Abstract: A compressor aerofoil rotor blade for a turbine engine includes: a root portion spaced apart from a tip portion by a main body portion. The main body portion is defined by a suction surface wall having a suction surface and a pressure surface wall having a pressure surface. The suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge. The tip portion comprises a shoulder provided on the pressure surface wall. A tip wall extends from the aerofoil leading edge to the aerofoil trailing edge. A transition region of the pressure surface wall tapers from the shoulder in a direction towards the tip wall. The tip wall includes a squealer defined by a first tip wall region which extends from the trailing edge to a winglet.

Abstract: A steam turbine includes a casing which is dividable and of which both ends are open, and a bundle accommodated in the casing. The bundle includes a rotor, a plurality of diaphragms which can be divided, a bundle casing to which the diaphragm is fixed inside thereof, and a bearing portion fixed to an inside of the bundle casing on an outside of the diaphragm, and a seal portion fixed to the inside of the bundle casing between the diaphragm and the bearing portion. The bundle casing can be attached and detached to and from the casing in a state of holding the rotor, the diaphragm, the bearing portion, and the seal portion.

Abstract: A turbine blade includes an internal vibration damping system having a plurality of unit cells. Each unit cell includes: an impacting structure; and a cavity encapsulating the impacting structure. The cavity, which includes a first hemisphere and a second hemisphere, is disposed within a substrate, which forms an outer casing of the cavity. At least one fluid is disposed in each of the first and second hemispheres between the impacting structure and the outer casing.

Abstract: A vacuum pump and a temperature control device are capable of preventing, with a simple configuration, overheating and overcooling of a pump that are caused due to abnormality in a temperature sensor used to control a heater or a water-cooling solenoid valve that is provided to prevent the deposition of products. Problems such as overheating and overcooling of a heater can be avoided in a case where a temperature sensor system fails and consequently the measured temperature continues to be constant between the upper limit and the lower limit. TMS function controls the measured temperature of the temperature sensor to a target temperature. Thus, if an application such as a target to be heated or a heater capacity is identified, the same cycles of turning ON/OFF of the heater or the water-cooling solenoid valve are repeated, and the upper limit of the time in which the ON/OFF state is sustained continuously is determined.

Abstract: A wind turbine (10) includes a first connecting structure (36) associated with the main shaft (34) fixed to a second connecting structure (40) of a rotor hub (22). A plurality of blades (24) is coupled to the rotor hub (22). A rotor locking disc (32) is carried on the main shaft (34). The rotor locking disc (32) has a peripheral region and a plurality of rotor locking elements (50) in the peripheral region for receiving one or more rotor locking pins (30). The first connecting structure (36) includes at least first and second sets of fastener holes (38a, 38b, 38b?). The first set of fastener holes (38a) is located at a position radially inward of the rotor locking elements (50) and the second set of fastener holes (38b, 38b?) is located between adjacent rotor locking elements (50). The first and/or second set of fastener holes (38a, 38b, 38b?) are used to receive fasteners (39a, 39b) to secure the main shaft (34) to the rotor hub (22).

Abstract: An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.

Abstract: The present invention is an improved wind turbine comprising: a wind turbine wheel having a hub, a rim and a cable extending between the hub and the rim; a set of airfoils rotatably carried by the cable and disposed between the hub and the rim; a cinch attached to the cable and disposed between adjacent airfoils; and, an upturned section included in at least one airfoil in the set of airfoils and disposed at a trailing edge of the airfoil wherein each airfoil has a different angle of attack relative to an adjacent airfoil.

Abstract: An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.

Abstract: The gas turbine engine described includes a first centrifugal compressor, a second centrifugal compressor, and intercompressor pipes extending therebetween. The intercompressor pipes fluidly interconnect an exit of a first impeller of the first centrifugal compressor and an inlet of a second impeller of the second centrifugal compressor. The intercompressor pipes have heat transfer structures on outer surfaces thereof to increase convective heat transfer.

Abstract: A transitioning wind turbine for land or offshore use having a tower base; a wind turbine tower attached to the tower base; a wind turbine attached to the wind turbine tower having a hub and an outer perimeter with spokes disposed between the hub and outer perimeter; a set of vanes carried by the spokes; a generator configured to engage the outer perimeter of the wind turbine and convert a rotational energy of the outer perimeter into power; a lifting tower having a pivot disposed at a proximal end of the lifting tower; a cable attached between the lifting tower and the wind turbine tower; and, wherein the lifting tower is configured to transition from the upright position to the tilted position as the wind turbine tower transitions between the horizontal position to the vertical position.

Abstract: An exemplary section of a gas turbine engine according to this disclosure includes, among other things, a first array of airfoils including a first number of airfoils, and a second array of airfoils downstream of the first array of airfoils. The second array includes a second number of airfoils. The second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.

Abstract: Adjustment and/or drive units that can be used in wind turbines to set the azimuth angle of the wind turbine nacelle or the pitch angle of the rotor blades, wherein such an adjustment and/or drive unit has at least two actuating drives for rotating two assemblies, which are mounted for rotation relative to each other, and has a control device for controlling the actuating drives, which control device controls the actuating drives in such a way that the actuating drives are braced in relation to each other during the rotation of the two assemblies and/or at a standstill of the assemblies. The invention further relates to a wind turbine having such an adjustment and/or drive unit and to a method for controlling such an adjustment and/or drive unit.

Abstract: A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a first cavity, a second cavity, and a rib extending from a suction sidewall to a pressure sidewall and separating the first cavity from the second cavity. The rib includes a central portion, a first edge portion extending from the pressure sidewall to the central portion, and a second edge portion extending from the suction sidewall to the central portion. The rib defines one or more communication openings from the first cavity to the second cavity in the first or second edge portion.

Abstract: A rotor rotation control system for a wind turbine and a control method thereof are provided. The control system includes a rotation unit configured to drive a rotor of the wind turbine to rotate relative to an engine base of the wind turbine, a driving unit configured to drive the rotation unit, and a processor configured to determine a bending moment load switching position on a rotating shaft of the rotor, and output an adjustment instruction to the driving unit based on the bending moment load switching position.

Abstract: A non-occluding intravascular pump comprises a shroud providing an inlet for incoming blood flow and an outlet for outgoing blood flow, wherein the shroud is a cylindrical housing; an impeller positioned within shroud, wherein a central axis of the shroud and impeller are shared; a motor coupled to the impeller, wherein the motor rotates the impeller to causes blood to be drawn through the inlet and output to the outlet, and the motor is centrally disposed and shares the central axis with the shroud and the impeller; and a plurality of pillars coupling the motor to the shroud, wherein the pillars secure the shroud in close proximity to the impeller. Various design features of the pump may be optimized to reduce hemolysis, such as, but not limited to, inlet length, impeller design, pillar angle, and outlet design.

Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

Abstract: A cast component includes a body and a passage defined within the body. The passage includes a first portion, a second portion and a turn portion fluidly coupling the first and second portions. The turn portion includes a first surface and a second surface. A surface anti-freckling element extends through the turn portion of the passage from the first surface to the second surface of the turn portion. The element separates the passage in the turn portion into a first sub-passage and a second sub-passage. The element is formed by an opening in a removable core used during the casting that includes a surface anti-freckling opening at the location of the element that provides a path for low-density liquid alloy to flow through a core turn portion of the core to reduce surface freckling of the passage in the body of the component.