Abstract: In various embodiments, foam is compressed to store energy and/or expanded to recover energy.

Abstract: A power source apparatus includes a controller that carries out horsepower control to determine a flow rate of a hydraulic pump in accordance with a discharge pressure of the hydraulic pump detected by a pump pressure determination sensor. In horsepower control, the controller determines the flow rate such that a maximum input setting for the hydraulic pump defined by the discharge pressure and the flow rate is greater than a maximum output of the engine when the discharge pressure is a first discharge pressure, gradually becomes smaller as the discharge pressure changes from the first discharge pressure towards a higher pressure, and becomes smaller than the maximum output of the engine when the discharge pressure is a second discharge pressure.

Abstract: A pneumatic mechanism for a timepiece, is disclosed, which comprises a mechanical energy source, the pneumatic mechanism being arranged to recharge the mechanical energy source, and comprising a sealed chamber capable of alternately expanding and contracting in volume as a function of variations in the surrounding temperature. The sealed chamber may contain a mixture of reactants comprising a metal alloy arranged in contact with a gas and capable of undergoing at least one phase change as a function of variations in the surrounding temperature. The mixture of reactants advantageously has a coefficient ?P/?T substantially higher than about 0.01 bar·° C.?1 and with operating ranges between about 0 and about 50° C. in temperature and between about 1 and about 50 bar in pressure. Furthermore, the minimum possible difference between temperatures associated with consecutive contrariwise variations in the surrounding temperature may be smaller than or equal to about 4° C.

Abstract: A vehicular hydraulic-pressure-generation device wherein a first bush compressively deforms due to pressure from a simulator piston that moves when hydraulic pressure produced when a brake pedal is depressed is transmitted into a cylinder part. Said vehicular hydraulic-pressure-generation device thus creates artificial reaction-force characteristics with respect to the position of the brake pedal. The aforementioned first bush has a third elastic modulus, which is smaller than a second elastic modulus, and is provided in parallel with a first return spring. The compressive deformation of the first bush occurs over a second region that overlaps a first region in which compressive deformation of the return spring primarily occurs. This makes the brake pedal move more smoothly, reducing the feeling of incongruity resulting from a V-shaped singularity in the reaction-force characteristics with respect to brake pedal position.

Abstract: An air supply device of a gas engine having a turbocharger includes a first intake passage configured to guide the mixture of outdoor air and unpurified gas into the turbocharger, a second intake passage configured to guide indoor air into the turbocharger, a filter configured to remove a solid impurity in the unpurified gas which is disposed in the first intake passage, a first damper capable of opening and closing the first intake passage disposed on the downstream side of the filter in the first intake passage, a heating unit for heating the indoor air disposed in the second intake passage, a second damper capable of opening and closing the second intake passage disposed on the downstream side of the heating unit in the second intake passage, and a damper control device configured to control the opening degree of each of the first and second dampers.

Abstract: In a turbine for an exhaust gas turbocharger having a turbine housing with a turbine rotor rotatable supported therein and including spiral channels for directing exhaust gas onto the turbine wheel, at least one annular blocking element is supported between the spiral channels and the turbine wheel so as to be rotatable in the peripheral direction of the turbine wheel and additionally movable in the axial direction of the turbine wheel for a controlling the exhaust gas flow to the turbine wheel between impulse turbine mode when extended into the space between the turbine wheel and the spiral chamber and an accumulation made when retracted, with the gas flow through the turbine wheel or by-passing the turbine wheel being adjustable by rotation of the blocking element.

Abstract: A dual hybrid heating apparatus, method of assembly and operation to pre-heat vaporizable fluid by free heat sources—waste heat from heat recovery units and insolation. The pre-heated vaporizable fluid is routed to where a parabolic dish solar concentrator vaporizes it to turn a blade of a turbine generator to generate electricity. Heat is extracted from the vapor to form condensate, but the vapor also heats the condensate before being cooled by heat exchange with fluid cooled by a cooling tower.

Abstract: A steam turbine facility is provided which is capable of appropriately sealing a gap between members made of cast material of Ni-based alloy even under the steam-temperature condition of 650° C. or higher, and which includes a first member and a second member whose base material is formed of cast material composed of at least one of Ni-based alloy, austenite steel, or high-chrome steel, form a space where the steam of 650° C. or higher flows. Between the first member and the second member, a metal gasket is provided which has a plurality of portions in line contact with the first member and the second member. On the first member and the second member, a first high-hardness layer which is harder than the base material, is provided at least in a portion where each of the first member and the second member is in line contact with the metal gasket.

