Abstract: An energy conversion system for converting wind energy into electrical energy includes at least one rotor having a substantially horizontal rotational axis and a plurality of rotor blades extending radially with respect to the rotational axis; a rotor mantle which fully surrounds the rotor; a plurality of wind funnels, including a first wind funnel arranged upstream of the rotor mantle and tapering towards the rotor mantle, and a second wind funnel arranged downstream of the rotor mantle and widening in a direction leading away from the rotor mantle; and a fixed frame which supports the rotor mantle and/or the plurality of wind funnels, wherein at least one adjustment device is provided, which is arranged and configured to orient the energy conversion system in a position corresponding to a prevailing wind direction.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a carrier, a first gear system, a second gear system and an idler. The first gear system includes a first sun gear, a first ring gear and a plurality of first intermediate gears. Each of the first intermediate gears is between and is meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the carrier. The second gear system includes a second sun gear, a second ring gear and a plurality of second intermediate gears. Each of the second intermediate gears is between and is meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The idler gear couples the first ring gear to the second ring gear.

Abstract: A fan module for a vehicle engine cooling system includes a pair of co-axial, counter-rotating, axial flow fans. Each fan is supported on and driven by a dedicated downstream motor, and each motor is supported by a dedicated shroud. The shroud that supports the first motor includes a barrel, a motor carrier that is surrounded by the barrel, and vanes that extend between the barrel and the motor carrier. For each vane, a line that extends between the vane nose and the vane tail is angled relative to the fan rotational axis, and the angle is selected to minimize air flow losses through the shroud.

Abstract: A propulsion assembly includes a rotor assembly, a mast coupled to the rotor assembly and a bull gear coupled to the mast. The bull gear is subject to radial and axial loads. The propulsion assembly includes a flexured standpipe extending through the bull gear and a ball bearing including inner and outer races interposed between the bull gear and the flexured standpipe. The ball bearing is configured to absorb axial loads from the bull gear. The bull gear is rotatably coupled to the flexured standpipe via the ball bearing. The flexured standpipe flexes in response to radial loads from the bull gear.

Abstract: A thrust balancing gear assembly for a turbo machine is provided. The gear assembly includes an input gear connected to an input drive shaft, an output gear connected to an output drive shaft, and a compound planet gear including a first planet gear and a second planet gear each connected to one another and positioned in axially adjacent arrangement. The first planet gear is connected to the input gear at a first interface and the second planet gear is connected to the output gear at a second interface.

Abstract: A wind control blade (31) of a wind guide (30) of the present invention forms a 20° wind control blade lateral curved surface gradient angle (32), a 30° wind control blade longitudinal spiral twist angle (33), a 180° wing control blade alignment angle (34), and a 15° wind control blade rear gradient angle (35). In addition, a turbine blade (41) forms a 30° turbine blade lateral curved surface gradient angle (42), a 40° turbine blade longitudinal spiral twist angle (43), and a 120° turbine blade alignment angle (44). The 20° wind control blade lateral curved surface gradient angle (32) and the 30° wind control blade longitudinal spiral twist angle (33) of the wind control blade (31) have more gradual and wider incidence angles than the 30° turbine blade lateral curved surface gradient angle (42) and the 40° turbine blade longitudinal spiral twist angle (43) of the turbine blade (41).

Abstract: A fairing system, includes a hub fairing and a fixed fairing, such as a shaft fairing or a pylon fairing, both arranged about a rotation axis. A gap is defined between the hub fairing and the fixed fairing, and a seal assembly is axially interposed between the hub fairing and the fixed fairing. The fixed fairing and the hub fairing are both removably mounted to the seal assembly such that either or both of the fairings can be dismounted from the seal assembly without disturbing the seal assembly to provide access to components disposed within the fairing.

Abstract: A wind turbine rotor shaft arrangement, e.g. of horizontal type, comprising a rotor shaft for supporting wind turbine blades, a non-rotating first housing structure for supporting the rotor shaft, and a first rolling bearing arranged to support, in a first axial direction, the rotor shaft in relation to the first housing structure at a first support point. The first rolling bearing is a single row self-aligning bearing comprising an inner ring, an outer ring, and a set of rolling elements formed of rollers arranged in an intermediate configuration between the inner and outer rings. Each roller is a symmetrical bearing roller having a curved raceway-contacting surface arranged contacting a curved inner raceway of the inner ring and a curved outer raceway of the outer ring. A contact angle between each roller and the inner and/or outer raceway is inclined in relation to the radial direction of the rotor shaft.

