Abstract: The invention relates to a device and a method for the recovery of waste heat from an internal combustion engine (2), according to which a feed pump (6), a heat exchanger (8), an expansion engine (10) and a capacitor (12) are arranged in a circuit (4) containing a circulating working medium. A bypass connection (14) is mounted in parallel to the expansion engine (10), in the circuit (4), the expansion engine (10) being coupled to the circuit (4), or decoupled therefrom, according to an operating situation of the internal combustion engine (2).

Abstract: A hydroelectric and geothermal system includes a fluid communication channel that includes a first portion that extends from the earth's surface toward a subterranean hot area, a second portion connected to the first portion and in thermal communication with the subterranean hot area, and a third portion connected to the second portion and that extends to the earth's surface. A first turbine generator is configured to convert kinetic energy of a fluid flowing substantially under the influence of gravity in the first portion of the fluid communication channel into electrical energy. A second turbine generator is configured to convert kinetic energy of a vapor flowing within or out from the third portion of the fluid communication channel into electrical energy. The system also includes a valve arrangement configured for manipulation to hold the fluid in the second portion of the fluid communication channel in thermal communication with the subterranean hot area to produce the vapor.

Abstract: A thermal power station system has at least one heat engine connected to at least one work receiver. The heat engine is arranged to be able to utilize a working fluid alternating between liquid and gas phase. In the heat engine is arranged at least one heat exchanger in thermal contact with at least one expansion chamber. A method is for energy supply to a building or a vessel.

Abstract: Provided are a solar light collecting mirror which can achieve high light collection efficiency even in a solar thermal power generation system such as a tower solar thermal power generation system in which the distance from a reflecting mirror to a heat collector is a long distance between several tens of meters and several hundreds of meters, can be manufactured easily and inexpensively, and can easily achieve concave mirrors with various curvatures, and a solar thermal power generation system using the same.

Abstract: The invention relates to a solar reflector for concentrated solar power plants, comprising a substrate a) in composite material based on resin reinforced with cut fibres, said substrate having means b) for attachment without either perforation or gluing, and a metallic reflective coating layer c). The reflector of the invention is used in solar collectors and in solar plants operating on concentrated solar power, more particularly for producing electricity, steam and/or heat.

Abstract: A method for the production of alcohol and other bioproducts from power boiler woody biomass extract containing hemicelluloses, with or without combining extract from wood prior to Kraft cooking. The process is integrated with the host Kraft pulp mill plant process to minimize the heat loss from extracting hemicelluloses and the energy used in the process.

Abstract: A method for reducing NOx and recovering waste heat from a stream of exhaust gas from a fossil fuel fired turbine includes contacting the stream of exhaust gas between an economizer and an evaporator with ozone gas to convert the NO to nitrogen dioxide (NO2) thereby forming a stream of exhaust gas comprising NO2 and residual NO. The method further includes, contacting the stream of exhaust gas comprising NO2 and residual NO with water mist to create an exhaust stream comprising nitric acid (HNO3) and residual NO. The method further includes cooling the stream of exhaust gas comprising HNO3 and residual NO, collecting a first residual water film on a first condensing medium to capture the HNO3 and removing the first water film and HNO3.

Abstract: Disclosed are devices which provide a practical means of extracting energy from the electromagnetic zero-point energy which permeates the universe. This is done by exploiting the Casimir-van der Waals' forces to accelerate a fluid through the device and exhaust it with a higher velocity and energy than that with which it entered. This kinetic energy gained by the fluid may then be used to do work, such as spin a turbine for power generation, or provide thrust for direct propulsion. These devices do not consume fuel nor any non-renewable resources during operation and they are capable of generating significantly more energy than they require to start or to be manufactured.

Abstract: A combustor generally includes a plate that extends radially and circumferentially within at least a portion of the combustor. The combustor may also include a shroud that at least partially surrounds the plate and a plurality of tubes that extend through the plate. One or more flexible couplings may at least partially surround at least some of the plurality of tubes and the one or more flexible couplings may be connected to the plate.