Abstract: A method is provided for connecting at least one further steam generator to a first steam generator in a power plant. The power plant includes at least two steam generators and a steam turbine, in which a fluid used to drive the steam turbine is conveyed in a fluid circuit having a plurality of steam systems. The steam systems are assigned individual steam generators and are able to be separated from one another by shut-off valves. The fluid of at least the first steam generator is connected to the steam turbine. The method involves opening the shut-off valve of at least one first steam system of the at least one further steam generator before the steam of the at least one further steam generator has reached approximately the same steam parameters as the steam of the first steam generator, so that steam can flow into the further steam generator.

Abstract: There is provided a protection device for a turbine exhaust chamber and a condenser, having, a condenser, a turbine exhaust chamber casing covering the steam turbine and the condenser, an atmosphere discharge disc for discharging atmosphere when a pressure reaches a first predetermined value, a temperature measuring unit for measuring a temperature in the turbine exhaust chamber casing, a first setter for setting a second predetermined value, an output unit for producing an external output, based on the measured temperature and the second predetermined value, when a pressure corresponding to the temperature becomes higher than or equal to the second predetermined value related to pressure or when the temperature becomes equal to or higher than the second predetermined value related to temperature, and a releasing unit for releasing the steam in the turbine exhaust chamber casing to an exterior when the output unit produces the external output.

Abstract: A waste heat recovery system is provided. The waste heat recovery system includes a Rankine cycle system for circulating a working fluid. The Rankine cycle system includes at least one first waste heat recovery boiler configured to transfer heat from a heat source to the working fluid. The Rankine cycle system also includes a first expander configured to receive the heated working fluid from the at least one first waste heat recovery boiler. Further, the Rankine cycle system includes a second expander and a third expander coupled to at least one electric generator. The waste heat recovery system also includes a condenser configured to receive the working fluid at low pressure from the first expander, the second expander and the third expander for cooling and a pump connected to the condenser for receiving a cooled and condensed flow of the working fluid from the condenser.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.

Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.

Abstract: A combustion burner 10A according to one embodiment of the present invention includes: a fuel nozzle 110; a burner tube 120 forming the air passage 111 between the burner tube 120 and the fuel nozzle 110; swirler vanes (swirler vanes) 130 arranged in a plurality of positions in the circumferential direction on the external circumferential surface of the fuel nozzle 110, each extending along the axial direction of the fuel nozzle 110, and gradually curving from upstream toward downstream; and a liquid fuel injecting hole 133A from which a liquid fuel is injected to a surface of each of the swirler vanes 130. The combustion burner 10A also includes multi-purpose injecting holes 11-1 to 11-3 as a cooling unit that cools a part of a vane pressure surface 132a of the swirler vane 130 on which the liquid fuel LF hits.

Abstract: A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.

Abstract: A brazed end cover assembly for a gas turbine combustor using Au-Ni braze is disclosed. The end cover assembly may include an end cover with openings, a flow insert, first and second gaps between the end cover and the flow insert, and first and second braze joints formed at the first and second gaps, wherein the braze materials used comprises Au and Ni. A method of brazing a flow insert into an end cover is also disclosed. The method may include providing an end cover and a flow insert with first and second gaps therebetween; applying a braze material to an outer surface of the flow insert, wherein the braze material comprises Au and Ni; inserting the flow insert into the end cover; heating the assembly to a brazing temperature for some time; and cooling the resulting brazed assembly to room temperature.

Abstract: A transition duct for a combustor of a gas turbine generally includes an end frame that has a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion between the radially outer and inner portions. A slot may be in at least one of the radially outer portion, radially inner portion, first side portion, or second side portion of the end frame. A first plurality of axially extending passages may pass through the end frame and intersect with the slot. A terminal end of the end frame may be uninterrupted adjacent to the slot.

Abstract: An exemplary igniter assembly for a turbomachine includes an igniter extending along an axis from an igniting end portion to an opposing end portion. The igniting end of the igniter is configured to be received within a bore of a tube. An annular seal restricts flow between the igniting end and the tube.

Abstract: A combustion nozzle includes a mixing section and an exit section. The mixing section includes an air inlet, and a fuel inlet. The exit section includes a plurality of jets formed in a predefined pattern on an exit surface. A ratio of a core area of the plurality of jets to an exit surface area is greater than 0.25.

Abstract: The invention relates a method for operating a power plant with a single shaft gas turbine, in which the gas turbine is operated at a constant speed which is below the speed at which the gas turbine is turning when the first generator is synchronized to an electric grid. The proposed method ensures good stable combustion with low emissions, a high turbine exhaust temperature, and minimized fuel consumption.

Abstract: Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved by diverting a portion of the recirculating exhaust gas and combining it with the oxidant feed to maintain a constant oxygen level in the combined oxidant-exhaust stream fed to the combustion chamber.

Abstract: A method and system for controlling a two-shaft turbine engine, the two-shaft turbine engine including a gas producer having a compressor with adjustable inlet guide vanes. The method includes monitoring a rotational speed of the gas producer, maintaining an inlet guide vane angle constant when a rotational speed of the gas producer is below a threshold value, and adjusting an inlet guide vane angle of the compressor at a predetermined rate when the rotational speed of the gas producer is above the threshold value.

