Abstract: A rotary pump for conveying a fluid, includes a pump housing, a pump shaft, a hydraulic unit, a mechanical seal, and a stator. The hydraulic unit conveys and pressurizes the fluid, includes an impeller fixedly mounted on the pump shaft, and during operation generates an axial thrust to act on the pump shaft. The mechanical seal seals the pump shaft and includes a rotor connected to the pump shaft in a torque proof manner. The stator is stationary with respect to the pump housing. The mechanical seal is arranged between the hydraulic unit and an end of the pump shaft, and is a balancing device configured to generate an axial force on the pump shaft during operation, with the axial force configured to counteract the axial thrust.

Abstract: A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4) that forms a wave (W) having a specific three-dimensional waveform.

Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is disposed radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features defining a purge airflow. A heat shield is positioned immediately downstream of the first seal and is configured in relation to the first seal such that the purge airflow enters a mixing plenum defined between the heat shield and the first seal.

Abstract: A turbomachine component has a wall outer surface and an internal coolant source. A film-cooling hole is in the wall and extends from the internal coolant source to the wall outer surface. The film-cooling hole includes a metering section in fluid communication with the internal coolant source, and a diffuser section in fluid communication with the metering section and including a first internal surface spaced from a second internal surface. A coating collector receives part of a coating and is part of the diffuser section. The film-cooling hole also includes a hood section including a member extending outwardly from the wall outer surface. The member may include a hood internal surface contiguous with the first internal surface of the diffuser section and a hood outer surface parallel to the wall outer surface. The hood section reduces, and possibly prevents, the coating from filling the film-cooling hole during application thereof.

Abstract: An airfoil journal bearing including a bearing housing having an inner surface forming a hollow so that a rotation shaft is insertable in the hollow; an airfoil in the hollow so that, when the rotation shaft is inserted in the hollow, the airfoil encloses at least 180 to 360 degrees of a circumference of the rotation shaft; and a ring member enclosing an outer surface of the bearing housing. The bearing housing includes an insert slit formed through the bearing housing from the inner surface of the bearing housing to the outer surface of the bearing housing. The airfoil includes an insert part bent from a circumferential direction of the airfoil to a radial direction of the bearing housing and extending, through the insert slit, to the outer surface of the bearing housing. The airfoil is engaged with an outer surface of the ring member through the insert part.

Abstract: A turbine blade includes a blade body, a division plate, a plurality of first protruding ridges, a plurality of second protruding ridges, a first jet hole group, and a second jet hole group. The blade body includes a suction-side wall surface and a pressure-side wall surface, which are provided with multiple film cooling holes. The stagnation region at the leading edge of the blade body is provided with multiple film cooling holes. The first and second jet hole groups are provided on the division plate. The first protruding ridges are provided on a suction-side inner wall surface, and the second ridges are provided on a pressure-side inner wall surface. An engine including the turbine blade is further provided.

Abstract: Electric submersible pump and other centrifugal pump stages having non-axisymmetric components and passage contours are disclosed. Such a component can be a shrouded impeller having a non-axisymmetric profile for its hub and/or shroud.

Abstract: A bonded body wherein functional base material is attached to object to be bonded. Functional base material and object are bonded with functional base material's end portion covered so operational effect neither lost nor adversely affected by fluid, bonded body has strong bonding property preventing functional base material peeled off due to weather. Peelability allows functional base material repair ease. Functional base material provided on object's curved surface to be bonded to along curved and/or smooth surface of object to be bonded to along smooth surface. Functional base material has peripheral side surface with peripheral distal-most end portion. Peripheral gap part provided between object to be bonded to and functional base material on inside of peripheral distal-most end portion and on side opposing to object to be bonded to. Peripheral gap part filled with holding member extending in laminar fan shape from peripheral side surface along curved and/or smooth surface.

Abstract: Stator structure (22) extending around an axis of the turbomachine and comprising: —a support (50) having an inner surface centred on the axis and—a flange (60) defining an air chamber (A2) and having an outer surface centred on the axis, the support (50) extending around the flange (60) such that the inner and outer surfaces are opposite to each other, the structure (22) defining an oil circuit and an air circuit which are formed by upstream channels (64, 65) and downstream channels (54, 55), —each upstream channel (64, 65) defining an outer opening in the outer surface, —each downstream channel (54, 55) defining an inner opening in the inner surface, each circuit being oriented between the outer and inner openings in a direction comprising a component radial to the axis.

Abstract: A monitoring system for monitoring a time period of a locking state of a rotor of a wind turbine includes at least one motion sensor and at least one computing unit, wherein the computing unit is configured to receive at least one motion measurement from the at least one motion sensor and wherein the computing unit is configured to determine whether the rotor may remain in the locking state or the rotor should be unlocked based on the at least one motion measurement. A wind turbine having the monitoring system and a method for monitoring a time period of a locking state of a rotor of a wind turbine is also provided.

