Abstract: A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.

Abstract: In the application disclosed are a wind shroud, which is used in a fan with a movable impeller, and a fan with the same. The wind shroud is integrally formed and comprises a body configured to be internally hollowed in an axial direction of the body for receiving the movable impeller. The body comprises an air inlet end and an air outlet end, and the air inlet end has an inner sidewall and an outer sidewall spaced apart from each other to form a silencing cavity for buffering the vibration generated when the movable impeller is rotated, so as to reduce the noise of the fan. In a direction from the air inlet end to the air outlet end, a distance between the inner sidewall of the air inlet end and the outer sidewall of the air inlet end first gradually increases, and then gradually decreases. In the above manner, where the wind shroud of the present application is applied to a fan, the noise problem of the fan can be effectively addressed.

Abstract: A propellant force generator is provided having the size in the axial direction of a rotational shaft of a motor reduced while making the pitch angles of rotational blades driven by the motor variable. The propellant force generator includes a propellant-force generating motor adapted to generate a propellant force for rotational blades, a pitch varying motor adapted to generate a rotational motion for changing pitch angles of the rotational blades, a rotation-linear motion converting unit adapted to convert the rotational motion generated by the pitch varying motor into a linear motion, and a linear motion-rotation converting unit adapted to convert the linear motions converted by the rotation-linear motion converting unit into rotational motions. At least a part of the linear motion-rotation converting unit is located within the propellant-force generating motor.

Abstract: A fan includes a hub and a plurality of fan blades. The hub has an axle center. The fan blades are disposed around the hub. Each of the fan blades has a bent portion, and the bent portions of the fan blades are extended along a surrounding direction surrounding the axle center. The hub is welded with the bent portion of each of the fan blades along the surrounding direction. As a result, the number of fan blades is maximized, the strength is simultaneously ensured to be enough, and the advantages of effectively enhancing the fan characteristics are achieved.

Abstract: A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.

Abstract: A blower assembly for a heating, ventilation, and/or air conditioning (HVAC) system includes a centrifugal fan having a fan wheel. A plurality of blades are coupled to the fan wheel at an inner blade boundary and extend radially to an outer blade boundary. The blower assembly includes a first housing panel and a second housing panel disposed on opposite sides of the centrifugal fan and extending transverse to the centrifugal fan. The blower assembly includes a wall extending between the first housing panel and the second housing panel and a flange extending from the wall at a vertex. The flange extends outwardly from the wall. A first radial distance from the vertex to the outer blade boundary is between 4 percent and 20 percent of a second radial distance from a rotational axis of the centrifugal fan to the outer blade boundary.

Abstract: A centrifugal pump includes an impeller that is rotatable about a rotational axis. The impeller includes impeller vanes disposed between a base plate and a shroud. The shroud outer surface includes recessed pump out vanes. For each pump out vane, the ratio R1 of the vane outer diameter to the shroud outer diameter is in a range of 0.8 to 0.98, the number of vanes N is in a range of 5 to 9, the ratio R2 of the width of the pump out vane to the shroud outer diameter is in a range of 0.02 to 0.04 and the pump out vane has a square leading edge profile with a square or chamfered trailing edge profile.

Abstract: An upstream space forming portion of a centrifugal blower has a space division portion that divides an upstream space into an inner connection space and an outer connection space. The outer connection space has an overlapping space that overlaps the space division portion in an axial direction, and a non-overlapping space excluding the overlapping space from the outer connection space. A suction port has an outer overlapping portion located outside the separation cylinder in a radial direction, and an outer non-overlapping portion excluding the outer overlapping portion from the separation cylinder located outside in the radial direction. A relationship S1/S2?0.5 is satisfied when a first area S1 is defined by projecting a boundary between the overlapping space and the non-overlapping space in the radial direction, and a second area S2 is defined by projecting the outer overlapping portion in the axial direction.

Abstract: A submersible pump comprises a rotational assembly and a rotational assembly housing. The rotational assembly has a plurality of in-line flow inducing sections. A centerline longitudinal axis of each of the flow inducing sections extends colinearly with a rotational axis of the rotational assembly. A downstream end portion of a flow pressurizing section is engaged with an upstream end portion of a rotational flow amplification section. A downstream end portion of the rotational flow amplification section is engaged with an upstream end portion of a flow outlet section. The rotational assembly housing has an interior space extending along a centerline axis of the rotational assembly housing. The rotational assembly is disposed within the interior space of the rotational assembly housing. The rotational assembly and the rotational assembly are jointly configured for causing the rotational axis to extend colinearly with the centerline longitudinal axis of the rotational assembly housing.

