Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. The evaporator module is within the cavity. The condenser module is within the cavity. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

Abstract: A valve train for an internal combustion engine includes an outlet valve, an engine brake rocker shaft that is pivotable around a pivot axis, where the outlet valve is operable by pivoting the engine brake rocker shaft during an engine braking operation of the internal combustion engine, a camshaft which has a cam via which the engine brake rocker shaft is pivotable around the pivot axis, and a spring element via which the engine brake rocker shaft is tensioned against the camshaft. The spring element is a leaf spring.

Abstract: A compressor assembly includes a compressor housing having an inlet port configured to receive intake air and an outlet port configured to discharge pressurized air. A hollow section having an inner radial surface defines the inlet port of the compressor housing. A compressor wheel is disposed in the hollow section. A positive crankcase ventilation (PCV) passage is configured to allow airflow between a crankcase of an engine and the hollow section of the compressor housing. The PCV passage has an outlet opening that opens into the hollow section of the compressor housing and the inner radial surface includes an integrally formed raised boss surrounding the outlet opening and protruding into the hollow section.

Abstract: Scalable greenhouse gas capture systems and methods to allow a user to off-load exhaust captured in an on-board vehicle exhaust capture device and to allow for a delivery vehicle or other transportation mechanism to obtain and transport the exhaust. The systems and methods may involve one or more exhaust pumps, each with an exhaust nozzle corresponding to a vehicle exhaust port. Upon engagement with the vehicle exhaust port, the exhaust nozzle may create an air-tight seal between the exhaust nozzle and the vehicle exhaust port. A first pipe may be configured to transport captured exhaust therethrough from the exhaust nozzle to. The captured exhaust may be at least temporarily stored in an exhaust holding tank connected to and in fluid communication with the first pipe.

Abstract: A diesel engine is provided with an exhaust after-treatment device for purifying exhaust gas. The exhaust after-treatment device includes a DPF that collects a particulate matter included in the exhaust gas, and an SCR that reduces nitrogen oxides included in the exhaust gas through addition of urea. The DPF is arranged to extend in an engine width direction orthogonal to both the engine front-rear direction and an up-down direction, on one side of the engine front-rear direction with respect to the DPF. The DPF and the SCR are attached to the diesel engine.

Abstract: A coolant heating system includes: a coolant heater including: a housing including: an inlet configured to receive coolant; and an outlet configured to output coolant; an electrically resistive heating element that is disposed within the housing and that is configured to generate heat when power is applied to the heating element; and a temperature sensor configured to measure a temperature of coolant within the housing; and a heater control module configured to: receive the temperature from the temperature sensor; selectively control application of power to the heating element based on maintaining the temperature at or above a predetermined temperature; selectively detect the presence of a condition based on the temperature; and when the presence of the condition is detected, disconnect the heating element from power.

Abstract: A fan shroud for a radiator fan contains a central impeller receptacle for receiving a radiator impeller, which receptacle defines a rotational axis for the radiator impeller which axis is oriented in an axial direction. The axial direction extends from an inflow side to a pressure side of the fan shroud. A shroud ring is provided, wherein a fan plane perpendicular to the axial direction is defined by the impeller receptacle and the shroud ring. A plurality of struts extend from the impeller receptacle to the shroud ring and extend from the inflow side to the pressure side. With a strut base, the struts are fastened to the impeller receptacle, and, with a strut tip, are fastened to the shroud ring. The struts are oriented at a strut angle in relation to the fan plane which angle varies from the strut base to the strut tip.

Abstract: A system for efficient combustion of a carbonaceous fuel is presented. An ultra low quantity of enhancement gas may be introduced to an internal combustion engine to improve at least one operating metric of the internal combustion engine such as fuel economy and/or reduce engine-out emissions, for example in a vehicle or generator.

Abstract: An electrolysis system may include a pressure-resistant assembly. The pressure-resistant assembly may include a first defined space configured to at least partially immerse a plurality of electrolysis plates in an aqueous solution. The pressure-resistant assembly may further include a second defined space configured to contain an enhancement gas or a component of the enhancement gas. The enhancement gas or the component of the enhancement gas may be generated in the first defined space. A volume of the second defined space may be in the range of 80-120% of a volume of the first defined space.

