Abstract: Wind turbine comprising a hub carrying a plurality of blades, the hub being rotatably mounted on a frame, the frame extending forward into the hub, wherein the frame comprises a manhole arranged in an upper side of the portion of the frame extending forward into the hub and the frame being dimensioned such that an average-size adult human can move around through it at least up to the manhole.

Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.

Abstract: A gas or steam turbine is disclosed herein. The turbine may include a throat area formed between adjacent buckets. The turbine also may include a variable throat device associated with at least one of the adjacent buckets. The variable throat device may be configured to vary the throat area between the adjacent buckets for improved part load performance.

Abstract: A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop.

Abstract: A coaxial, dual rotor system includes a first rotor assembly positioned at a rotor axis. A first rotor quill shaft is operably connected to the first rotor assembly at the rotor axis to drive rotation of the first rotor assembly about the rotor axis. A nonrotating static mast extends along the rotor axis through the first rotor quill shaft. A second rotor assembly is positioned at the rotor axis. A second rotor quill shaft is operably connected to the second rotor assembly to drive rotation of the second rotor assembly about the rotor axis. The second rotor quill shaft is coaxial with the first rotor quill shaft and disposed inside of the static mast. A second rotor bearing is positioned between the second rotor assembly and the static mast to transfer loads from the second rotor assembly to the static mast.

Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller. The radial diffuser assembly includes a first arcuate wall and a second wall, and a near axial diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly. The gas turbine includes a gas seal coupled between the second wall and a wall of the near axial diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the near axial diffuser.

Abstract: A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.

Abstract: An object is to provide a turbine housing assembly in which reduction of weight, facilitation of manufacture, cost-cutting, and reduction of heat capacity are further promoted compared to a conventional turbine housing made of sheet metal. A turbine housing assembly includes a plurality of constituent members connected to one another to constitute a turbine housing into which a turbine wheel is inserted. The turbine housing assembly at least includes a scroll part 2 and an exhaust part 8 of a tubular shape having a separate body separate from the scroll part 2. The scroll part 2 is formed by processing a single piece of sheet metal so that, on a back face side of a bottom face part 22 of the scroll part 2, a recess portion 22b on which a through-hole of an exhaust gas outlet 2B is formed and a projecting portion 22a formed by a bottom surface of an exhaust gas flow path 2A projecting toward the back face side are formed, the projecting portion 22a surrounding the recess portion 22b.

Abstract: In accordance with an embodiment, a gas turbine engine is provided having a bearing chamber leak detection system. The gas turbine engine includes a rotatable shaft, a bearing assembly supporting the rotatable shaft, and a plurality of bearing chamber seals surrounding the rotatable shaft creating an annular bearing chamber enclosing the bearing assembly. One or more walls substantially surrounding the bearing chamber create a plenum between the walls and the bearing chamber, and a pressurized air inlet to the plenum is provided. The pressurized air inlet includes an airflow sensor configured and positioned to sense a flow of pressurized air into the plenum, such that airflow at the sensor is indicative of airflow from the plenum into the bearing chamber via one or more of the plurality of bearing chamber seals.

Abstract: Various aspects of the technology provide for reducing noise and vibration in a pressure exchanger for high pressure fluid handling equipment such as a desalination system, by disposing grooves between a seal surface and a port. The groove reduces a hammer effect in moving high pressure fluid to a low pressure port and moving low pressure fluid to a high pressure port. Reduction in the hammer effect, in addition to reducing noise, reduces vibration that can cause deterioration of high pressure fluid handling equipment.

Abstract: A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure. The foil bearing system includes a foil bearing and a self-aligning foil bearing mount to align the foil bearing with an axis of rotation of the compressor and the turbine. A snubber operative to transmit rotor loads to the static structure in parallel with the foil bearing is also disclosed.

Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

Abstract: A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.

Abstract: A turbomachine is made by first providing a stepped shaft having a large-diameter cylindrical portion, an intermediate-diameter cylindrical portion, and a small-diameter cylindrical portion all centered on a common axis. A separately manufactured a one-piece and annular first impeller wheel is then permanently mounted on the large-diameter portion with a back face of the first wheel facing axially toward the intermediate-diameter portion and carrying a rotor bearing half of an axial magnetic bearing. A rotor ring of a radial bearing is then detachably mounted on the intermediate-diameter portion of the shaft, and finally a one-piece and annular second impeller wheel is detachably mounted on the small-diameter portion of the shaft with a back face of the second wheel facing axially toward the first wheel and carrying a rotor bearing half of another axial magnetic bearing.

Abstract: A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing. The first opening extends in a first opening direction which forms an angle with the guide vane direction. The guide vane includes a cover portion including a first material and a core portion which is at least partially enclosed by the cover portion.

Abstract: Provided is a windmill device including a wind tunnel member with a wind tunnel passage and a windmill held rotatably inside the wind tunnel passage of the wind tunnel member. The windmill includes a hub serving as a rotation center, plurality of spokes extending radially therefrom, an approximately annular limb connecting outer ends of the plurality of spokes, and plurality of sailcloth pieces, each sailcloth piece being approximately triangular in shape, one side of each sailcloth piece left as a free end 24a not supported by any of the spokes and the limb. A ratio S2/S1 is 0.9 or more. S1 is a cross-sectional area of the wind tunnel passage. S2 is a wind catching area of the plurality of sailcloth pieces.

Abstract: A support block for a steam turbine casing, a related assembly and apparatus. Various embodiments include a steam turbine casing support block having: a body portion sized to substantially fill a pocket in a steam turbine casing, the body portion having a greater length than a depth or a width; a set of tabs extending from the body portion, each of the set of tabs sized to substantially fill a corresponding slot in the steam turbine casing, wherein the set of tabs are located at a radially outwardly facing wall of the body portion; and a pin hole on a bottom surface of the body portion for receiving a retaining member.

Abstract: A centrifugal pump for a slurry combines design changes with respect to conventional configurations that produce quasi-laminar flow and materially extend the life of the casing. The cutwater clearance of the casing is increased to a range of 0.20 to 0.25 times the diameter of the impeller. The casing includes a redesigned removable annular liner with a diameter increased to at least 1.15 times the diameter of the impeller. The pump preferably also has an axially adjustable wear ring with a diameter increased such that it extends by at least 10% over the diameter of the area of interface between the wear ring and the impeller.

Abstract: The gas turbine engine (S1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided. The flow path surface (31) includes: depression portions (31a) depressed relative to the base surface (32), each depression portion (31a) including at least an area overlapping with a front end (7b1) of each turbine blade (7b), when viewed from a direction of the turbine axis (L); and protrusion portions (31b) protruding relative to the base surface (32), each protrusion portion (31b) being at least part of each area positioned between front ends (7b1) of the turbine blades (7b), when viewed from the above direction.

Abstract: A method and system for shutting down a wind turbine is presented. The method includes determining one or more pitch positions for one or more rotor blades of the wind turbine such that a sum of potential energy and kinetic energy in the wind turbine is minimized. The method further includes pitching the one or more rotor blades from an operating position to the determined pitch positions.