Abstract: Various embodiments are provided herein for a system and method for air compression. In at least some embodiments provided herein, there is provided a compressor device having an annular chamber, at least one inlet port, at least one blade, at least one dynamic partition wall and at least one outlet, wherein when the at least one partition wall is in a closed position, the at least one blade approaching the at least one partition wall causes the air to compress and wherein when the at least one partition wall is in the open position, at least one blade moves from a first side to a second side of the at least one partition wall. The compressor device may contain a gearbox train configured to move the at least one partition wall from the closed position to the open position when the at least one blade is within a predetermined distance.

Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A fan with airfoil blades is provided for a regenerative air vacuum street sweeper. The blades are formed using cut and pressed upper and lower panels which are welded at a forward edge to a rod to form the airfoil leading edge and welded at the rear edges to form the airfoil trailing edge. Pins extend laterally outwardly from the rod for mounting each blade in corresponding holes in the front and rear plates of the fan housing. The side edges of the blade are welded to the plates at a 9-11° angle of attack. The airfoil blades allow for reduced size, horse power, noise, and manufacturing and shipping costs.

Abstract: An inertial particle separator (IPS) duct assembly is disclosed having a duct having an inlet section extending downstream from an intake flow opening for receiving airflow to a junction, a scavenge flow section and a core flow section, the scavenge flow section and the core flow section splitting from the inlet section at the junction, the scavenge flow section having a scavenge flow outlet downstream of the junction, the core flow section having a core flow outlet downstream of the junction and fluidly connectable to the air intake of an engine core. A splitter cartridge is removably mounted at the junction, the splitter cartridge including a splitter body extending between a duct wall of the scavenge flow section and a duct wall of the core flow section.

Abstract: A silencing device and a compressor having the silencing device are disclosed. The silencing device has a housing. An air inlet and an air outlet are provided to the housing. An air flow channel is provided in the housing for allowing air communication between the air inlet and the air outlet. An oil hole is provided in the housing for discharging oil from the housing. An oil guide part is arranged on the outside of the housing and at a position downstream of the oil hole in the moving direction of the oil, such that the oil drips from the housing after flowing from the oil hole to the oil guide part.

Abstract: A stator structure and a motor are provided, including an air duct housing. A fixing part is coaxially disposed in the air duct housing and configured to install a motor assembly, connecting components disposed between the air duct housing and the fixing part fix a relative position between the air duct housing and the fixing part, a position of a mounting inlet of the fixing part is on the same side as a position of a fan blade assembly of the air duct housing, an end of the fixing part far away from the mounting inlet is provided with a mounting end cover. By setting the mounting inlet of the fixing part and the fan blade assembly of the air duct housing on the same side, processing of surfaces A, B and C can be completed by one processing without secondary processing, therefore ensuring coaxiality and accuracy of the processing.

Abstract: A vibration attenuator has a first spinner configured for rotation about a first axis and a first mass coupled to the first spinner for rotation therewith, the first mass being movable radially relative to the first axis between an inner position and an outer position. An actuator is coupled to the first mass for selectively controlling a radial location of the first mass relative to the axis, and a first motor is configured for driving the first spinner in rotation about the first axis.

Abstract: Some embodiments of the present disclosure provide a shaft sleeve assembly, a blade mounting structure and an air conditioner. The shaft sleeve assembly is configured to connect a blade shaft and a motor shaft and includes: a blade shaft sleeve a first end of the blade shaft sleeve being configured to be connected with the blade shaft; and a motor shaft sleeve, a first end of the motor shaft sleeve being configured with be connected to the motor shaft and a second end of the motor shaft sleeve being connected with a second end of the blade shaft sleeve and at least one of the blade shaft sleeve and the motor shaft sleeve is an injection molded member.

Abstract: An impeller for a disc pump has a drive disc with a connector for joining to a shaft of the disc pump, a driven disc affixed to the drive disc so as to define a space therebetween, and a plurality of wing vanes formed in the face of at least one of the drive disc and the driven disc. The drive disc has a face facing a face of the driven disc. The drive disc extends in generally parallel planar relationship to the driven disc. The plurality of wing vanes radiate across the face toward an outer diameter of one of the drive disc and the driven disc. Each of the plurality of wing vanes has a portion extending outwardly beyond the outer diameter of the drive disc and the driven disc.

Abstract: A method for determining a set of optimal operating parameters for a pumping plant that pumps a fluid medium by a set of multiple pumps connected in parallel includes: determining, from the set of pumps, a set of possible scenarios, each scenario indicating, for each pump in the set, whether the pump is running or not running; optimizing, for each scenario, a set of operating parameters including operating parameters of the pumps that are running according to the respective scenario so that all running pumps together bring a given input mass flow of the medium from a given input pressure to a given output pressure while minimizing a total power consumption of all running pumps, and assigning the found minimum power consumption and the corresponding optimal operating parameters to the respective scenario; and determining, from the set of scenarios, the scenario with a lowest power consumption.

Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.