Abstract: Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved through methods or systems that ensure delivery of a consistent mass flow rate of oxidant to the combustion chamber.

Abstract: A method of co-firing fuel within a gas turbine engine. The method may include injecting a first fuel into a combustion system of a gas turbine engine. The first fuel may include a high energy liquid fuel. The method may also include injecting a second fuel into the combustion system. The second fuel may include a gaseous low Wobbe fuel. Only the first fuel may be injected during a first mode of operation. The first fuel and the second fuel may be injected simultaneously and discretely during a second mode of operation.

Abstract: An LNG fuel system for gas turbine engine systems is disclosed that allows more efficient management of cryogenic fuels such as LNG to reduce emissions and improve engine efficiency. In one configuration, an intercooled, recuperated gas turbine engine comprises an LNG tank incorporating a liquid-to-vapor LNG fuel circuit in parallel with a vapor fuel circuit. In a second configuration, an alternate vapor fuel circuit is disclosed. In either configuration, the fuel in the liquid fuel circuit is vaporized and heated by the engine's intercooler or by both the engine's intercooler and/or a heat exchanger on the exhaust. In another configuration, both the fuel in the liquid-to-vapor LNG fuel circuit and the vapor fuel circuit are heated by a heat exchanger on the exhaust.

Abstract: A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.

Abstract: A method to start up and manage a combined cycle thermal plant for energy production comprising the execution according to a set sequence of a plurality of functional groups.

Abstract: An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a second portion of the turbomachine.

Abstract: An aircraft engine includes a precooler disposed within a nacelle. The precooler defines an ambient air passage and a bleed air passage. Air passes through the precooler from an ambient air inlet to an ambient air outlet. Bleed air passes through the precooler from a bleed air inlet to a bleed air outlet. Heat is transferred between the air and the bleed air via heat exchange within the precooler. At least one pressure relief door disposed proximate to the air outlet of the engine. A controller is operatively connected to the pressure relief door. The controller at least opens the pressure relief door based on a demand for increased flow of air through the ambient air passage.

Abstract: A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

Abstract: A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.

Abstract: A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.

Abstract: A cooling apparatus bifurcates and regulates cooling airflow provided to a mid-turbine frame. The cooling apparatus includes a flow metering tube and a metering plate. The flow metering tube includes a top portion and a tube portion, wherein the top portion includes a first central aperture that directs a first cooling airflow into the tube portion and a first plurality of apertures located circumferentially around the central aperture that directs a second cooling airflow to a portion outside the tube portion. The metering plate is located on the top portion of the flow metering tube, wherein the metering plate includes a second central aperture aligned with the central aperture of the flow metering tube and a second plurality of apertures located circumferentially around the central aperture, wherein a size of the second central aperture meters the first cooling airflow and a size and number of the second plurality of apertures meters the second cooling airflow.

Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.

Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes. One of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).

Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes, wherein one of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).

Abstract: An apparatus for storing hydrogen and magnetic energy includes a storage tank for liquefied hydrogen with an inlet line for compressed hydrogen and an outlet line for hydrogen at a relatively low pressure. The apparatus includes a superconducting magnetic energy store, which comprises a magnetic coil relative to which electrical energy can be supplied or withdrawn via power supply lines to the magnet coil, the energy being located in a cryogenic tank provided with a cooling device and being held at operating temperature. The storage tank for liquefied hydrogen includes cooling device, at least one regenerator, with a heat-absorbing and heat-emitting storage medium, a warm side and a cold side. From the warm side, the compressed hydrogen and, from the cold side, liquefied hydrogen can be supplied from the storage tank for liquefied hydrogen. A relief valve is located in the field region of the at least one magnet coil.

Abstract: An oxygen liquefier system may be configured to defrost an oxygen line included therein. The system may include one or more sieve beds, a liquid oxygen reservoir, an oxygen line, a controller, a heating apparatus, and/or other components. The one or more sieve beds are configured to extract oxygen from air obtained from an ambient environment. The liquid oxygen reservoir is configured to store oxygen extracted at the one or more sieve beds that has been liquefied. The oxygen line is configured to provide fluid communication between the one or more sieve beds and the liquid oxygen reservoir. The controller is configured to detect a blockage caused by frozen liquid within the oxygen line based on a liquid oxygen production rate. The heating apparatus is configured to defrost the oxygen line to melt frozen liquid within the oxygen line responsive to the detection of the blockage.

Abstract: A monitoring system for monitoring operation of a refrigerant-cycle system is disclosed. A first temperature sensor measures a first temperature of air at a first location downstream of an evaporator. A second temperature sensor measures a second temperature of air a second location upstream of the evaporator. A processing system determines a temperature drop across the evaporator based on the first temperature, the second temperature, and a humidity of air. The processing system that determines whether airflow through the evaporator is restricted based on the temperature drop across the evaporator.