Abstract: A variable-pitch vane including a plurality of propeller blades (2). Each blade has a variable pitch according to a blade rotational axis (A1) and a root (201). A plurality of rotor connecting shafts (6), each shaft having a foot (602) and a head (601). The root (201) of each blade is mounted on the head (601) of a rotor connecting shaft via a pivot (8) in such a way as to allow each blade (2) to rotate according to the blade rotational axis (A1), in which each blade (2) has a blade pitch, such that the blade rotational axis (A1) is inclined relative to a radial axis (A2) passing through the foot (602) of the corresponding shaft.

Abstract: A rotor hub assembly for a rotary-winged aircraft includes a spool portion and a plurality of hub arms extending radially outwardly from the spool portion. A rotor blade is connectable to each hub arm. Each hub arm includes a spine portion and at least two leg portions extending from the spine portion. The spine portion and the at least two leg portions defining an I-shaped cross-section of each hub arm. A rotor assembly includes a rotor hub assembly including a spool portion and a plurality of hub arms extending radially outwardly from the spool portion. Each hub arm includes a spine portion and at least two leg portions extending from the spine portion. The spine portion and the at least two leg portions define an I-shaped cross-section of each hub arm. A rotor blade is secured to each hub arm.

Abstract: A propulsion system for an aircraft may include two coaxial propellers to operate in two different flight conditions. Each propeller may be attached to a driveshaft via corresponding one-way devices that allow each propeller to be driven in one direction but spin freely in the other direction. A reversible motor may selectively rotate the driveshaft in one direction to cause one propeller to operate while the other spins freely. For example, one propeller may be operated for one flight condition (such as vertical lift) and the other propeller may be operated for another flight condition (such as horizontal flight). Another propulsion system may include a propeller, a one-way bearing, a motor, and a generator. The one-way bearing may allow the motor to drive the propeller in one direction and to spin freely in the other direction to drive the generator with incoming airflow during a gliding phase of flight.

Abstract: A wind turbine comprises a hub, a blade rotatably mounted to the hub, and a pitch system. The pitch system includes a support, a first drive configured to rotate the blade relative to the support, a second drive configured to rotate the support relative to the hub. The support is configured to be selectively fixed relative to the blade and the hub such that the first or second drive may be used to pitch the blade. A method of pitch corresponding to this operation is provided.

Abstract: This disclosure provides an apparatus, system and method for an energy capturing pod (ECP). The ECP includes a specialized funnel shell, a first turbine, and a second turbine. The specialized funnel shell is designed to accelerate in coming wind speed and is structured with a first choke point and a second choke point for wind. The first turbine is located at the first choke point. The second turbine is located at the second choke point.

Abstract: According to at least one exemplary embodiment, an oil-free contra-rotating transmission is disclosed. The contra-rotating transmission may comprise a lower drive unit; and an upper drive unit, wherein the lower drive unit receives power from a motor and is configured to (i) transfer power from the motor to the upper drive unit, and (ii) rotate a first axial fan in a first direction. The upper drive unit may be configured to rotate the second axial fan in a second direction opposite to the direction of rotation of the first direction.

Abstract: Provided here is a counter-rotating axial flow fan with improved air flow-static pressure characteristics and reduced power consumption and noise compared to the related art. A plurality of struts are disposed to be stationary between a front impeller and a rear impeller in an air channel. A plurality of front blades are each formed of a swept-back blade, and a plurality of rear blades are each formed of a forward-swept blade.

