11160results about "Propulsive elements" patented technology

A transmission for a marine propulsion system uses a cone clutch in such a way that, when in a forward gear position, torque is transmitted from an input shaft, or driving shaft, to an output shaft, or driven shaft, solely through the cone clutch. When in forward gear position, driving torque between the driving and driven shafts is not transmitted through any gear teeth. When in reverse gear position, torque is transmitted through an assembly of the bevel gears.

A modular apparatus for and method of alternating current photovoltaic power generation comprising via a photovoltaic module, generating power in the form of direct current; and converting direct current to alternating current and exporting power via one or more power conversion and transfer units attached to the module, each unit comprising a unitary housing extending a length or width of the module, which housing comprises: contact means for receiving direct current from the module; one or more direct current-to-alternating current inverters; an alternating current bus; and contact means for receiving alternating current from the one or more inverters.

A modular apparatus for and method of alternating current photovoltaic power generation comprising via a photovoltaic module, generating power in the form of direct current; and converting direct current to alternating current and exporting power via one or more power conversion and transfer units attached to the module, each unit comprising a unitary housing extending a length or width of the module, which housing comprises: contact means for receiving direct current from the module; one or more direct current-to-alternating current inverters; an alternating current bus; and contact means for receiving alternating current from the one or more inverters.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

A vertical axis tower fan apparatus having an adjustable support column. The tower fan apparatus is comprised of a support base, a telescopic support column adjustable between fixed, retracted and extended positions, a vertical axis propeller encased within a housing, and a motor. The vertical axis propeller is contained within the cylindrical housing, wherein the housing is rotatably coupled to one end of the support column. The fan is rotatably connected to the top of the support column and is adapted to rotate freely thereon, when activated. The opposing end of the column is insertable into the support base. The telescopic column is comprised of a hollow pillar and an extendable member removably inserted within the hollow pillar. The column is manually adjustable to a variety of heights to provide cooling air to different target heights via the use of an adjustable locking sleeve. The sleeve may be loosened, to allow the extendable member to be extracted from within the hollow pillar and raised until the fan reaches a desirable height. Conversely, the extendable member may be retracted until the fan reaches another target height. When the desired height is reached, the sleeve is tightened thereby preventing the member from moving within the pillar. A keypad located in the housing cover, or a remote control unit allows the user to program the fan, via the use of a microcontroller within the fan housing, to achieve a variety of speeds and wind patterns, as well as activating an oscillation mode and a timer.

The system is an integrated and self contained electric thruster system integral with a dynamic positioning control system for dynamic positioning of any waterborne vessel having a hull with at least two sides and a deck connecting the sides, at least two azimuthing thrusters, each removably mounted to the vessel, at least two self-contained electric power units removably secured to the deck, one for each thruster, at least one dynamic positioning computer connected to each of the self contained electric power units, at least one motion reference sensor connected to the dynamic positioning computer to correct reference position signals for motion of the vessel, at least one heading sensor, and at least one sensor that is either a position reference sensor connected to the dynamic positioning computer, environmental sensors connected to the dynamic positioning computer, or a combination thereof.

A stable portable air moving device capable of generating an air stream elevated above a support surface allowing the air stream to be directed as desired by the user is provided. The device includes an air blower assembly located within an elongate housing generating an exhaust air stream that exits the elongate housing at an elevation above the air blower assembly.

The disclosure relates to fluid working devices including reciprocating internal combustion engines, compressors and pumps. A number of arrangements for pistons and cylinders of unconventional configuration are described, mostly intended for use in reciprocating internal combustion IC engines operating without cooling. Included are toroidal combustion or working chambers, some with fluid flow through the core of the toroid, pistons reciprocating between pairs of working chambers, tensile valve actuation, tensile links between piston and crankshaft, energy absorbing piston-crank links, crankshafts supported on gas bearings, cylinders rotating in housings, injectors having components reciprocate or rotate during fuel delivery. In some embodiments pistons mare rotate while reciprocating. High temperature exhaust emissions systems are described, including those containing filamentary material, as are procedures for reducing emissions during cold start by means of valves at reaction volume exit. Compound engines having the new engines as a reciprocating stage are described. Improved vehicles, aircraft, marine craft and transmissions adapted to receive or be linked to the improved IV engines are also disclosed.