Abstract: A resonance damper for damping acoustic oscillations within a combustor housing of a gas turbine engine is provided. The resonance damper includes a container, an opening, and a pipe. The container is configured to be attached to an interior wall of the combustor housing and has a cavity. The opening is provided on the container. The pipe is rigidly connected to the opening to define the resonance damper with the cavity.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for a working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provide fluid communication for fuel to flow through the tube wall and into the tube, and the fuel ports are non-circular.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.

Abstract: A combustor includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface. A shroud circumferentially surrounds at least a portion of the end cap, wherein the shroud at least partially defines a fuel plenum between the upstream surface and the downstream surface. A combustion chamber downstream from the end cap defines a longitudinal axis. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap to the combustion chamber. A transition duct circumferentially surrounds at least a portion of the combustion chamber downstream from the end cap and curves tangentially from the longitudinal axis.

Abstract: A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism.

Abstract: A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.

Abstract: A system includes a fuel nozzle. The fuel nozzle includes a center body configured to receive a first portion of air and to deliver the air to a combustion region. The fuel nozzle also includes a swirler configured to receive a second portion of air and to deliver the air to the combustion region. The swirler includes an outer shroud wall, an inner hub wall, and a swirl vane. The swirl vane includes a radial swirl profile at a downstream edge of the swirl vane. The radial swirl profile includes a region extending from the outer shroud wall to a first transition point and a second region extending from the transition point to the inner hub wall. At least one of the first and second regions is substantially straight and at least one of the first and second regions is arcuate.

Abstract: A combustor generally includes a liner that at least partially defines a combustion chamber within the combustor. The liner may generally include a hole that extends through the liner and that at least partially defines a mating surface. An insert having an outer surface extends at least partially through the hole. A projection that at least partially defines a mating surface at least partially circumferentially surrounds the insert outer surface. A joint between the projection mating surface and the hole mating surface provides a connection point between the projection mating surface and the liner hole mating surface.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors.

Abstract: A system for cooling a gas turbine with an exhaust gas provided by the gas turbine generally includes an exhaust gas recirculation system including an exhaust gas scrubber. The exhaust gas recirculation system is disposed downstream from the gas turbine and may receive at least a portion of the exhaust gas provided by the gas turbine. The system may also include a moisture separator located downstream from the exhaust gas recirculation system, and a cooling circuit configured to connect to one or more cooling circuit inlets. The one or more cooling circuit inlets may provide fluid communication between the cooling circuit and the gas turbine.

Abstract: A fuel injector includes a flow path for fuel air mixture to a combustor extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery at least partially encircling the flow path. The gallery may include a plurality of fuel spokes configured to deliver liquid fuel from the gallery to the flow path. The fuel injector may also include an annular outer housing circumferentially positioned about the gallery to form an insulating air cavity at least partially around the gallery. The outer housing may include at least one purge hole to provide communication between the insulating air cavity and outside the outer housing of the injector.

Abstract: A combustion nozzle includes at least one passage having a mixing section and an exit section. The mixing section includes an air inlet, and a fuel inlet. The mixing section has a first length and a first diameter. The exit section has a second length different from the first length, and a second diameter different from the first diameter.

Abstract: A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

Abstract: A flow control system is provided. The flow control system includes at least one control valve coupled to at least one nozzle of a turbine engine, wherein the control valve is configured to regulate fluid flow in a first direction or a second direction. The first direction is when the fluid is channeled from a compressor to the nozzle and the second direction is when the fluid is channeled from the nozzle to an exhaust section of the turbine engine. A controller is coupled to the control valve and is configured to control the fluid flow in the first direction during operation of the turbine engine and to change the direction of the fluid flow from the first direction to the second direction to facilitate reconditioning of the turbine engine.

Abstract: A gas turbine engine includes a compressor for generating compressed air. The compressor includes a rotor defined by a plurality of axial disks including a first disk and a second disk. A first row of blades extends radially outwardly from the first disk, and a second row of blades extends radially outwardly from the second disk. A row of cantilevered vanes is located at an axial location between the first row of blades and the second row of blades. A bleed path extends at least partially through the second disk and includes an entrance at an axial location between the first row of blades and at least a portion of the row of cantilevered vanes. The entrance communicates with a compressed air flowpath through the compressor.