Abstract: The invention relates to rotary units and rotary mechanisms that are suitable for use in numerous applications. Rotary units typically include rotational components that are configured to rotate. In some embodiments, for example, multiple rotary units are assembled in rotary mechanisms such that neighboring pairs of rotational components counter-rotate or contra-rotate relative to one another during operation of the rotary mechanisms. Rotational components generally include one or more implements that are structured to perform or effect one or more types of work as the rotational components rotate relative to one another in a given rotary mechanism. In certain embodiments, implements are configured to rotate and/or to effect the movement of other components as rotational components rotate. In some embodiments, engines include rotary mechanisms and are used in, for example, ground vehicles, marine vehicles, aircraft, or devices.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

Abstract: A rotor system includes a first rotor located at a rotor axis that imparts a first axial load and a first moment, and a first shaft connected to the first rotor at the axis. A first bearing connects a gearbox to the first shaft, transferring the first axial load from the first shaft to the gearbox. A second rotor located at the axis imparts a second axial load and a second moment. A second shaft is connected to the second rotor at the axis, the second shaft coaxial with the first rotor. A second bearing connects the gearbox to the second shaft, transferring the second axial load from the second shaft to the gearbox. A nonrotating standpipe is located at the axis radially between the first shaft and the second shaft. An intershaft bearing located at the standpipe reacts the first and second moments using the first and second bearings.

Abstract: A turbine engine including two contrarotating unducted propellers of an upstream propeller and a downstream propeller, with a power turbine mounted axially between the two propellers, the turbine including an outer rotor constrained to rotate with the upstream propeller and an inner rotor driving rotation of an inlet shaft of a step-down gearbox, the gearbox includes an outlet shaft driving rotation of the rotor of the upstream propeller and an outlet shaft driving rotation of the downstream propeller.

Abstract: An aircraft control system includes a co-axial, counter-rotating propeller shaft assembly. Also included is a first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, wherein the first plurality of blades are disposed at a substantially identical nominal pitch during rotation of the first rotor. Further included is a second rotor operatively coupled to the propeller shaft assembly, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second plurality of blades is configured to cyclically change during rotation of the second rotor.

Abstract: The invention relates to a fixed turbine engine receiver part comprising a fixed hollow shaft for carrying ancillary systems of a turbine engine, centered on the turbine engine axis, turbine engine ancillary systems, an assembly for holding ancillary systems in position situated inside the fixed hollow shaft. The assembly for holding ancillary systems in position comprises at least one first ancillary system support ring, having an axis substantially parallel with the turbine engine axis, a first distance sleeve for holding the first ancillary system support ring in position, having an axis substantially parallel with the turbine engine axis, the first distance sleeve bearing against the first support ring, such that the first support ring comprises a plurality of mutually separated through holes, each through hole defining a passage for at least one ancillary system, each through hole being traversed by at least one of the ancillary systems of the turbine engine.

Abstract: According to at least one exemplary embodiment, an oil-free contra-rotating transmission is disclosed. The contra-rotating transmission may comprise a lower drive unit; and an upper drive unit, wherein the lower drive unit receives power from a motor and is configured to (i) transfer power from the motor to the upper drive unit, and (ii) rotate a first axial fan in a first direction. The upper drive unit may be configured to rotate the second axial fan in a second direction opposite to the direction of rotation of the first direction.

Abstract: Disclosed are a propulsion device for a ship and a ship having same. The propulsion device, according to an embodiment of the present invention, comprises: a rear propeller fixed to a driveshaft; a front propeller positioned in front of the rear propeller, and supported rotably on the driveshaft; and a counter rotation device for reversing and transmitting the rotation of the driveshaft to the front propeller; a motor for rotating the driveshaft; and an housing, which extends from to the lower part of the hull, and which is installed so as to envelope the counter rotation device and the motor.

Abstract: A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blade of the first rotor independently. At least one slip ring is configured to transmit electrical power and/or a control signal to the at least one IBCS.

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract: Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power.

Abstract: A blower having counter rotating fan blades for generating uniform air flow across a heat sink, which maximizes the cooling efficiency of the heat sink. The counter rotating fan blades may individually controlled to optimize performance of the blower. Only one set of fan blades may be used for low temperature conditions, thereby consuming less power and reducing acoustic noise, while both sets of fan blades may be used for high temperature conditions, thereby maximizing heat transfer. The blower may be configured to operate one or both sets of fan blades at a desired operating fan speed based on one or more pre-determined conditions. The pre-determined conditions include at least one of temperature, acoustic, and power levels and or measurements of one or more components of the computer system.

