Abstract: A centrifugal gas compressor fed with a gas and a processing liquid comprises a rotor rotated by a prime mover. The rotor defines an internal axial cavity with a cylindrical surface, an annular peripheral collection cavity, and a tapered radial channel fluidly connecting the internal axial cavity and the annular peripheral collection cavity. With each rotation of the rotor, a portion of the processing fluid is swept into the inlet of the tapered radial channel and travels radially as a fluid piston under centrifugal force pushing and compressing a column of gas entrained in front of said fluid piston, and is expelled into the annular peripheral collection cavity where it undergoes centrifugal separation, leaving the compressed gas to be drawn off through the compressed gas outlet for downstream use. A method for compressing a gas is also provided.

Abstract: A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

Abstract: [Problem] To provide a flying body having a new structure capable of improving flight efficiency. [Solution] The problem is addressed by a flying body capable of traveling along at least a first direction and comprising an airframe part and an auxiliary part wherein the airframe part has a body part and a lift generating part, the body part having a right part and a left part extending along the first direction and a connecting part whereby the ends of the right part and the left part in a second direction opposing to the first direction are connected. The flying body is thus configured so as to create a surrounded space surrounded by the left part, the right part, and the connecting part when seen from a third direction perpendicular to the first direction.

Abstract: A method for determining a yaw position offset of a wind turbine (1) is provided. A neighbouring wind turbine (2) of the wind farm is identified, the neighbouring wind turbine (2) being arranged in the vicinity of the wind turbine (1). Produced power data and/or wind speed data from the wind turbine (1) and from the neighbouring wind turbine (2), is obtained during a period of time, and a yaw position offset of the wind turbine (1) is derived, based on the obtained produced power data and/or wind speed data, and based on the geographical positions of the wind turbine (1) and the neighbouring wind turbine (2). A local maximum and a local minimum being separated by an angular difference in yaw position being substantially equal to 180°.

Abstract: A portable system for converting wind energy into electrical energy is disclosed. The disclosed system may include a frame hosting one or more conversion modules, arranged as desired. A given conversion module may include one or more wind energy conversion devices (WECDs), arranged as desired. The conversion modules may be electrically connected, directly or indirectly, with one or more downstream electrical energy storage elements (e.g., such as a battery or other capacitive element, optionally native to a host platform). In this manner, the disclosed system may be configured for use in storing and/or supplying electric power for downstream consumption by a host platform or otherwise. In a more general sense, the disclosed system may be utilized, for example, for micro-generation of renewable electrical energy from wind.

Abstract: A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

Abstract: An inner shroud assembly of a variable vane actuation system for a gas turbine engine includes a shroud assembly comprising a multiple of forward shroud segments and a respective multiple of aft shroud segments. A multiple of variable vanes are rotationally retained at an inboard trunion between the forward and aft shroud segments of the shroud assembly. A retainer assembly includes a multiple of retainer ring segments that retain the forward and aft shroud segments together. The inner shroud assembly is assembled into an engine case with an inboard extending feature that engages with an outer diameter feature of each of the multiple of retainer ring segments.

Abstract: A blower (100) includes a blower attachment housing (112), a power head housing (122) having a handle (130) operably coupled thereto, a motor (140) disposed in the power head housing (122), a fan (160) disposed in the blower attachment housing (112), a battery (150), and an intake chamber (174) disposed between the motor (140) and the fan (160) to enable the air to enter the blower (100) between the motor (140) and the fan (160).

Abstract: An engine bi-material joint includes a first flange composed of a first material and defining a first coefficient of thermal expansion, and a second flange composed of a second material and defining a second coefficient of thermal expansion. The second flange is different from the first material. An interface flange is engaged with the first flange and with the second flange. The interface flange defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion of the first flange. The third coefficient of thermal expansion is less than the second coefficient of thermal expansion of the second flange. The first coefficient of thermal expansion of the first flange is less than the second coefficient of thermal expansion of the second flange.

Abstract: Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a throttle ring disposed between stages of the compressor. The throttle ring can allow or obstruct flow through the side stream injection port. The throttle ring can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. A method of operating a centrifugal compressor can include actuating a throttle ring by rotating a drive ring to adjust a flow of interstage fluid into the second stage impeller.

Abstract: An arrangement for monitoring a centrifugal pump is provided. receiving the residual axial thrust of a centrifugal pump. The arrangement includes a load-relieving device configured to receive the residual axial thrust developed during pump operation, an axial bearing, and a sensor ring is associated with the axial bearing. The ring (10) is divided into segments having sensors at the segment dividing regions.

Abstract: A span-wise extending pin for joining blade segments of a rotor blade includes a distal portion having a length defined by a first end and an opposing, second end. The distal portion has a conical shape extending for at least a portion of the length thereof for providing ease of insertion of the pin into a pin joint slot of one of the first and second blade segments. The pin also includes a pin portion adjacent to the distal portion. The pin portion includes a first section and a second section. The second section is configured for securing within a beam structure of the first blade segment. The first section extends span-wise from a receiving end of the beam structure. The pin also includes a proximal portion having at least a rod member that extends span-wise through and secures together the pin portion and the distal portion.

Abstract: A compact and unobtrusive rotor control mechanism is presented that provides collective and cyclic pitch change to both rotors of a coaxial rotor system as well as a differential collective pitch change to one or both rotors simultaneously.

Abstract: A wind turbine, including a main gear box, which is lubricated and/or cooled by oil, and a thermosiphon cooling system for cooling the oil is provided. The thermosiphon cooling system solves the main challenges facing the oil cooling systems in wind turbines. The high efficiency of the evaporation heat transfer mechanism gives the capacity to transfer the required heat load in relatively smaller size system. In this way, installation space is reduced. The thermosiphon cooling system has no service requirements over the lifetime of the wind turbine since the thermosiphon cooling system has no moving parts. Costs are saved since the simplicity of the thermosiphon cooling system adds a big value to the system business case.

Abstract: A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus including a containment member configured to pivot about a pivot location, the containment member including a retaining arm located on a first side of the pivot location and a catch located on a second side of the pivot location, wherein the containment member is movable about the pivot location to a first position in which the catch is engaged with a lip of a disc of the rotor assembly to position the retaining arm in a containment position.

Abstract: A rotor blade retention system for a gas turbine engine includes a rotor blade connection component defining a slot, with the rotor blade connection component including a first set of electric leads. Furthermore, the rotor blade retention system includes a rotor blade having a root section received within the slot, with the rotor blade further including a second set of electric leads. In this respect, the first and second sets of electric leads are electrically coupled together to permit electric current to be supplied to the rotor blade.

Abstract: A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

Abstract: A pump assembly includes at least one rotatingly driven impeller (14) and at least one valve element (18) which is rotatable about a rotation axis (X) between at least two switching positions. The valve element (18) includes a first face side (22) which extends transversely to the rotation axis of the valve element. A suction opening (24), which is engaged with a suction port (26) of the impeller (14), is formed in this first face side in a central region. The first face side (22) includes a pressure surface which surrounds the suction opening (24) and is adjacent to a delivery chamber (28) which surrounds the impeller (14).

Abstract: A phonic wheel having a body and a tooth is disclosed. An embodiment of the phonic wheel includes a body that is configured to rotate about a rotation axis. The tooth is attached to the body. The tooth has a first axial end relative to the rotation axis, a second axial end opposite the first axial end, and a mid portion extending between the first and second axial ends. The mid portion has a substantially axially uniform height from the body. The first axial end has a greater height from the body than the height of the mid portion.

Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.