Abstract: A system includes a turbine. The turbine includes a rotor, a stator, and a cooling insert. The rotor includes multiple turbine blades. The stator surrounds the rotor and includes an inner wall surrounding the multiple turbine blades, an outer wall surrounding the inner wall, and a cooling chamber between the inner wall and the outer wall. The cooling insert extends through an opening in the outer wall into the cooling chamber. The insert includes a side wall extending around an axis, an end wall crosswise to the axis, a set of lateral ports extending through the side wall, and end ports extending through the end wall. The cooling insert is configured to direct a cooling fluid through the set of lateral ports and end ports into the cooling chamber.

Abstract: A cooling structure for a servo valve includes a shroud to enclose at least a portion of the servo valve; and a base connected to the shroud to define a cooling chamber surrounding the servo valve, the base including an inlet port to receive cooling air, a flow channel connecting to the inlet port and a plurality of flow passages connecting the flow channel to the cooling chamber to allow cooling air flow from the inlet port into the cooling chamber.

Abstract: A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.

Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a flexible seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct. The flexible seal includes a sheet having a first surface, an opposing second surface, and a peripheral edge therebetween.

Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct.

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.

Abstract: A fan blade having a body with a dovetail and an airfoil extending radially outwardly. The airfoil includes a pair of skins spaced to form an internal core, which define a pressure side and a suction side, and extending from a radially inner end to a radially outer tip. The core receives a plurality of braided tubes, with the tubes extending with at least a component in a radially outward direction. A fan and an engine are also described.

Abstract: A nacelle structure for a gas turbine engine assembly includes a fan case, an inlet, and a noise attenuation device. The fan case is configured to be disposed about a fan section of the gas turbine engine, which fan section has a diameter D. The inlet is attached to the fan case and extends axially forward of the fan case. A hilite of the inlet is spaced a distance L from a region in which the fan section is configured to be disposed. A ratio L/D is less than about 0.6. The noise attenuation structure covers a portion of an inner surface of the fan case and the inlet.

Abstract: The present invention provides a magnetic refrigerant bed, which is a column composed of n magnetic refrigerant bed components, and these n magnetic refrigerant bed components are arranged in a descending order according to Curie temperatures or phase transition temperatures of the magnetic refrigeration materials used, wherein n=1-1000. The magnetic refrigerant bed components are flat sheets (1), straight wave-shaped sheets (2) or zigzag wave-shaped sheets (3) which can easily form a magnetic refrigerant bed with high specific surface area and flow channels of low resistance.

Abstract: A cryocooler may comprise a first stage, a second stage and a phase control device. The first stage may define a first volume. The second stage may define a second volume. The phase control device may be positioned between the first stage and the second stage to receive a flow of working fluid between the first stage and the second stage. The phase control device may comprise a flange and a plunger. The flange may be positioned along a longitudinal axis parallel a direction of the working fluid flow. The plunger may be translatable along the longitudinal axis at least partially within the flange. The plunger and the flange may be sized such that the plunger and the flange define a gap there between and a dimension of the gap is determined by a position of the plunger along the longitudinal axis.

Abstract: A single cryogenic liquid vessel in which two cryogenic machines are disposed, supported and operable in tandem. In one embodiment the two cryogenic machines are operable in series or individually, and in another embodiment the two cryogenic machines are operable in parallel or individually. Preferably the machines are supported intermediately relative to the vessel, or at a top of the vessel. In various embodiments the machines are pumps or turbines or expanders.

Abstract: The present invention relates to a floating LNG plant (1, 1?, 100) comprising a converted LNG carrier with a hull and a plurality of LNG storage tanks (4, 104) wherein in that the floating LNG plant (1, 1?, 100) comprises:—at least one sponson (2, 2?, 3, 3?, 102, 103) on the side of the hull, for creating additional hull volume,—process equipment (110) for LNG processing on the floating LNG plant (1, 1?, 100), and—a reservoir for storing fluids separated during the LNG processing, wherein said reservoir is formed by the ballast tank or in the space reserved for the ballast tank of the original LNG carrier.