Abstract: A turbo-machine with blade wheels, comprises a body, a rotor which is held in a rotatable manner by the body, at least two rotatably arranged blades which are distributed uniformly along a circular line of the rotor and which are mounted with their axis parallel to the axis of the rotor, transmission members between each axis of the blade and a sleeve which is rotatable on the shaft of the blade wheel. The first rotor is assigned a second rotor which is held in a rotatable manner by the first rotor, wherein the second rotor comprises at least two rotatably arranged blades which are distributed uniformly along a circular line of the rotor and which are mounted with their axis parallel to the rotor, transmission members between each axis of the blade and the sleeve which is rotatable on the shaft of the rotor.

Abstract: A system of contra-rotating propellers for an aircraft turbomachine, including: a free power turbine including a first rotor; first and second propellers; and a mechanical transmission system including a planetary gear train fitted with a sun gear driven by the rotor, at least one planet gear driving the first propeller, and a ring driving the second propeller. The free power turbine also includes a second rotor that is contra-rotating relative to the first rotor, and rotating the ring.

Abstract: A counter-rotating axial flow fan with reduced noise at the target operating point achieved without modifying a front impeller, a rear impeller, or a middle stationary portion is provided. An annular rib including a projecting surface for generating turbulent flow is formed on an inner wall portion of a casing at a position off from the middle stationary portion to a side of the rear impeller, the projecting surface extending radially inwardly of the inner wall portion and extending continuously in the circumferential direction of the inner wall portion. A fluid striking the projecting surface for generating turbulent flow is partially disturbed to form a turbulent flow before entering an area in which the rear impeller is provided. The turbulent flow suppresses flow separation of a fluid flowing along the surfaces of rear blades of the rear impeller from the surfaces of the rear blades.

Abstract: This invention describes a device effective in maximizing the power output of a rotor in a fluid. This turbine uses a rotor (2) similar to HAWT but placed in a vertical position enclosed in a static diffuser with the shape of an inverted wing. The motionless structure (1) is influenced by two combined flows, enhancing the energy produced by the rotor (2). The rotor (2) is connected to an element of transformation of mechanical energy integrated in the structure (1) with an aerodynamic shape of an inverted wing. The system does not have an orientation mechanism with the direction of the wind since it is completely omnidirectional and presents only one movable component, the rotor (2) with blades (3). The turbine may still comprise an aerodynamic deflector in a brim (6) in the upper part of the structure (1) and is divided in multi-elements (9) with at least two aerodynamic elements. This invention is applicable in the energy producing energy with the micro-generation, as well as large power systems.

Abstract: A fluidfoil is disclosed including a leading edge and a leading edge zone behind the leading edge. The leading edge zone extends spanwise for the full length of the fluidfoil. The leading edge zone includes one or more deflected regions which locally reduce the angle of attack of the fluidfoil.

Abstract: A fan assembly includes two fans, and a number of rigid bars. The fans are connected in series. Each of the fans includes an impeller. The impellers of the fans rotate in opposite directions. The rigid bars extend through the fans and are fixed to the fans, to counteract opposing torque forces produced by the fans.

Abstract: Disclosed are a ship propulsion device and a ship having the same. According to one embodiment of the present invention, the ship propulsion device includes a rear propeller fixed on a drive shaft; a front propeller supported on a drive shaft of the front of the rear propeller to be rotated; and a reverse rotary device having a plurality of gears which are provided on a rear side of the ship, and transmits rotation of the drive shaft after reversing the rotation to the front propeller.

Abstract: A rotor system is provided wherein coaxial, closely spaced multi-bladed rotors counter-rotate at extremely low RPMs while their pitches are controlled to account for wind gusts and velocity conditions, thereby eliminating many of the deficiencies of conventional helicopters. The embodiments can dramatically decrease the power required to lift a given quantity of weight, even beyond the level required by a typical airplane.

Abstract: A counter-rotating axial flow fan with improved characteristics and reduced noise compared to the related art can be provided. Defining the number of front blades as N, the number of stationary blades as M, and the number of rear blades as P, and defining the maximum axial chord length of the front blades as Lf, the maximum axial chord length of the rear blades as Lr, the outside diameter of the front blades as Rf, and the outside diameter of the rear blades as Rr, the counter-rotating axial flow fan satisfies the following two relationships: N?P>M; and Lf/(Rf×?/N)?1.25 and/or Lr/(Rr×?/P)?0.83.

