Abstract: A rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width in the circumferential direction.

Abstract: A powertrain for a wind turbine (100) comprises at least a first powertrain component (21, 22, 23, 26) and a second powertrain component (21, 22, 23, 26). A rotating output of the first powertrain component (21, 22, 23, 26) is coupled to a rotating input of the second powertrain component (21, 22, 23, 26) and a powertrain housing enclosing the powertrain components (21, 22, 23, 26), the powertrain housing comprising at least a first powertrain housing section (211, 221, 231, 261) enclosing at least part of the first powertrain component (21, 22, 23, 26) and a second powertrain housing section (211, 221, 231, 261) enclosing at least part of the second powertrain component (21, 22, 23, 26).

Abstract: An oil passage of a centrifugal compressor includes a first oil passage that communicates with an oil pan and a speed increaser chamber to supply oil to a speed increaser and the seal. A second oil passage communicates with the speed increaser chamber. A third oil passage extends upward in a gravitational direction from an end of the second oil passage. A fourth oil passage extends in a horizontal direction and causes the oil pan and an end of the third oil passage to communicate with each other. A pressure relief passage that communicates with an outside is arranged in at least one of a portion of the fourth oil passage through which a gas layer passes and a portion of the oil pan in which the gas layer is stored.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes an exterior monolithic ceramic shell and an interior CMC liner that has CMC plies. An outermost ply of the CMC plies forms tabs that are raised from an underlying ply so as to define a slot. The exterior monolithic ceramic shell includes an underlapping shell piece and an overlapping shell piece. The underlapping shell piece has a portion disposed in the slot and bonded with the tabs. The overlapping shell piece extends over the tabs and is bonded to the tabs. There are channels bounded by adjacent ones of the tabs, the underlapping shell piece, and the overlapping shell piece. Channel orifices through the CMC liner connect the cavity and the channels.

Abstract: A vane for a gas turbine engine includes an airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side that bound an internal cavity. The airfoil section has associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure. The airfoil wall has a single rib connecting the pressure side and the suction side. The single rib is aligned with the aerodynamic load vector.

Abstract: The present invention relates to a wind tower (10) for delivering wind flow to a turbine. The wind tower (10) including includes a support structure (12) mounted to a support surface (14) and a wind intake section 16 rotatably mounted to the support structure (12) and elevated with respect to the support surface (14). The intake section (16) includes a plurality of internal passageways (32) extending between a plurality of wind-facing inlets (22) and a plurality of outlets (34). The plurality of inlets (22) are orientated for concurrently receiving an oncoming wind-flow W. Each of the inlets (22) are in fluid communication with one of the outlets 34 via one of the passageways (32). The wind tower (10) further includes an output passageway (42) for collecting wind flow W from the plurality of outlets (34).

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.

Abstract: A wind turbine system comprising a nacelle mounted on a tower, a rotor having a plurality of blades and a boundary layer control system configured to control airflow through blade surface openings in each of the blades. The wind turbine system includes a control system configured to perform at least one of the following: to monitor an operational speed parameter of the wind turbine, and to activate the boundary layer control system if it is determined that the 1 operational speed parameter exceeds a predetermined speed parameter threshold; to monitor tower motion and to activate the boundary layer control system based on a determination of excessive tower motion; to monitor for a wind turbine shutdown condition, and to activate the boundary layer control system if it is determined that a wind turbine shutdown condition has been identified; and to monitor the aerodynamic loads on the blades, and to activate the boundary layer control system also based on a determination of excessive blade loads.

