Abstract: A method for detecting and reducing edgewise vibrations in a rotor blade of a wind turbine includes, for a given wind speed, determining a frequency or frequency band at which edgewise vibrations are producible in the rotor blade. The method determines an electrical characteristic of the pitch actuator that correlates to an increased torque required to hold a pitch angle of the rotor blade constant at the frequency or frequency band. During an operational power-production mode of the wind turbine, the electrical characteristic of the pitch actuator is monitored. Upon the electrical characteristic reaching a predefined limit value indicative of edgewise vibrations in the rotor blade, corrective action is initiated by the wind turbine controller to reduce or prevent the edgewise vibrations.

Abstract: A nacelle of a wind turbine comprising a machine carrier which is adapted to be installed on a tower of the wind turbine and to carry a generator and a rotor hub of the wind turbine, a working frame installed on the machine carrier and having one or more working planes, and a nacelle housing which encloses the machine carrier and the working frame for protection from weather influences, wherein the nacelle housing has a nacelle base compartment accessible from the working frame. It is proposed that the nacelle base compartment is adapted to be lowerable relative to the working platform. A wind turbine and a maintenance method is also provided.

Abstract: A safety apparatus for containing an energy release from a rotor sub-assembly, the safety apparatus includes a plurality of containment members. The containment member has an elongate region defining a longitudinal axis; and at least two arms projecting away from the longitudinal axis of the elongate region; and at least one connecting member connected to at least two of the plurality of containment members. In use the at least one connecting member is configured to connect the safety apparatus to the sub-assembly and the plurality of containment members are configured to withstand an energy release from the sub-assembly.

Abstract: An air moving device has a housing with a primary flow path and a secondary flow path that extends from a secondary inlet of the housing and empties into an inner outlet adjacent the primary flow path. An impeller assembly rotates a blade to cause air to enter the housing and flow along the primary flow path. The flow of air through the primary flow path creates a low pressure region at the inner outlet of the secondary flow path, causing air to flow through the secondary flow path and mix with the air in the primary flow path. The mixture of air flows through a downstream portion of the primary flow path having an expanded width compared to an upstream portion of the primary flow path and exits the housing. Stator vanes may extend longitudinally within the housing to cause columnar air flow. The device may be used for destratification of thermal gradients of air within an enclosure, such as a home or warehouse.

Abstract: A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.

Abstract: A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.

Abstract: A variable diffuser includes a backing plate, a shroud, a first divider between the backing plate and the shroud, a first diffuser channel between the backing plate and the first divider, a second diffuser channel between the first divider and the shroud, the second diffuser channel, and a valve controlling flow through the second diffuser channel. The valve moves between a first position and a second position. The first diffuser channel includes a first channel inlet and a first outlet. The second diffuser channel includes a second channel inlet adjacent to the first channel inlet and a second outlet adjacent to the first outlet.

Abstract: A propeller includes a bushing, a propeller body, and a propeller damper. The bushing includes a first cylinder portion surrounding the propeller shaft and a first projection protruding outwardly in a radial direction of the propeller from an outer peripheral surface of the first cylinder portion. The propeller body includes a second cylinder portion surrounding the bushing and a second projection protruding inwardly in the radial direction from an inner peripheral surface of the second cylinder portion. The first and second projections are arranged along a rotation direction of the propeller. The propeller damper includes first and second dampers side by side along an axial direction of the propeller between the first and second cylinders. The first and second dampers are separated from each other by a separation portion, and are individually elastically deformable.

Abstract: An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis and a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. Torque from the rotor disc is transmitted to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the shaft. Torque from the rotor disc is transmitted from the rotor disc to the screwed member when the torque ceases being transmitted from the rotor disc to the shaft. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation.

Abstract: A platform for a wind turbine, the platform including a lift beam for carrying a load of a transport cabin of a tower lift of the wind turbine is provided. By the lift beam being part of the platform, an easier installation of the platform and the lift beam is possible. Furthermore, less components are needed. Another advantage is that the lift beam is installed at a smaller height of the tower where the tower has a larger diameter compared to a conventional lift beam. This increases the available space for lift cables hanging from the lift beam.

Abstract: A centrifugal fan is disclosed and includes a lower case, an impeller and an upper case. The lower case includes a bottom plate and a sidewall. The impeller is disposed on the bottom plate. The upper case is assembled with the sidewall to form an outlet. The upper case is formed by stamping and includes a first plane, an inlet and a grille. When the impeller is rotated, an airflow flowing from the inlet to the outlet is formed. The grille is protruded outwardly from the first plane, and includes a connecting frame and plural ribs. A spacing height is formed between the connecting frame and the inlet. Each rib has a first end connected to the connecting frame and a second end connected to the first plane. A pair of notches are disposed adjacent to two opposite lateral edges of the second end of the corresponding rib, respectively.

Abstract: A fan shroud for a heating, ventilation, and/or air conditioning (HVAC) unit may include an outer wall to couple to a housing of the HVAC unit and an inner wall disposed within the outer wall. Additionally, the inner wall may be air permeable. The fan shroud may also include an acoustic damping material disposed between the outer wall and the inner wall. The fan shroud may encircle a fan of the HVAC unit to reduce noise.

Abstract: A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.

Abstract: A gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides a spline for engaging the bearing package.

Abstract: A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

Abstract: A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.

Abstract: A fluid machine includes: a shaft portion; a shroud surrounding the shaft portion and including an inside surface that forms a flow path-forming surface defining a flow path with the shaft portion; a first propeller rotatably provided in the flow path; a second propeller rotatably provided on a downstream side of the first propeller in the flow path; and a motor including a rotor that is fixed to an outer circumferential portion of the second propeller and that is accommodated in the shroud, and a stator that surrounds the rotor via a clearance and that is fixed in the shroud. A portion of the flow path-forming surface on a downstream side of the second propeller decreases in diameter toward the downstream side, and the shroud includes an inlet flow path that is open at a portion between the first propeller and the second propeller of the flow path-forming surface.

Abstract: A tip shroud may include a platform to couple to an airfoil having a pressure side and a suction side. A front tip rail and a rear tip rail extend radially from the platform with each including a downstream side, an upstream side, and an origin(s). Each of the downstream side and the upstream side of the rear tip rail and the downstream side of the front tip rail has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, Z set forth in a respective table and originating at a selected origin. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, Z values by a minimum rear tip rail X-wise extent expressed in units of distance. The X, Y, Z values are connected by lines to define each respective surface profile.

Abstract: A vacuum pump includes a rotor provided with a plurality of rotor blades and a rotor cylinder portion, a driving portion, a bearing, stator blades, a thread groove stator that is disposed downstream of the stator blades and has an inner peripheral surface facing an outer peripheral surface of the rotor cylinder portion, and a heat insulating wall disposed downstream of the thread groove. The heat insulating wall includes a ring-shaped annular portion, and a substantially cylindrical wall portion extending from an inner portion of the annular portion in the radial direction to the upstream side and forming a flow path on the outer peripheral surface side. A first corner portion is formed between an upstream-side surface of the annular portion and the outer peripheral surface of the wall portion, the first corner portion being formed in an arc shape.

Abstract: A vane arm connection system for a gas turbine engine includes a vane stem having a head with flat contact surfaces; a vane arm having a claw, the claw having opposed arms having inwardly facing surfaces engaging the flat contact surfaces of the head; and a torque transfer member having a body defining an opening for engaging the flat contact surfaces of the head of the vane stem, and at least one arm extending from the body to contact the claw, whereby load from torque is transferred away from the inwardly facing surfaces.