Abstract: A rotor for an aircraft rotary engine includes a rotor body. The rotor body extends about an axial centerline. The rotor body includes an outer body portion, an annular inner body portion, and ribs. The outer body portion forms a plurality of sides and a plurality of apex portions of the rotor. The annular inner body portion is disposed radially inward of the outer body portion. The ribs extend radially between and connect the outer body portion and the annular inner body portion. The rotor body forms at least a first lubrication passage within the inner body portion and within a first rib of the ribs. The first lubrication passage includes at least one passage inlet and at least one passage outlet. The at least one passage inlet is disposed at the annular inner body portion.

Abstract: A centrifugal compressor comprises: an impeller; an inlet pipe portion forming an intake passage to introduce air to the impeller; and a throttle mechanism capable of reducing a flow passage area of the intake passage upstream of the impeller. The throttle mechanism includes an annular portion configured to move between a first position and a second position upstream of the first position in an axial direction of the impeller. In a cross-section along a rotational axis of the impeller, an outer peripheral surface of the annular portion is formed to smoothly connect a leading edge and a trailing edge of the annular portion.

Abstract: A spiral orbiting wrap of an orbiting scroll is meshed with a spiral fixed wrap of a fixed scroll. A first compression chamber is formed by an inner wall surface of the orbiting wrap and an outer wall surface of a fixed wrap. A second compression chamber is formed by an inner wall surface of the fixed wrap and an outer wall surface of the orbiting wrap. The orbiting base plate of the orbiting scroll includes a first through hole capable of communicating the first compression chamber with the back pressure chamber and a second through hole capable of communicating the second compression chamber with the back pressure chamber. The first compression chamber communicates with the back pressure chamber via the first through hole prior to the communication of the second compression chamber with the back pressure chamber via the second through hole.

Abstract: A rotary engine comprised of a pair of counterrotating rotors within a non-rotating outer housing. Each of the rotors is coupled to a common power shaft, one directly and the other through a reversing gear arrangement. Both are driven by the hyper-expansion of combustion gases in a repeating combustion cycle. Each has a generally circular, nearly frictionless working surface perpendicular to the power shaft axis. Each rotor surface defines chambers which rotate past each other. Within such chambers, compressed air and fuel are introduced, mixed, ignited, allowed to hyper-expand (and thus cause the rotation) and exhausted. The power shaft may be connected to a conventional clutch, torque converter, gearbox, differential, alternator or a similar system.

Abstract: A scroll fluid machine includes: a fixed scroll 11 having a helical wrap 16; an orbiting scroll 12 having a helical wrap 21; a drive shaft 13 that causes the orbiting scroll 12 to orbit relative to the fixed scroll 11; and a helical tip seal 29A inserted into a seal groove 28A of the wrap 21. The tip seal 29A has: a groove 36A that has an opening at a central portion of a sliding surface 30 in the seal width direction; and a communication groove 37A communicating between the inside of the groove 36A and a working chamber SH on the inner side in the wrap width direction. In groove 36A the differential pressure (PH-PL) is equal to or higher than 0.1 Mpa between the working chamber SH and a working chamber SL on the outer side in the wrap width direction.

Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

Abstract: A method for abrasive flow machining includes moving an abrasive media through a high-aspect passage of a workpiece. Local pressure of the abrasive media is increased at target abrasion surfaces of the high-aspect passage using a passage geometry that is configured to direct flow of the abrasive media into the target abrasion surfaces such that the target abrasion surfaces are preferentially polished by the abrasive media over other, non-targeted surfaces of the high-aspect passage at which the flow of the abrasive media is not directed into.

Abstract: A submersible pump assembly. The submersible pump assembly comprises a motor comprising a first drive shaft; a seal section comprising a second drive shaft that is coupled to the first drive shaft of the motor; and a centrifugal pump assembly comprising a third drive shaft that is coupled to the second drive shaft of the seal section and a plurality of pump stages, wherein each pump stage comprises an impeller coupled to the third drive shaft and a diffuser retained by a housing of the centrifugal pump assembly, wherein the diffuser of each pump stage comprises a first plurality of vanes each having a first axial length and a second plurality of vanes each disposed between a pair of vanes of the first plurality of vanes and each having a second axial length, wherein the second axial length is less than the first axial length.

