Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts have a tubular shape.

Abstract: A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade.

Abstract: An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

Abstract: A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

Abstract: A gas turbine engine configured with an engine core. A fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox arranged to receive an input from the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox comprising a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted, the planet carrier having an effective linear torsional stiffness and the gearbox having a gear mesh stiffness between the planet gears and the ring gear. Additionally, the product of the effective linear torsional stiffness of the planet carrier and the gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 5.0×1018N2m?2.

Abstract: Disclosed are a method and apparatus for detecting a yaw-to-wind abnormality. The method includes: acquiring a wind direction deviation angle within a specified time period; calculating a power performance index, wherein the power performance index is a dimensionless number used to characterize power generation performance of a wind turbine; determining an optimal wind direction deviation angle based on the power performance index; determining a current wind direction deviation angle according to probability distribution of the wind direction deviation angle; and if a difference between the optimal wind direction deviation angle and the current wind direction deviation angle is greater than a preset threshold, determining that a yaw-to-wind abnormality is detected.

Abstract: A portable blower assembly includes a cylinder that has an exhaust port integrated into the cylinder. A handle extends around the cylinder and the handle can be gripped by a user for directing the exhaust port toward a vehicle. A blower is rotatably integrated into the cylinder to urge air outwardly through the exhaust port thereby facilitating the air to be directed onto the vehicle for drying the vehicle when the blower is turned on. A heater is integrated into the cylinder such that the heater is in thermal communication with an interior of the cylinder. The heater is positioned between the blower and the exhaust port to heat the air is blown by the blower for enhancing drying the vehicle.

Abstract: A propeller fan includes: a rotation-axis part that serves as a center of rotation; and a plurality of blades provided on an outer circumferential side of the rotation-axis part, the plurality of blades being joined to adjoining blades at leading edges and trailing edges thereof. A first rib projecting towards the center of rotation of the rotation-axis part to surround the rotation-axis part, and second ribs projecting towards the center of rotation to extend from the rotation-axis part toward the first rib are provided on pressure surfaces of the plurality of blades. Among ends of the second ribs in the direction of the center of rotation, the ends distant from the pressure surfaces project away from the pressure surfaces farther than an end of the first rib distant from the pressure surfaces, among the ends of the first rib in the direction of the center of rotation.

Abstract: The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.

Abstract: Pump assemblies may include a pumping unit. The pumping unit may include at least one impeller having an impeller housing with an impeller housing intake end, an impeller housing outlet end and an impeller housing interior extending from the impeller housing intake end to the impeller housing outlet end. An impeller assembly may be disposed in the impeller housing interior of the impeller housing. The impeller assembly may include an impeller hub. At least one impeller screw blade may extend from the impeller hub. An impeller shaft may drivingly engage the impeller hub for rotation of the impeller assembly in the impeller housing interior. The impeller shaft may be configured for driving connection to the power unit.

Abstract: A vacuum pump comprises: a cylindrical rotor; multiple heat insulating pins; and a stator having a cylindrical portion arranged with a predetermined gap in an outer peripheral side of the rotor and a fixing portion to be fixed to a pump base through the multiple heat insulating pins. The heat insulating pins have a lower thermal conductivity than those of the stator and the pump base, and support the fixing portion.

Abstract: A blower assembly for a powered air-purifying respirator (PAPR) assembly includes: a lower housing; an upper housing connected to the lower housing, such that the upper housing and the lower housing collectively define a first interior cavity; a filter configured to filter ambient air drawn into the blower assembly; and a fan. The upper housing and the filter define a pathway for a flow of air into the first interior cavity. The fan is positioned in the first interior cavity such that, when the fan is activated, ambient air is drawn into the blower assembly and travels along the pathway into the first interior cavity for subsequent delivery out of the blower assembly. The lower housing defines an outlet port for directing breathable air out of the blower assembly for delivery to a user (e.g., via a breathing tube interconnecting a headpiece and the outlet port).