Abstract: A monitoring system for monitoring operation of a refrigerant-cycle system is disclosed. A condenser unit sensor measures an operating characteristic of a condenser unit, the condenser unit including a condenser and a compressor. An evaporator unit sensor measures an operating characteristic of an evaporator unit, the evaporator unit including an evaporator and a fan. An electrical sensor measures an electrical quantity indicative of power consumption of the refrigerant-cycle system. A processing system calculates an efficiency of the refrigerant-cycle system based on the power consumption of the refrigerant-cycle system, the operating characteristic of the condenser unit, and the operating characteristic of the evaporator unit.

Abstract: A monitoring system for monitoring operation of a refrigerant-cycle system is disclosed. A plurality of sensors measure operating characteristics of the refrigerant-cycle system. The refrigerant-cycle system includes a condenser unit and an evaporator unit. The condenser unit includes a condenser and a compressor. The evaporator unit includes an evaporator and a fan. A processing system receives the measurements from the plurality of sensors and outputs data regarding operation of the refrigerant-cycle system to a remote monitoring system.

Abstract: A monitoring system for monitoring operation of a refrigerant-cycle system is disclosed. A differential pressure sensor measures a pressure difference between: (i) air at a first location upstream of an evaporator of the refrigerant-cycle system; and (ii) air at a second location downstream of the evaporator of the refrigerant-cycle system. An electrical sensor measures an electrical quantity indicative of power consumption of the refrigerant-cycle system. A processing system determines whether airflow through the evaporator is restricted based on the pressure difference. The processing system calculates an efficiency of the refrigerant-cycle system based on the power consumption of the refrigerant-cycle system.

Abstract: A monitoring system for monitoring operation of a refrigerant-cycle system is disclosed. An electrical sensor measures an electrical quantity indicative of power consumption of a component of the refrigerant-cycle system. A processing system selectively identifies a condition indicative of an airflow restriction through the refrigerant-cycle system based on the power consumption of the component.

Abstract: A control system for a crank case heater for an inverter operated compressor of a cooling system includes a contactor operably connected to the crank case heater and an inverter controller compressor and at least one compressor temperature sensor disposed at the compressor to sense a compressor temperature and an compressor internal temperature sensor. A controller is operably connected to the crank case heater and the at least one compressor temperature sensor and configured to close the contactor to energize the crank case heater independently from operation of the compressor when the at least one compressor temperature sensor senses a compressor temperature below a desired threshold.

Abstract: An upwardly helical flow path of mechanically refrigerated air inside a spiral freezer may be used to chill or freeze products.

Abstract: A liquid or suspension is formed into frozen particles through contact of a diverging cone spray of the liquid or suspension with a converging cone spray of a liquid cryogen. The converging cone spray of the liquid cryogen is sprayed from a converging annulus defined by an outer surface of an atomization nozzle and an inner surface of a liquid cryogen housing surrounding the atomization nozzle.

Abstract: Systems and methods are disclosed for processing hot, humid air resulting from an industrial process, such as paper production. These systems and methods allow a large amount of water to be recovered from the air and the plume emitted into the environment to be reduced, all with reasonable energy consumption. The exhaust stream of air is passed through two heat exchangers, which cool the exhaust air by heating respective streams of water. The heated streams of water are routed to and cooled by an absorption cooler before being returned as input to the heat exchangers. Some embodiments may also include a scrubber, which allows direct air-water contact, positioned between the two heat exchangers. The scrubber also aids removal of pollutants. Some embodiments may mix heated outside air with the exhaust stream of air prior to discharge in order to reduce the emitted plume.

Abstract: An air conditioning system for a mine that operates in a mine environment. A condenser. A refuge system for protecting users from a toxic environment. The system comprises a refuge shelter. An evaporator. A method for cooling a refuge shelter. An inflatable chamber having an airlock, the airlock includes a tube that extends from the chamber's outer surface into the chamber's interior.

Abstract: A cooling system includes; an evaporator evaporating a refrigerant by heat exchange with room air; a water-cooled condenser being arranged above the evaporator and condensing the refrigerant by heat exchange with cold water; a cold-water flow control valve controlling the flow rate of the cold water supplied to the water-cooled condenser; a refrigerant cooling tower being arranged above the evaporator and condensing the refrigerant by heat exchange with outside air; a blower being arranged at the refrigerant cooling tower and blowing the outside air; a refrigerant-temperature detector detecting the temperature of the refrigerant condensed by the water-cooled condenser and/or the refrigerant cooling tower; and a controller changing at least one of the opening in the cold-water flow control valve and the rotational speed of a motor in the blower according to the temperature.