Abstract: The invention relates to a stabilizer channel, in particular of a radial compressor or diagonal compressor, having an annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel and is delimited from the main flow channel by an annular bridge. The annular stabilizer chamber is bladeless and is connected to the main flow channel via a downstream inlet channel and an upstream outlet channel. A plurality of flow directing elements are arranged in the downstream inlet channel. The downstream inlet channel is arranged between an upstream part of the annular bridge and a downstream part of the annular bridge. The invention furthermore relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer channel according to the invention and to a turbocharger comprising the compressor.

Abstract: A double-layer reverse rotation vertical shaft power machine adopting a horizontal combined movable wing relates to the technical field of green energy generating sets, which includes main body devices, movable wing devices, transmission devices and a self-clutch device; each movable wing device includes combined wings vertically arranged along the circumferential direction of the main body devices, each combined wing includes combined shafts and combined movable wings connected to the combined shafts, and the combined shafts vertically arranged along the circumferential direction are alternately arranged according to the axial length. The combined shafts that are alternately distributed along the circumferential direction in turn can effectively stagger the adjacent combined movable wings and avoid the mutual interference between the adjacent combined movable wings, thereby reasonably using all combined movable wings, fully obtaining the outside potential energy and improving the efficiency.

Abstract: A variable cam timing phaser includes a housing disposed about an axis and having an inner housing surface defining a housing interior. The variable cam timing phaser includes a rotor moveable between an advance position and a retard position. The rotor includes a hub and a vane, with the rotor and the housing defining a chamber. The vane further defines the chamber into an advance chamber and a retard chamber. The variable cam timing phaser also includes a control valve assembly including a valve housing and a control piston. The variable cam timing phaser also includes a chamber biasing assembly disposed in one of the advance and the retard chambers and configured to bias the rotor into a predetermined position between the advance and the retard positions. The chamber biasing assembly includes a chamber piston, a chamber biasing member, and a chamber check valve.

Abstract: A method of installing a wind turbine (10) at an offshore location. The wind turbine (10) includes a tower (18) and an energy generating unit (16). The tower (18) is configured to be secured to a transition piece (12, 42). Prior to shipping, the method includes electrically coupling electrical devices and/or systems (52) by cables (54) to energy generating unit (16) or wind turbine tower (18) or a test dummy therefor. The electrical devices and/or systems (52) are configured to be attached to transition piece (12, 42) once the tower (18) is installed. The method includes testing and commissioning the electrical devices and/or systems (52) while electrically coupled to the cables (54). Prior to shipping and after testing and commissioning, the method includes storing the electrical devices and/or systems (52) and attached cables (54) inside the tower (18).

Abstract: A gas-cycle system operable using a Bell-Coleman cycle, the gas-cycle system comprising an expander (23) and a compressor (27) incorporated in a flow path (13). The expander (23) and compressor (27) are integrated in a rotary machine (41), and each comprises a rotor assembly (70) configured to define one or more zones (80) each of which changes continuously in volume during a rotation cycle of the rotor assembly. The expander (23) and compressor (27) are drivingly interconnected whereby rotational drive applied to one is transmitted directly to the other. Each rotor assembly (70) comprises an inner rotor (73) and an outer rotor (75) adapted to rotate about parallel axes at different rotational speeds. The inner rotors (73) are each drivingly connected to a common shaft for rotation therewith. The two outer rotors (75) are coupled together such that rotational drive applied to one is transmitted directly to the other.

Abstract: A modular blade connection structure includes a first module, a second module and a structural adhesive module. The first module is provided on an end face thereof with a bonding flange extending into the second module; a gap between the butting surfaces of the first module and the second module is injected with a structural adhesive, which is extruded and cured to form a structural adhesive module; and the thickness of the first module at the starting end of the bonding flange extends towards the inner surface to form a first reinforcement, and the structural adhesive module extends inside the second module in a direction away from the bonding flange to form a second reinforcement. The present disclosure facilitates the control the bonding quality of the double-sided overlapping of the modular blade by means of the bonding flange and the improvement of the fatigue resistance at the assembling position.