Abstract: A method for a combustion engine has a working cycle of three revolutions of the crankshaft. The method includes: feeding a fuel mixture into a combustion chamber of a cylinder while moving a piston from a second top dead-center to a first bottom dead-center; compressing an air-fuel mixture in the combustion chamber while moving the piston from the first bottom dead-center to a first top dead-center; burning the air-fuel mixture while moving the piston from the first top dead-center to a second bottom dead-center; compressing a gas mixture in the combustion chamber while moving the piston from the second bottom dead-center to the first top dead-center; burning the gas mixture while moving the piston from the first top dead-center to the first bottom dead-center; and expelling the gas mixture from the combustion chamber while moving the piston from the first bottom dead-center to the second top dead-center.

Abstract: A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.

Abstract: A powerplant includes a turbine engine core configured to power a mechanical load. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A recovery system includes a condenser and an evaporator. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser from an inlet into the core flowpath to an exhaust from the core flowpath. The recovery system is configured to condense water vapor flowing through the core flowpath into water using the condenser. The recovery system is configured to evaporate the water into steam using the evaporator and to provide the steam to the turbine engine core during a first mode of operation. The recovery system is configured to flow the water through the evaporator during a second mode of operation.

Abstract: A micro gas turbine equipped with a valve mechanism by means of which the operation of the micro gas turbine can be influenced and optimized, particularly by regulating a supply of hot gas from the cabinet and/or the exhaust of the micro gas turbine to an inlet side of the compressor. When the temperature of ambient air is relatively low, thermal output and thermal efficiency of a micro gas turbine decrease. The present micro gas turbine compensates for the loss of thermal efficiency.

Abstract: The present disclosure provides pumped heat energy storage systems that can be used to store and/or extract electrical energy. A pumped heat energy storage system of the present disclosure can store energy by operating as a heat pump, whereby net work input can be used to transfer heat from the cold side to the hot side. A working fluid of the system is capable of efficient heat exchange with heat storage fluids on a hot side of the system and on a cold side of the system. Such pumped energy storage systems can be beneficially integrated with steam plants to provided heating to the steam cycle.

Abstract: An air compressor system includes: two or more compressed air tanks previously filled with compressed air; several compression chambers also filled with compressed air, each containing a small internal expandable tube; located inside a larger external heavy-walled tube bonded to endcaps containing one-way and two-way valves, rigidly attached to top and bottom outside tanks; a timed valve inside expandable tube allowing compressed air from top tank to expand that tube to inside of heavy-walled tube, compressing ambient air outside expandable tube that entered through one-way valves. A second timed valve opens, forcing the original air back into the tank bottom or for immediate use or storage. Several other compression chambers follow the same procedure nonstop, increasing the psi in tank for immediate use or storage. All FIG. 1A compression chambers share two common tanks, which fill from top tank 600 and empty in bottom tank 602 in sequence.

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

Abstract: The invention relates generally to waste exhaust energy recovery and, in particular, a system or a retrofit kit for generating cavitation including a cantilevered bearing arrangement. The system may include a turbine wheel configured to drive an input shaft in response to exhaust energy. The input shaft may further support a cavitation impeller for generating pressure, fluid flow, and cavitation within a fluid. Upon collapsing, the cavitation bubbles may release energy that is captured by an output turbine mounted on an output shaft. Output shaft may harness the captured energy, which may be transmitted to an output device to, for example, turn a crankshaft to add torque or operate a generator to charge an external power source, such as a battery. Additionally, the system facilitates reducing emissions and fuel consumption while also supporting enhanced performance.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: A turboprop powered aircraft having a cowling or nacelle surrounding the engine, said cowling incorporates an air inlet and internal ducting to the engine wherein the inlet incorporated anti-icing ducts, said inlet shape has a closed oval or other non-circular shape that is not coaxial to the engine propeller drive shaft. Inlet anti-icing heating duct means are provided for channeling a portion of the engine's exhaust to the interior of the inlet rim. A further improvement in inlet efficiency can be achieved by reducing the thickness of the inlet cross-section, but this results in less space available for the hot exhaust connections.

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

Abstract: A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

Abstract: A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

Abstract: A turbine engine is provided that includes a fan section, a turbine engine core, an evaporator, a condenser, a core flowpath and a bypass flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The evaporator is arranged axially along an axis between the fan section and the turbine engine core. The condenser is arranged axially along the axis between the fan section and the turbine engine core. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser. The bypass flowpath is fluidly coupled with and downstream of the fan section. The bypass flowpath is radially outboard of and extends axially along the evaporator and the condenser.