Abstract: An assembly for manually rotating a rotor includes a housing enclosing a first shaft and a second shaft accessible through an exterior wall of the housing. The first shaft extends from a first end rotationally coupled to the rotor to a second end selectively engageable with the second shaft. The second shaft includes a thrust plate extending from and rotatable with the second shaft. A spring disposed between the thrust plate and the housing biases the second shaft towards the exterior wall of the housing.

Abstract: A centrifugal heat dissipation fan including a housing and an impeller is provided. The housing has at least one flow inlet. The impeller assembled in the housing and rotating about an axial direction includes a hub and a plurality blades disposed around the hub. The flow inlet is located in the axial direction and faces the hub. Each of the blades has a wing tab next to the flow inlet, and the wing tab extends from a main surface of the blade to another blade. The wing tab has an inclined surface facing toward a periphery of the flow inlet along a radial direction of the impeller.

Abstract: The invention relates to a threaded bearing housing and a side channel blower incorporating the same wherein the threaded bearing housing is installed on the outer casing element of the side channel blower. The bearing housing supports the outer ring of the blower's bearing. The bearing housing location is adjustable radially and along the axial axis of the side channel blower. These adjustments provide a variable positioning of the rotating components of the side channel blower. This adjustment reduces the necessary assembly tolerancing and allows the impeller's blade and the channel between the casing elements in which it rotates to be properly spaced apart for easy and facile installation and efficient operation.

Abstract: A lubricating oil circuit of a turbomachine includes a distribution valve that distributes an oil flow rate among a first heat exchanger and a bypass duct, connected to an oil duct, which is connected to an heat exchanger positioned against a turbomachine fuel passage duct, and includes a gearbox of a rotation speed reducer that lowers a rotational speed of a first rotary fan shaft of the turbomachine relative to a rotational speed of a second low-pressure compressor rotary shaft of the turbomachine or of a second low-pressure turbine rotary shaft of the turbomachine, and a regulation device. The regulation device includes a local regulation loop that generates an oil flow rate distribution control signal and regulates an oil temperature of the oil duct on a temperature setpoint, and a global regulation loop that generates the temperature setpoint as a function of the temperature and of the temperature setpoint.

Abstract: The present disclosure is directed to providing impeller type oil transportation device including; a transport unit provided such that a mixed fluid including an oil is fed on one side; and an impeller provided in the transport unit, the impeller including a core connected to a rotation axis, and wings extending radially from the core and having hydrophilic teeth on an outer surface to transport the mixed fluid including the oil to the other side of the transport unit by rotation, wherein the impeller is provided in the transport unit such that parts of the wings are exposed above a surface of the mixed fluid, to separate the oil adhered to the teeth while the mixed fluid is fed into a space between the adjacent teeth by capillary flow when the wings exposed above the surface of the mixed fluid move on to the mixed fluid by the rotation.

Abstract: An integral fan blade includes a fan blade connecting disk and a plurality of fan blade bodies arranged around and equidistantly surrounding the fan blade connecting disk. The fan blade bodies and the fan blade connecting disk are integrally formed. This design allows the wind angle to cover a cone-shaped area from top to bottom. Under the same specifications, the wind force is relatively larger than ordinary conventional fan blades, and the coverage area is also larger, thus bringing better blowing effect and better use effect to users.

Abstract: A wind turbine includes a blade having a leading edge, a trailing edge, and opposing first and second surfaces extending between the edges. A vortex generator pair includes a base attached to the first surface and first and second spaced apart fins extending outwardly from opposing portions of the base. The fins each have a leading edge, a trailing edge, a suction side and a pressure side. Each of the suction sides have a trailing half and a leading half.

Abstract: Systems and methods for air injection passageway integration and optimization in turbomachinery using surface vortex generation. An airfoil including a leading edge, a trailing edge, a pressure side, and a suction side, and is configured to influence an airflow as it passes from the leading edge to the trailing edge. The airfoil defines an aerodynamic passageway having an inlet on the pressure side and an outlet on the suction side to deliver air from the airflow through the airfoil to the suction side. The outlets are configured to inject the air at areas on either airfoil side targeted due to their propensity to generate undesirable boundary layer growth and associated flow losses. Outlet may also be included in the hub and the shroud of the turbomachine.