Abstract: A fan includes a hub configured to be driven by motor to rotate about a fan rotational axis, blades that protrude radially from the hub and a band that surrounds the rotational axis and connects the tips of the blades. The band includes structurally-reinforcing thickened regions that protrude from outer surface of the band in a direction away from the hub. A thickened region is disposed between respective tips of each pair of adjacent blades. Each thickened portion bridges a knit-line of the band.

Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a bladed rotor rotatable about an axis, and an engine case. The engine case includes an outer duct wall, a first circumferential stiffener, a second circumferential stiffener and a plurality of axial stiffeners. The outer duct wall forms a shroud around the bladed rotor. The first circumferential stiffener extends circumferentially about the outer duct wall. The second circumferential stiffener extends circumferentially about the outer duct wall. The axial stiffeners are arranged circumferentially about the outer duct wall. Each of the axial stiffeners extends axially between the first circumferential stiffener and the second circumferential stiffener.

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: Control systems are described that mitigate the effects of icing events on wind turbines. Example methods include determining, with a control system, that an icing event has begun to affect the wind turbine; based on a determination that the icing event has begun to affect the wind turbine, changing a phase of the wind turbine with the control system to an operational-icing phase by modifying angles of attack of blades of the wind turbine via changing blade pitch angles, wherein the wind turbine continues to generate electrical power when the wind turbine is in the operational-icing phase; and based on a determination that electrical power generation of the wind turbine is below a threshold, changing the phase of the wind turbine with the control system to a stopped-icing phase, wherein rotation of the blades of the wind turbine is halted when the wind turbine is in the stopped-icing phase.

Abstract: Compressors having multi-speed gearboxes are disclosed. The apparatus comprises: a fluid channel to convey a fluid, a compressor fluidly coupled to the fluid channel, a gearbox operatively coupled to the compressor, the gearbox to control the compressor using a first gear ratio and a second gear ratio different from the first gear ratio to vary a flow rate of fluid in the fluid channel, and clutches to vary the gearbox between the first gear ratio and the second gear ratio.

Abstract: A method includes applying a material coating on a surface of a machine component using a thermal spray, wherein the material coating is formed from a combination of a hardfacing material and aluminum-containing particles. The method also includes thermally treating the material coating to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material.

Abstract: A wind power generation facility capable of realizing a lightning strike suppression effect while maintaining power generation efficiency by maintaining a blade shape that greatly affects power generation efficiency. An erected support column, a generator G provided at an upper portion of the support column, a hub H provided on a drive shaft that rotationally drives the generator, a plurality of blades radially provided to the hub about the drive shaft, charged bodies provided at tips of the blades, and a capacitor provided in an inner space of the hub are provided, and the capacitor includes a first electrode body that is grounded and a second electrode body that faces the first electrode body with an electrically insulating layer interposed therebetween and connected to the charged bodies.

Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.

Abstract: A gas turbine engine includes a fan section that includes a fan drive shaft. A star gear system for driving the fan section has a carrier mounted to a static structure to prevent the carrier from rotating. A ring gear is attached to a ring gear attachment point on the fan drive shaft. A first fan section support bearing supports a fan drive shaft and is mounted forward of the ring gear attachment point. A second fan section bearing supports the fan drive shaft and is mounted aft of the ring gear attachment point on the fan drive shaft. An outer race of the second fan section bearing is fixed relative to an engine static structure.

Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

Abstract: A seal member is disposed between a rotor and a stator to provide a seal between the rotor and the stator. The seal member comprises: a rotary-side member fixed to a surface of the rotor opposing the stator; a fixed-side member fixed to the stator and facing the rotary-side member; and a first fin and a second fin which are disposed on one of the rotary-side member and the fixed-side member, the first fin protruding on the opposing surface side, the second fin being disposed on a lower pressure side in a rotating axis direction relative to the first fin and protruding on the opposing surface side. The thickness, in the rotating axis direction, of the second fin at the root thereof is greater than the thickness, in the rotating axis direction, of the first fin at the root thereof.

