housing or casing. The turbine housing includes a carrier ring and a ring contour component which is fastened to the carrier ring. The ring contour component has a circumferential flange with which it bears against an annular end face of the carrier ring. At least one hold down is provided which enables the flange of the ring contour component to be releasably fixed against the end face of the carrier ring. The turbine is configured to be part of a micro gas turbine in a combined heat and power cogeneration system.

Abstract: A turbocharger includes a variable vane mechanism includes a unison ring and at least one bearing member that is fixed to the unison ring. The bearing member includes a bearing surface that supports rotation of the unison ring within the variable vane mechanism. The unison ring and the at least one bearing member have independent material characteristics.

Abstract: A nacelle for a wind turbine, the nacelle comprising a roof panel forming an opening into an internal space; a cooling arrangement extending upwards from the roof panel; and a closure movable between an open position revealing the opening and a closed position closing the opening. To enable easy parking of the closure and particularly to enable parking of the closure in a position where it does not occupy a large surface space on the roof panel, the nacelle further comprises a track configured to guide the closure between the open and the closed positions, the track being carried at least partly by the cooling arrangement.

Abstract: A pump includes a closed pump rotor being rotatably housed about a rotational axis in a pump space in a casing and including a shroud, a seal ring being shiftably provided, along the rotational axis, being coaxial with the rotational axis with respect to a cylindrical portion in a center of the shroud, and a shift mechanism configured to exert a shift force in a direction along the rotational axis with respect to the seal ring with rotation of the pump rotor and bring the seal ring into contact with an inner wall of the pump space.

Abstract: A shroud segment (100) for disposition on a blade of a turbomachine is provided, in particular a gas turbine, the shroud segment having a stiffening structure raised above a shroud segment surface (15), the stiffening structure including at least three interconnected ribs (3, 5, 7), and a first end portion of the ribs (3, 5, 7) being connected to an upstream sealing tip (11) of the shroud segment (100), and a second end portion of these ribs (3, 5, 7) being connected to a downstream sealing tip (13) of the shroud segment (100). The angles (W1, W2, W3) between the direction of the axis of rotation (a) of the blade and the longitudinal orientations (21, 23, 25) of the ribs (3, 5, 7), as viewed in the direction of flow (9) through the turbomachine, are between zero degrees and eighty degrees. The present invention also relates to a blade (200) of a turbomachine.