Abstract: A transport refrigeration system includes an engine, a generator set, and a refrigeration system. An electronic control unit and/or a reefer controller are configured to obtain an engine operation condition value and a transport refrigeration system operation value respectively. A genset controller is configured to determine a fuel efficient engine operation speed that is associated with the engine and/or transport refrigeration system operation condition value. The genset controller instructs the electronic control unit to operate the engine at the fuel efficient operation speed.

Abstract: A method of controlling an air conditioning compressor in a heating ventilation and air conditioning system having a evaporator including a phase change material is presented. The method includes the steps of measuring an evaporator output air temperature, determining a state of charge value by calculating a difference between an estimated refrigerant temperature based on the evaporator output air temperature and a phase change material freeze temperature and integrating this difference over time and operating the air conditioning compressor to maintain the state of charge value between an upper and lower limit. A method of recovering braking energy in a vehicle containing a heating ventilation and air conditioning system having the evaporator including the phase change material is also presented.

Abstract: In an apparatus and method for chilling or freezing objects, an interior surface of a rotating drum includes recesses formed between prominences extending inwardly from the interior surface. One or more liquid CO2 nozzles inject solid CO2 towards the interior surface. The injected snow replenishes a depth of solid CO2 in empty or partially empty recesses and/or provides a fresh layer of solid CO2 on top of the objects. Because the interior surface is made of polyethylene and the depth of solid CO2 is replenished in empty or partially empty recesses, the product/drum sticking problem experienced by conventional apparatuses and methods is reduced or avoided. Optionally, the CO2 snow is injected into empty or partially empty recesses by at least one first liquid CO2 nozzle and is deposited on top of the objects by at least one second liquid CO2 nozzle so that each opposing surface of the object is in direct contact with solid CO2.

Abstract: A method for providing a refrigerant medium having a controlled flow temperature in a secondary cycle (20), wherein the refrigerant medium in the secondary cycle (20) takes up heat from one or more process coolers (22) and then gives off heat to primary water in a primary cycle (10) before it flows back to the process coolers (22), wherein at least two primary heat exchangers (12, 14) are present for cooling the refrigerant medium, in addition a bypass line (26) in the secondary cycle (20) branches off after exit from the process coolers (22) for bypassing the primary heat exchangers (12, 14), and the temperature in the secondary cycle (20) in the flow to the process coolers (22) is controlled via the setting of the bypass stream.

Abstract: Refrigeration systems with a purge for removing non-condensables from the refrigerant and an acid filter for remove acid from the refrigerant are provided. The acid filter can be operatively connected to the purge. Optionally, the purge can include a separating device for separating non-condensable gases from condensable refrigerant gases and an acid filter is provided to remove acid from the condensable refrigerant gases.

Abstract: A space conditioning system includes a hot gas reheat section and one or more modulating valves to direct a percentage of refrigerant flow to the hot gas reheat section. The hot gas reheat section includes multiple refrigerant circuits arranged in parallel. A control valve is used to allow the refrigerant to flow through selected ones of the multiple refrigerant circuits in response to the percentage of refrigerant flow directed to the hot gas reheat section, thereby varying the internal volume of the hot gas reheat section available to the refrigerant. Refrigerant charge hold-up within the hot gas reheat section can thereby be minimized.

Abstract: Refrigeration systems with a purge for removing non-condensables from an environmentally-suitable chiller refrigerant are provided. The refrigeration systems utilize an environmentally-suitable chiller refrigerant with a 100 year direct global warming potential (GWP) of less than 150. The refrigeration systems further include a remover to remove refrigerant-harmful gases from the chiller refrigerant.

Abstract: A refrigeration system (2) comprises a condenser/gas cooler (4), an intermediate expansion device (6) and a refrigerant collecting container (8); a normal refrigeration branch (10) connecting the refrigerant collecting container (8) to the condenser/gas cooler (4) said normal refrigeration branch (12) comprising a first expansion device (12), a first evaporator (14) and a compressor unit (16) of the normal refrigeration branch (10); a freezing branch (18) connecting the refrigerant collecting container (8) to the condenser/gas cooler (4), said freezing branch (18) comprising a second expansion device (20), a second evaporator (22), and a first compressor unit (24) and a second compressor unit (26) of said freezing branch (18), the first and second compressor units (24, 26) of the freezing branch (18) being connected in series.