Abstract: Provided is a corrosive environment monitoring device capable of monitoring the condition of a turbine for a long period of time without corrosion damage to a sensor caused by turbine steam. A corrosive environment monitoring device 10 includes: a steam extraction part 11 that extracts steam from inside of a casing 21 of a steam turbine 22 to outside thereof; a condensed water storage part 12 that stores therein condensed water produced by condensation of steam passing through the steam extraction part; and a corrosion factor sensor part 13 that detects properties of the condensed water. The condensed water storage part 12 includes a gap simulation part that simulates a gap inside the turbine and has a predetermined gap capable of storing the condensed water therein, and an annular channel formed on an outer periphery side of the gap simulation part.

Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Abstract: Provided is a lightning suppression device for wind turbine blades that is provided at a tip of a wind turbine blade and suppresses lightning struck on the wind turbine blade, the device including: an electrical insulator attached to the tip of the wind turbine blade and formed of a non-conductive material; an internal electrode attached to the electrical insulator on a side opposite to the wind turbine blade; and an external electrode attached to the electrical insulator so as to surround the internal electrode with a predetermined gap therebetween, wherein the electrical insulator is fixed to the tip of the wind turbine blade by a fixing member, and a ground line is connected to the internal electrode.

Abstract: A nacelle for a wind turbine includes a nacelle housing; a rotor hub; a rotor bearing for bearing the rotor hub on the nacelle housing, wherein the rotor bearing has at least one inner ring element and at least one outer ring element, wherein at least one sliding bearing element is formed between the inner ring element and the outer ring element. The sliding bearing element is inseparably connected to the inner ring element or the sliding bearing element is inseparably connected to the outer ring element.

Abstract: A blade for a wind turbine including heating means connected to power cables, a lightning protection system including a down conductor, and surge protection devices is provided. The heating means include a first radiant element and a second radiant element arranged adjacent to each other around a leading edge of the blade, the first radiant element being connected to the power supply cables through respective electrical connectors at the respective connection points, and the down conductor is connected to each power supply cable at the connection points through the respective surge protection device, the second radiant element being connected to the first radiant element so that the second radiant element is electrically supplied only through the first radiant element.

Abstract: A method for providing a wind turbine blade with lightning protection, the method including the steps of: providing a lightning protection cover including a non-conductive medium and a conductive medium embedded in the non-conductive medium, providing a blade body, and attaching the lightning protection cover to the blade body. An effective lightning protection is thus provided.

Abstract: The invention relates to a wind turbine (100) having a rotor (102) rotatable about a vertical axis of rotation (104) having a rotating hub (3) and a plurality of rotor blades disposed along an outer periphery of the rotor (102), each of which have a lower segment (4) and an upper segment (5) attached to an upper distal end of the lower segment (4). The lower proximal ends of the lower segments (4) of the rotor blades are each attached to the rotating hub (3). To form a particularly stable and lightweight platform for the rotor (102) or rotor blades, it is proposed that the lower segments (4) of the rotor blades form an inverted pyramid in conjunction with the hub (3), guy wires (7) and bracing wires (8), wherein the guy wires (7) interconnect first attachment points (6) in the area of the distal ends of the lower segments (4) and the bracing wires (8) connect the first attachment points (6) to the hub (3).

Abstract: One feature pertains to an acoustic attenuation device. The acoustic attenuation device comprises a fan assembly, the fan assembly including at least one fan module that directs airflow in at least one direction, wherein the at least one fan module includes a top surface and a bottom surface, a plurality of air deflectors mounted to the top surface and the bottom surface of the at least one fan module, wherein the plurality of air deflectors include a plurality of surfaces, and wherein at least one of the plurality of surfaces is an angled surface that redirects the airflow 90-degrees, and acoustic attenuating foam, wherein the acoustic attenuating foam has a two-dimensional (2-D) surface and is applied to interior surfaces of the plurality of surfaces.

Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.