Abstract: A method of operating a combined cycle power plant to facilitate increasing an output of the power plant. The method includes discharging a first exhaust gas stream from a gas turbine engine and extracting heat from the first exhaust gas stream via a heat recovery steam generator. The method also includes discharging a second exhaust gas stream from the heat recovery steam generator, pressurizing a first portion of the second exhaust gas stream using a recirculation compressor, and cooling the first portion of the second exhaust gas stream using a first cooler. The method further includes discharging a cooled exhaust gas stream from the first cooler to the gas turbine engine and modulating, via a controller, a flow and a temperature of the first portion of the second exhaust gas stream recirculated towards the gas turbine engine.

Abstract: Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.

Abstract: An example aircraft engine includes a fan and a gas turbine engine to drive the fan. The gas turbine engine has a low-pressure drive shaft operatively coupling a low-pressure turbine and a low-pressure compressor and a high-pressure drive shaft operatively coupling a high-pressure turbine and a high-pressure compressor. The aircraft engine includes a power transfer system including a differential having an input shaft, a first output shaft in gear with the low-pressure drive shaft, and a second output shaft in gear with the high-pressure drive shaft, and a gearbox between the low-pressure drive shaft of the gas turbine engine and the first output shaft of the differential. The gearbox is configured to provide power transfer through the differential from the low-pressure drive shaft to the high-pressure drive shaft.

Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.

Abstract: A method of controlling a combustor of a gas turbine engine, the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a scheduled pilot fuel split, the pilot fuel split is the percentage of the pilot fuel quantity of the total fuel quantity, monitoring combustion instability, applying a steady state active pilot split offset to the scheduled pilot fuel split when a predetermined temperature of the combustor is exceeded and/or a predetermined value of combustion instability is exceeded to create a steady state pilot fuel split, monitoring a condition of the gas turbine engine that influences an air/fuel ratio in the combustor, disabling the steady state active pilot split offset when the condition of the gas turbine engine is indicative of a transient condition and when a threshold value of combustion instability is exceeded, and applying a transient

Abstract: An engine control apparatus has: a first acquiring section that acquires an estimated torque of an engine according to a current rotation speed of the engine, and an instruction value representing an injection amount of a fuel injected to a cylinder of the engine; a second acquiring section that acquires an actual torque according to an amount of generated power generated by an electric power generator coupled to an output shaft of the engine when the amount of the fuel according to the instruction value is injected to the cylinder of the engine; and a correcting section that corrects at least any one of combustion timing at which the fuel is combusted in the cylinder and the instruction value on a basis of a first torque difference between the estimated torque acquired by the first acquiring section and the actual torque acquired by the second acquiring section.

Abstract: A system for controlling an electronic throttle body includes an engine speed setting device having a first terminal coupled to a source for a reference voltage, a second terminal coupled to a first end of a conductor and means for varying a level of resistance between the first and second terminals. The level of resistance is indicative of a desired engine speed. The second terminal outputs an analog engine speed signal indicative of the desired engine speed on the conductor. An electronic control module includes an engine speed signal processing circuit including a resistor coupled between a node located between the first and second ends of the conductor and one of a voltage supply and a voltage return. A controller coupled to the second end of the conductor is configured to generate a control signal for the electronic throttle body responsive to the engine speed signal.

Abstract: This engine structure includes: a cylinder block in which a cylinder bore is formed; a piston provided in the cylinder bore; a cylinder head provided to an upper portion of the cylinder block in a manner to seal the cylinder bore; and a ring that is inserted in the upper end portion of the cylinder bore and has an inner diameter that is smaller than the diameter of the cylinder. A first abradable layer that is worn down by contact with an outer peripheral surface of the piston is formed on an inner peripheral surface of the ring.

Abstract: A rotary internal combustion engine includes a rotor housing having a peripheral wall circumscribing a rotor cavity and a rotor disposed within the rotor cavity. A side housing is secured to the rotor housing and a plate defines a seal running surface for the rotor. The plate is disposed between a portion of the side housing and the rotor housing and at least one shim is disposed between the plate and the side housing for spacing the plate apart from contact with the side housing.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, an actuation linkage and a door lock. The blocker door is pivotally coupled to the translating structure. The actuation linkage operatively couples the blocker door to the fixed structure such that translation of the translating structure to the deployed position actuates pivoting of the blocker door into a flowpath. The door lock is configured to lock the actuation linkage to the translating structure such that the pivoting of the blocker door into the flowpath is delayed as the translating structure translates from the stowed position towards the deployed position.