Abstract: A wind turbine blade is provided, which includes a blade body extending from a blade root toward a blade tip along a blade length direction, a first sprayed layer disposed so as to cover at least a leading edge on a side of the blade tip of the blade body, for suppressing erosion of the leading edge of the blade body, a second sprayed layer formed between the blade body and the first sprayed layer, and having a lower electrical resistivity than the first sprayed layer, and a first conductive part for electrically connecting the second sprayed layer to a ground.

Abstract: In a compression unit, an upper compression unit suction tube is connected to an upper suction hole of an upper cylinder, and a lower compression unit suction tube is connected to a lower suction hole of a lower cylinder. In an accumulator shell of an accumulator vessel, an accumulator suction tube, an upper gas-liquid separation tube, and a lower gas-liquid separation tube penetrate a side wall of the accumulator shell, and are fixed by welding to a first through hole, a second through hole, and a third through hole of the accumulator shell, respectively. The upper gas-liquid separation tube is connected to the upper compression unit suction tube via an upper connecting tube outside the accumulator shell. The lower gas-liquid separation tube is connected to the lower compression unit suction tube via a lower connecting tube outside the accumulator shell.

Abstract: Various examples of the present disclosure provide aircraft engine sensing apparatuses and methods of manufacturing aircraft engine sensing apparatuses. For example, an example aircraft engine sensing apparatus includes an aircraft engine sensor, a plurality of connection wires, and at least one ceramic insulator. In some examples, the aircraft engine sensor is positioned within an aircraft engine. In some examples, the plurality of connection wires connect the aircraft engine sensor to a sensor connector. In some examples, the plurality of connection wires are positioned within a wire protection housing. In some examples, the at least one ceramic insulator is positioned within the wire protection housing and defines a plurality of insulator openings. In some examples, each of the plurality of connection wires passes through one of the plurality of insulator openings.

Abstract: The disclosure provides rotary machines that include, in one embodiment, a shaft defining a central axis A, the shaft having a first end and a second end. The shaft can have a first gearbox disposed thereon defining one or more cavities therein. At least one contour is slidably received into an arcuate cavity in an exterior surface of the gearbox. The contour has a convex outer surface that cooperates with an inwardly facing curved surface of a housing to form a working volume. A gearbox mechanism consisting of gears, crankshafts, bearings and connecting rod creates an oscillatory motion 2 times per revolution such that the contour can navigate about the arcuate cavity without contacting the cavity at a high rate of rotating speed. Thus, said working volume can expand and compresses twice per rotatable shaft revolution.

Abstract: A turbine (10) for a charging device (1) with a turbine housing (100) with a feed duct assembly (200), a turbine outlet duct (110) and a receptacle space (120). The feed duct assembly (200) includes a first feed duct (210) having a first fluid inlet portion (211) and a first fluid outlet portion (212), and a second feed duct (220) having a second fluid inlet portion (221) and a second fluid outlet portion (222). The first fluid outlet portion (212) extends across a first angular range (?1) about the guide installation (400). The second fluid outlet portion (222) extends across a second angular range (?2) about the guide installation (400). The first angular range (?1) is larger than the second angular range (?2). The first fluid inlet portion (211) and the second fluid inlet portion (221) are mutually spaced apart in the circumferential direction (26).

Abstract: Fuel injectors for gas turbine engines include an inner housing having a center body installed within the inner housing, an intermediate housing arranged radially outward from the inner housing, and an outer housing arranged radially outward from the intermediate housing. The center body is a hollow body structure defining a center body airflow passage therethrough, a first fluid passage is partially defined between an outer surface of the inner housing and an inner surface of the intermediate housing, a second fluid passage is partially defined within the intermediate housing, and a third fluid passage comprises the center body airflow passage, an inner airflow passage defined between an exterior surface of the center body and an interior surface of the inner housing, and an outer airflow passage that is defined by the outer housing and radially outward from the intermediate housing.