A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a first fan assembly disposed upstream from the core gas turbine engine, a first gearbox coupled to the first fan assembly, and a second gearbox coupled to a booster compressor such that the booster compressor rotates in a rotational direction that is opposite to the rotational direction of the first fan assembly. A method of assembling the above turbofan engine assembly is also described herein.

A turbine includes a turbine blade, a plurality of sensors, a wireless sensor module, a data aggregator, and a blade pitch control unit. The plurality of sensors are distributed in a plurality of locations on the turbine blade suitable for determining a moment of the turbine blade. The sensor module is configured to transmit data to the data aggregator to determine the moment. The data aggregator is configured to provide an output to the blade pitch control unit. The blade pitch control unit is configured to adjust pitch of the turbine blade based on the moment.

A gas turbine engine assembly includes a gas turbine engine mounted on a three-point mounting frame. The three-point mounting frame includes an engine support structure having first and second beams in a V-configuration, and a secondary support structure that is positioned about the engine support structure and has a rectangular footprint. The frame may include a Y-configuration that includes the V-configuration, and may be implemented in a machine mounting system, such as in a marine vessel.

A fan assembly includes a motor-driven impeller for creating an air flow, at least one heater for heating a first portion of the air flow, and a casing comprising at least one air outlet for emitting the first portion of the air flow, and first channel means for conveying the first portion of the air flow to said at least one air outlet. To cool part of the casing, the casing includes means for diverting a second portion of the air flow away from said at least one heater, and second channel means for conveying the second portion of the air flow along an internal surface of the casing. This second portion of the air flow may merge with the first portion within the casing, or it may be emitted through at least one second air outlet of the casing.

Machines useful for wind turbine and ship propulsion purposes include a wind turbine generator or a ship propulsion motor with two concentric air gaps. In one embodiment, the machine includes a rotor with an inner rotor core and an outer rotor core; and a double-sided stator with an inner stator side and an outer stator side. The double-sided stator is concentrically disposed between the inner rotor core and the outer rotor core.

Marine LNG carrier and method of operating the marine LNG carrier. The LNG carrier carries LNG in at least one tank. Gas composed of evaporated LNG within the at least one tank is removed. The gas is fed to at least one gas consuming prime mover of the LNG carrier. Power is provided with the at least one gas consuming prime mover. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

A marine vessel running controlling apparatus controls running of a marine vessel and includes a pair of propulsion systems which respectively generate propulsive forces on a rear port side and a rear starboard side of a hull, and a pair of steering mechanisms which respectively change steering angles defined by directions of the propulsive forces with respect to the hull. The apparatus includes a target combined propulsive force acquiring section, a target movement angle acquiring section, a steering controlling section which controls the steering angles of the respective steering mechanisms such that a turning angular speed of the hull is substantially equal to a predetermined target angular speed, a target propulsive force calculating section which calculates target propulsive forces to be generated from the respective propulsion systems based on the target combined propulsive force, the target movement angle and the steering angles of the respective steering mechanisms, and a propulsive force controlling section which controls the respective propulsion systems so as to attain the target propulsive forces.

A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a first fan assembly disposed upstream from the core gas turbine engine, a first gearbox coupled to the first fan assembly, and a second gearbox coupled to a booster compressor such that the booster compressor rotates in a rotational direction that is opposite to the rotational direction of the first fan assembly. A method of assembling the above turbofan engine assembly is also described herein.

This invention relates to a method and apparatus for controlling power distribution in an electrical aircraft propulsive system having at least one electrical propulsion unit which includes a plurality of rotatable blades, each blade having an adjustable pitch; a pitch adjusting mechanism for adjusting the pitch of the blades; at least one electrical machine electrically connected to the electrical propulsion unit so as to provide electrical power when in use; and, a control system, the method comprising the steps of: determining the required propulsion; determining whether the propulsive units are delivering the required propulsion; and, adjusting the pitch angle of the blades of at least one propulsive unit so as to increase or decrease the propulsion provided by that propulsive unit.