Abstract: An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a door link and a structure link. The blocker door is pivotally coupled to the translating structure. The door link includes a first door link arm, a second door link arm and a door link mount connected to the first door link arm and the second door link arm. The first door link arm and the second door link arm are each pivotally coupled to the blocker door. The first door link arm and the second door link arm laterally converge towards one another as the first door link arm and the second door link arm extend longitudinally towards the door link mount. The structure link extends longitudinally between and is pivotally coupled to the door link mount and the fixed structure.

Abstract: The subject matter of this specification can be embodied in, among other things, an engine assembly includes a nacelle configured to at least partially surround an engine, and a thrust reverser coupled to the nacelle, the thrust reverser having a thrust-reversing element movable relative to the nacelle between a stowed position and a deployed position, a hydraulic actuator operably coupled to move the thrust-reversing element between the stowed position and the deployed position, and a fluid control system configured to operate the hydraulic actuator, the fluid control system having an electrohydraulic servo valve operable to selectively route fluid between a pressurized fluid source, the hydraulic actuator, and a fluid return reservoir, and a bypass fluid line providing fluid communication between the hydraulic actuator and the fluid return reservoir independent of the electrohydraulic servo valve.

Abstract: An assembly is for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, a linkage mount and an actuation linkage. The blocker door is pivotally coupled to the translating structure. The linkage mount includes a mount link, a mount spring and a mount stop. The mount link is pivotally coupled to the fixed structure about a pivot axis. The mount spring is configured to bias the mount link about the pivot axis against the mount stop. The actuation linkage operatively couples the blocker door to the mount link.

Abstract: A method of propulsion includes providing a high-speed-launch ramjet boost (HSLRB) stage and HSLRB engine attached to a launch aircraft providing a speed ?1.5 Mach. The HSLRB engine includes a combustion system and inlet(s) for air flow to the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator exhausts gas from combustion. A processor receives sensing signals from sensor(s) during flight that provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle, and if the inlet is a VG inlet to an inlet actuator to dynamically control the VG inlet shape. The HSLRB engine is ignited while attached to the aircraft at 1.5 to 1.99 Mach if assisting the aircraft to accelerate to 2.0 Mach, or at a speed of ?2.0 Mach if the aircraft can accelerate to 2.0 Mach autonomously, then the HSLRB stage is separated from the aircraft.

Abstract: Systems, methods, and devices for transmitting and controlling ignition output of a controller having a power source, a programmable interface, a wireless transmission module, and an ignition output unit are disclosed.

Abstract: A gas injector for injecting a gaseous fuel. The gas injector includes a solenoid actuator including an armature, an internal pole, and a coil; a closure element which opens and closes a gas path on a valve seat, the armature being connected to the closure element; a closed lubricant chamber filled with a lubricant and in which the armature is arranged, the lubricant ensuring the armature is lubricated; a flexible sealing element sealing the lubricant chamber in relation to the gas path, and a braking device which is arranged in the lubricant chamber and is configured to brake the closure element during a process of restoring the gas injector from the open into the closed state. The braking device has a brake pin, a damping chamber that is filled with lubricant and is in fluid communication with the lubricant chamber, and a resilient brake element.

Abstract: A method is disclosed of testing operability of a vapor blocking valve (VBV) in a first passageway that is fluidly arranged between a fuel tank and a carbon canister. A canister valve solenoid (CVS) is arranged in a second fluid passageway that fluidly interconnects the carbon canister and an atmospheric port. The method includes obtaining a first desired pressure in the first passageway, closing the VBV, opening the CVS, monitoring a first test pressure in the first passageway with a pressure sensor, obtaining a second desired pressure in the first passageway, opening the VBV, opening the CVS, monitoring a second test pressure in the first passageway with the pressure sensor, comparing the first and second test pressures, and determining the VBV operability based upon the comparing step.

Abstract: An engine includes a cylinder and a cylinder head stacked on an upper portion of a crankcase, an electronically controlled throttle interposed in an intake passage behind the cylinder head, and an exhaust pipe extending rearward from the cylinder head through a side of the cylinder. The electronically controlled throttle includes a throttle valve provided in the intake passage and an actuator that opens and closes the throttle valve. The actuator is disposed on an opposite side of the exhaust pipe with respect to a vehicle center line extending in a vehicle front-rear direction.