Abstract: A blade, configured to be mounted on a hub of a turbomachine propeller so that an empty space is defined between a base of the blade and a face of the hub facing the base. The blade includes a retractable blanking mechanism configured to reversibly occupy at least one of following two positions: a deployed position in which the retractable blanking mechanism at least partially closes off the empty space; and an extreme retracted position in which the retractable mechanism is kept out of the empty space.

Abstract: A counter-rotating axial flow fan in which the shape of stationary blades of a middle stationary portion is optimized to reduce noise is provided. Defining the maximum axial chord length of front blades as Lf, the maximum axial chord length of rear blades as Lr, and the maximum axial chord length of stationary blades as Lm, a relationship of Lm/(Lf+Lr)<0.14 is satisfied. Defining the maximum dimension between the blade chord for lower surfaces of the stationary blades and the lower surfaces as K1, the maximum axial chord length Lm of the stationary blades satisfies a relationship of Lm/K1>5.8.

Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.

Abstract: Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear.

Abstract: An air vehicle propulsion system incorporates an engine core with a power shaft to drive an outer blade row. The power shaft extends through and is supported by a counter rotation transmission unit which drives an inner blade row in counter rotational motion to the outer blade row. The counter rotation transmission unit exchanges power from the engine core with the shaft. An actuator engages the shaft for translation from a first retracted position to a second extended position.

Abstract: The present disclosure relates to a turbine for hydraulic power generation comprising two bladed wheels (11, 12, 31, 32) successively arranged in a turbine tube section (10, 21) as a fore wheel (11, 31) and an after wheel (12, 32) with respect to the water flow direction (23) along a common rotation axis (30) extending in the water flow direction (23), the wheels (11, 12, 31, 32) being configured to rotate in opposite directions driven by the water flow, and to a corresponding hydroelectric power plant.

Abstract: A gas turbine engine comprises a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case, a shaft rotatable relative to the fan case about an engine center axis, and a geared architecture driven by the shaft to provide driving output to rotate the fan hub. A compressor is positioned forward of the geared architecture and radially inward of the fan blades, with the compressor being driven by the shaft.

Abstract: A rotor apparatus for extracting energy from bidirectional fluid flows comprises a first rotor (7) mounted for rotation about an axis of rotation (4) in a first direction of rotation, the first rotor (7) having at least one helical blade (2) with a pitch that decreases in a direction along the axis of rotation (4); and a second rotor (8) mounted for rotation about the same axis of rotation (4) in an opposite direction of rotation and having at least one helical blade (2) with a pitch that increases in the same direction along the axis of rotation (4), wherein fluid exiting the first rotor (7) is passed to the second rotor (8).

Abstract: A system, including: a linear actuator axially arranged in a first propeller and rotatably secured thereto, a first linking mechanism connecting a rod of the linear actuator to a second propeller to change a setting of blades thereof, and including an intermediate bearing between the propellers, which is capable of transmitting translation of the rod of the linear actuator and disconnecting a rotatable link to the first propeller to make it possible to change the setting of the blades of the second propeller rotated in an opposite direction to the first propeller, and a second linking mechanism combined with blades of the first propeller to change a setting thereof.

Abstract: A fairing system according to an exemplary aspect of the present disclosure includes, among other things, a shaft fairing mounted for rotation about an axis of rotation and a planetary gear set configured to control a position of the shaft fairing about the axis of rotation.

Abstract: A bidirectional water turbine including: an upstream rotor and a downstream rotor, wherein the upstream rotor and downstream rotor are contra-rotating and each rotor includes a plurality of blade, the blades of the upstream and downstream rotors having substantially the same profile.

Abstract: A propulsive fan system comprises a fan unit comprising a first stage array of rotatable blades upstream of a second stage array of rotatable blades. The first stage is coupled to a first drive means. The second stage is coupled to a second drive means. The first drive means is independently operable of the second drive means during operation of the fan system.

Abstract: A gas turbine engine includes in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a combustion chamber; and a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft. The first turbine is adapted to influence a gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, wherein the gas turbine engine further includes an arrangement for controlling the rotational speed of the first turbine. A method for controlling a gas flow rate in an axial flow gas turbine engine is also provided.

Abstract: An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.