A wind turbine is presented where the operation lifetime of the main bearing is extended by relieving the main bearing by reducing the mean bending moment on the bearing by means of individual pitch control of the blades of the rotor so as to create an aerodynamic mean tilt moment on the rotor by means of aerodynamic forces on the blades, the tilt moment at least partly counteracting the bending moment caused by the overhang load forces on the main bearing from the gravitational pull on the rotor mass.

The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle crate a plasma the discharges through the hollow electrode nozzle.

A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.

An exhaust mixer assembly having a twisted mixer and an open centerbody is provided. The open centerbody is centrally disposed within the twisted mixer and helps to provide efficient cooling of exhaust air from gas turbine engines. A method for cooling exhaust air from a gas turbine engine using the exhaust mixer assembly of the invention is also provided.

The invention relates to a water surface garbage cleaning ship. In the invention, a ship body is of an dual-body design, and the water surface garbage cleaning ship is composed of a detection and navigation system, a collection system, a garbage treatment system, a garbage unloading system and a propulsion system; and the water surface garbage cleaning ship can have three working modes, namely a free navigation mode, a landing operation mode and a non-landing operation mode. The water surface garbage cleaning ship can realize autonomous navigation and work, unmanned operation, full automation, good cleaning effect, strong flexibility, smoothness in working, safety and reliability by using the detection and navigation system to detect a region with garbage on the water surface. A scraper bucket chain network type collection and transmission device designed in the water surface garbage cleaning ship can realize the combination of continuous and intermittent work of recovery, thereby being energy-saving and high-efficient. Simultaneously, the device can change the amplitude up and down by hydraulic drive and fish floating objects in different water depths faster and more effectively.A satellite ship is designed for collaborative collection, thereby having better flexibility and high efficiency. The shoreside water surface floating objects and semi-floating objects are recovered and taken onto the ship by using a hydraulic rotary water spray gun to spray water.

A bladeless fan assembly for creating an air current includes a nozzle mounted on a base housing a device for creating an air flow through the nozzle. The nozzle includes an interior passage for receiving the air flow from the base and a mouth through which the air flow is emitted. The nozzle extends about an axis to define an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle includes a surface over which the mouth is arranged to direct the air flow. The surface has a diffuser portion tapering away from the axis, and a guide portion downstream from the diffuser portion and angled thereto.

A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.

A fan assembly includes a device for creating an air flow and an air outlet for emitting the air flow, the air outlet being mounted on a pedestal including a base and a height adjustable stand. The base includes an oscillating mechanism for oscillating the stand and the air outlet.

A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid capture duct 62. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes 36 defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction 18 that would otherwise impede thorough mixing of two fluid streams.

A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area through a cam drive ring. The flap assembly generally includes a multiple of flaps, flap linkages and an actuator system. The actuator system rotationally translates the cam drive ring relative an engine centerline axis which results in a follower of the flap linkage following a cam surface to pivot each flap such that the flap assembly dilates about the circumferential hinge line. Rotation of the cam drive ring adjusts dilation of the entire fan nozzle exit area in a symmetrical manner. Another cam drive ring includes a multiple of movable cams which engages the follower of the flap linkage of each flap such that pivotable movement of a particular number of the multiple of movable cams about a respective cam pivot results in vectoring of the FVAN.

A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas turbine engine core. A nozzle (40) associated with the fan bypass passage includes a first nozzle section (54a) that is operative to move in a generally axial direction to influence the bypass airflow, and a second nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction. An actuator (42) selectively moves the first nozzle section and the second nozzle section to influence the bypass airflow and provide thrust reversal.

A wind turbine with a sensor that measures the out-of-plane deflection of the blades and a controller that uses the signal from the sensor to determine the risk of a tower strike. The controller takes any necessary action to prevent a tower strike when it determines that the risk of a strike is high. The sensor can include strain gages or accelerometers mounted on the blades or it can include a fixed sensor mounted on the side of the tower to measure tower clearance as the blade passes by. The control action taken can include pitching blades, yawing the nacelle, or stopping the turbine. The controller is preferably a fuzzy logic controller.