Abstract: The present invention relates to compositions comprising at least one fluoroolefin and an effective amount of stabilizer that may be at least one phenol or a mixture of at least one phenol with other stabilizers. The stabilized compositions may be useful in cooling apparatus, such as refrigeration, air-conditioning, chillers, and heat pumps, as well as in applications as foam blowing agents, solvents, aerosol propellants, fire extinguishants, and sterilants.

Abstract: A heat exchange system for realizing an adequate heat exchange among a plural type of fluids uses a refrigerant radiator and a radiator which are combined to have one unit for enabling heat exchange between a refrigerant and a coolant, and decreases an inflow amount of the coolant flowing into the radiator when coolant temperature of the coolant flowing into the radiator is equal to or higher than a second standard temperature, which is set to be lower than a temperature of the refrigerant flowing into the refrigerant radiator, and is equal to or lower than a predetermined first standard temperature. In such manner, heat from the refrigerant is effectively transferred to an outside air by reducing an unwanted heat exchange between the refrigerant and the outside air.

Abstract: An expansion valve includes a shaft for transmitting the drive force to a valve element and a vibration-proof spring, set between the body and the shaft, which generates the sliding friction by biasing the shaft. The vibration-proof spring includes a spring body of a hollow tube shape, a spring part, which is integrally formed with a side wall of the spring body, and a bulging portion formed on the spring part in a protruding manner such that the tip of the bulging portion is placed opposite to a part of the shaft. When the bulging portion abuts against the shaft inserted to the vibration-proof spring, the spring part is placed in a position along the spring body or is warped outwardly from the spring body, so that the elastically reactive force resulting from the warped spring part allows the shaft to slide in a stabilized manner.

Abstract: An air conditioning system using outdoor air has a first heat exchanger, an evaporator, a condenser, and a first fan disposed on the interior side; and a second heat exchanger and a second fan disposed on the exterior side. An expansion valve and a compressor are further provided. An air conditioner has a first piping connected to the evaporator, the condenser, the expansion valve, and the compressor, for circulating a first refrigerant to perform a compression-type refrigeration cycle. An indirect outdoor air cooler has a second piping connected to the first heat exchanger and the second heat exchanger for circulating a second refrigerant to induce a heat exchange in the first heat exchanger between the second refrigerant and the indoor, and to induce a heat exchange in the second heat exchanger between the outdoor air and the second refrigerant.

Abstract: The disclosure relates to a unitary heat pump air conditioner (Unitary HPAC) that includes a refrigerant loop having a condenser, a refrigerant expansion device, and an evaporator hydraulically connected in series. An electrically driven compressor is provided to circulate a two-phase refrigerant through the refrigerant loop to transfer heat from the evaporator to the condenser. The unitary HPAC also includes a cold side chiller configured to hydraulically connect to a cold side coolant loop and is in thermal communication with the evaporator. The unitary HPAC further includes a hot side chiller configured to hydraulically connect to a hot side coolant loop and is in thermal communication with the condenser. The refrigerant loop transfer heat from the cold side chiller to the hot side chiller, thereby cooling the cold side coolant loop and heating the hot side coolant loop. The components of the unitary HPAC are mounted on a common platform.

Abstract: A geothermal system, comprising at least one geothermal column, comprising at least one spirally wound refrigeration coil configured to communicate with a heat pump compressor; a hollow tube having an outer wall of diameter substantially greater than that of said at least one spirally wound refrigeration coil and positioned so as to surround said at least one spirally wound refrigeration coil, said outer wall having a substantially rigid configuration such that said hollow tube maintains its shape; and a support member configured to retain a shape of said at least one spirally wound refrigeration coil and maintain a centrally located position of said at least one spirally wound refrigeration coil within said hollow tube; and a compressor section in communication with the at least one geothermal column and a climate system.