Abstract: An alternative fuel management system may include a base configured for arrangement on a supporting floor or other framework of a vessel and configured to support alternative fuel supply equipment. The system may also include a sealed enclosure sealingly coupled to the base and configured to surround the alternative fuel supply equipment. The system may also include the alternative fuel supply equipment and it may be arranged within the sealed enclosure. The alternative fuel supply equipment may include a high-pressure pump, a fuel filter, a transfer pump, and a high-pressure fuel delivery line extending across the sealed enclosure and configured to provide alternative fuel from the high-pressure pump to a combustion engine. The alternative fuel management system may also include a purge fluid system configured to deliver purge fluid to the combustion engine from a source of purge fluid.

Abstract: A vehicle has a frame, a front suspension assembly, a pair of skis, an endless drive track, and an internal combustion engine. The engine has: a motor-generator having a rotor and a stator, the motor-generator being operable in motor mode and in generator mode; a recoil starter operable to rotate a crankshaft of the engine via the rotor in a same direction as does the motor-generator in generator mode; at least one sensor adapted for sensing at least one engine parameter; and an engine control unit (ECU) receiving a signal from the at least one sensor, the ECU controlling a rotation of the crankshaft by one of the motor-generator and the recoil starter based on the signal.

Abstract: The present invention is applied to a control device for controlling a vehicle that travels using a driving force of an engine. The control device for the vehicle includes the vehicle speed detection unit that detects the vehicle speed, and the automatic engine stop unit that performs the automatic engine stop after a prescribed time elapses from when the vehicle speed detection unit detects that the vehicle is in the stopped state. When a failure of the vehicle speed detection unit is detected, the automatic engine stop by the automatic engine stop unit is prohibited.

Abstract: The invention concerns a method for starting a hydroelectric turbine (10) in a pumping mode, said turbine being provided with a runner (6) mechanically coupled to a shaft line (8) and a variable speed electric motor connected to a grid, a distributor (4) comprising guide vanes to control a flow of water to said runner, the method comprising: a) a step of operating the variable speed motor at least partly at fixed speed, said guide vanes being only partially opened, and of defining or calculating: data of a plurality of hydraulic characteristics (C1, C2, Ci) of the turbine for an operation without cavitation; data of an operation range of the electric motor, giving the speed of the motor as a function of its power; b) then a step of operating the turbine in a power control mode.

Abstract: A hydrodynamic electrification system that generates electricity from water moving from a high side to a low side and around a structure that divides the low side from the high side generally includes a water transport system that directs the water from the high side presenting a hydraulic head, over the structure, and to the low side. The system includes a power extraction system having a wheel that receives the water from said water transport system and a mounting system having a high side anchor that connects near an intake to the water transport system at the high side and having a low side anchor that connects to the power extraction system at the low side.

Abstract: The invention relates to a wave driven electrical generator having a single panel, or an array of panels that may be triangular in shape or may have another shape. A movable connection is provided between the panels to allow relative movement in two dimension or three dimensions. The movable connection may include at least one panel link has a length that is at least as long as the width of the panels to facilitate stacking of the panels for storage. One or multiple generators may be mounted on each panel and may be housed in a cavity where it is protected from damage and/or exposure to water. The area of coverage of a panel array includes open areas within the array of panels that define less than 20% of the area of coverage thereby facilitating the generation of maximum amount of power with a relatively small footprint.

Abstract: A wave energy production apparatus for producing energy from the heave motion of the surface of a body of water. It has one or more compression module which comprises a piston and a cylinder assembly and a reciprocating assembly positioned around the compression module, which is operatively connected to cylinder, such that, in Generation Mode, reciprocates together with the cylinder relative to the piston of the compression module due to the movement caused by the heave and sinking movement of the surface of the body of water.

Abstract: A kelp-inspired marine energy converter (MEC) device having a plurality of strips of flexible electroactive materials connected to a power conditioning module and anchored to a structure (such as the ocean floor) is described. The movement of the strips caused by water motion or current action (i.e., water motion) converted by the electroactive material to electrical energy.

Abstract: This disclosure is directed to hydrodynamic electric generators, including their structural design, methods of deployment, anchoring systems, drive systems and control systems. The system can be scaled from ones that can be hand carried to large, stationary devices that can generate up to and greater than 20 kw in a current of 3 knots. In a stationary system, the device can be anchored to an underwater floor by an anchoring device supported by four adjustable legs. These legs can eliminate the need for extensive mooring lines, providing the device with a small footprint that is non-hazardous to marine animals or vegetation. Individual components, such as rotors, generators and other mechanical components can be modularly installed for easy removal and servicing without having to disturb the entire system.