Abstract: A centrifugal compressor includes a volute base block, a volute cover plate, an impeller, a diffuser-adjusting assembly, a radial constraint assembly, an axial constraint assembly and a driving assembly. A diffuser and a connected volute are formed between the cover plate and the base block. The impeller discharges gas to the centrifugal compressor through the diffuser and the volute. The diffuser adjustment assembly includes a driving ring, a driving rod, a pin and a diffuser ring. The radial constraint assembly is disposed on an inner circumference surface of the driving ring. The axial constraint assembly on an outer circumference surface of the driving ring is located between the top and bottom portions. The drive assembly is to rotate the driving ring. When the driving ring rotates, the pin slides along the pin track, and the driving rod displaces the diffuser ring to adjust a flow-path width of the diffuser.

Abstract: A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.

Abstract: Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a number of comb elements, a comb element including comb teeth arranged in a comb plane, wherein the comb plane of a mounted comb element is essentially perpendicular to the trailing edge of the rotor blade and to the airfoil surface of the rotor blade. A wind turbine rotor blade including at least one such aerodynamic structure, and a method of equipping a wind turbine rotor blade with such an aerodynamic structure, is also provided.

Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a part on the input shaft on the input side of the gearbox device.

Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.

Abstract: The present disclosure relates to a downhole centrifugal pump system designed to include a diffuser configuration which optimally transfers fluid and builds head pressure at a dead zone between the diffuser and an adjacently upper impeller, the dead zone being defined as an open rotational area between the stationary diffuser and the adjacently upper impeller. The diffuser includes a first side for receiving fluid from a first impeller and a second side for transferring the fluid upwardly to the adjacently upper impeller. The diffuser also includes a plurality of vanes that direct fluid flow from the first side to the second side. Each vane of the diffuser includes an edge at the second side that includes a bulge between a proximal edge and a distal edge on the second side. The bulge advantageously extends upwardly toward the second impeller to reduce the dead zone relative to if the second edge extended linearly from the proximal edge to the distal edge.

Abstract: A gas turbine engine for an aircraft includes an engine core, a fan and a gearbox which receives an input from a turbine shaft and which outputs drive for the fan for driving the fan at a lower rotational speed than the turbine shaft. The gearbox has a sun gear which is driven by the turbine shaft. The turbine shaft and the sun gear form a spline connection which is lubricated with oil. The turbine shaft has, on its radially inner side, at least one indentation which is suitable for receiving oil, and the turbine shaft has at least one bore which extends from the indentation to the radially outer side of the turbine shaft and which is suitable for transporting oil from the at least one indentation to the radially outer side of the turbine shaft as the turbine shaft rotates.

Abstract: A fan assembly includes a shrouded fan rotor (18) having a plurality of fan blades (22) extending from a rotor hub (24) and rotatable about a central axis (20) of the fan assembly and a fan shroud (26) extending circumferentially around the fan rotor (18) and secured to an outer tip diameter of the plurality of fan blades (22). A stator assembly (28) is located downstream of the fan rotor (18), relative to an airflow (14) direction through the fan assembly. The stator assembly (28) includes a plurality of stator vanes (30) extending between a stator hub (32) and a stator shroud (34). A flow control ring (36) is positioned between the fan rotor (18) and the stator assembly (28) to block radial flow migration in an axial spacing between the fan rotor and the stator assembly resulting from a radial flow component of an airflow (14) exiting the fan rotor (18).

Abstract: A method for manufacturing a wind turbine blade that is pre-staged for subsequent retrofitting with a replacement blade tip segment includes providing the wind turbine blade with a continuous spar structure from a root end to a tip end of the wind turbine blade. At a pre-defined span-wise location, one of a span-wise extending beam structure or span-wise extending receiver section is configured with the spar structure.

Abstract: A fan blade containment system is arranged to surround a fan including a plurality of fan blades in a gas turbine engine for an aircraft. The fan blade containment system includes a fan case arranged to surround the fan; a debris retainer, such as a front hook, mounted on the fan case and arranged to prevent forward debris release should all or part of a fan blade become detached from the fan; and a front panel mounted on the fan case adjacent to and rearward of the front hook, and arranged to move or break when struck by a detached fan blade or fan blade part so as to allow the detached fan blade or fan blade part to engage the front hook.

Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.