Abstract: A turbine rotor blade includes a leading edge portion having a plurality of cooling holes. The plurality of cooling holes includes: m cooling holes arranged in a first range in the blade height direction, where m is an integer of 2 or more; and n cooling holes arranged in a second range on the blade tip side of the first range in the blade height direction, where n is an integer of 2 or more, and n/b<m/a is satisfied, where a is the dimension of the first range in the blade height direction, and b is the dimension of the second range in the blade height direction.

Abstract: A wind turbine blade assembly, includes a wind turbine blade and a lightning protection system including an internal down conductor inside the wind turbine blade and multiple air termination devices having a receptor, which is electrically conductively coupled to the down conductor, wherein the length of the wind turbine blade assembly is divided into a first part having the internal down conductor and spanning from the blade root to at least one first air termination device and a second part spanning from the first air termination device to the assembly tip, wherein the lightning protection system further includes a second air termination device in the second part, and an external, electrically conductive strip extending between a pair of a first and a second air termination devices in the second part and being electrically conductively coupled to their receptors.

Abstract: A turbine vane includes an airfoil having a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, and an outer shroud disposed opposite to the inner shroud at the other end of the airfoil to support the airfoil, wherein a corner part is formed at a portion where the airfoil and the inner shroud or the outer shroud meet, the corner part including a first round portion connected in an arc shape to the inner shroud or the outer shroud, a first inclined portion connected to the first round portion and outwardly extending in an inclined shape, and a second round portion connected to the first inclined portion and outwardly extending in an arc shape.

Abstract: A sealing device according to at least one embodiment includes not less than three arc-shaped fins arranged in an axial direction. The arc-shaped fins include: a first fin which is one of two outermost fins located on an outermost side in the axial direction; a second fin disposed adjacent to the first fin in the axial direction; and at least one third fin disposed opposite to the first fin across the second fin in the axial direction. It is preferable that the third fin is disposed to be inclined with respect to a radial direction such that a tip end portion is located on a side of the first fin in the axial direction relative to a base end portion, and the third fin has a larger inclination angle than the first fin or the second fin with respect to the radial direction.

Abstract: A wind turbine comprising: a vibration source; a component arranged to receive a vibration from the vibration source, the component having a first resonant frequency; and a resonator module arranged to vibrate with a first wavelength when excited at the first resonant frequency, the resonator module being operably coupled to the component at a first location, wherein the resonator module has a first length extending from the first location to a first free end of the resonator module, and wherein the first length of the resonator module is a quarter of the first wavelength.

Abstract: A method for compensating an imbalance of a wind rotor of a wind turbine includes applying at least one test-offset to a parameter characterizing a state of the wind rotor, wherein the imbalance depends on the parameter; measuring for the at least one test-offset an acceleration of the wind turbine, wherein the acceleration depends on the imbalance; and determining a compensation-offset based on the measured acceleration, wherein the imbalance is at least partially compensated, when the compensation-offset is applied to the parameter. Furthermore, a corresponding wind turbine includes a control unit configured to carry out the above method.

Abstract: Disclosed herein are an airfoil, and a turbine blade and gas turbine including the same. The airfoil includes a first cooling passage allowing a first cooling fluid introduced from the bottom of a leading edge to flow into a first serpentine channel formed on a pressure side, and to be then discharged to the rear of a trailing edge, and a second cooling passage allowing a second cooling fluid introduced from the bottom of a suction side to be divided and flow into at least two second serpentine channels formed on the suction side, and allowing the divided cooling fluids introduced into the at least two second serpentine channels to be joined at the bottom thereof and to be then discharged to the rear of the trailing edge.

Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is positioned radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features. A bifurcation feature is positioned downstream of the first seal. The bifurcation feature is configured to direct a portion of an airflow through the first seal into a cooling air passage. A second seal contacts the bifurcation and the first seal, such that fluid radially inward of the bifurcation feature.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.

Abstract: A sensor signal produced by a sensor as a feedback device rotates with a propeller about an axis and moves along the axis with adjustment of a blade angle of the propeller is received, the sensor signal indicative of a rotational speed and of the blade angle of the propeller. From the sensor signal, it is determined whether the rotational speed is within a predetermined range of a reference speed and an expected change in the blade angle has occurred in response to a command to adjust the blade angle to maintain the rotational speed at the reference speed. In response to determining that the rotational speed is within the predetermined range of the reference speed and the expected change in the blade angle has failed to occur in response to the command, inoperable movement of the feedback device along the axis is determined and an alert is output.