Abstract: A thermo-acoustic engine and/or cooler is provided and includes an elongated tubular body, multiple regenerators disposed within the body, multiple heat exchangers disposed within the body, where at least one heat exchanger is disposed adjacent to each of the multiple regenerators, multiple transducers axially disposed at each end of the body, and an acoustic wave source generating acoustic waves. At least one of the acoustic waves is amplified by one of the regenerators and at least another acoustic wave is amplified by a second one of regenerators.

Abstract: A heat exchanger is provided that includes plate pairs stacked one above the other. A first flow chamber is formed between the two plates of a plate pair by conducting a first fluid therethrough, a second flow chamber for conducting a second fluid therethrough, wherein the second flow chamber is formed between two adjacent plate pairs, an inlet opening for introducing the first fluid, and an outlet opening for discharging the first fluid. The plates have at least one expansion opening, in particular at least one expansion slit, for reducing stress in the plates. The heat exchanger can withstand high thermal and mechanical loads even over a long time period, such as 10 years.

Abstract: A control apparatus for an internal combustion engine is provided that is capable of calculating a high-accuracy turbine rotational speed. A turbo supercharger which includes, in an exhaust passage, a turbine that is operated by exhaust energy of the internal combustion engine. A turbine rotational speed model which calculates a turbine rotational speed. The turbine rotational speed is corrected by an exhaust energy correction part equipped with the turbine rotational speed model.

Abstract: An engine exhaust heat recovery system includes an engine exhaust heat conduit that interacts with a two-phase fluid that exists in liquid and gaseous states within a single closed loop. A first heat exchanger, which may be a boiler, interfaces with and receives heat from the engine exhaust conduit. Exhaust heat energy converts the fluid from the liquid state into the gaseous state for transfer into a heat expander situated downstream of the first heat exchanger. The heat expander utilizes the gaseous heat energy to rotate a flywheel, and a system of clutches is situated and adapted to permit the flywheel to transfer mechanical energy for subsequent, selective production of work upon demand. In one disclosed embodiment, the heat expander may be a high-speed turbine with a rotary power shaft coupled to a transmission and a plurality of clutches adapted to engage and actuate the flywheel.

Abstract: A system is disclosed for use with an engine. The system may have an intake manifold configured to direct air into combustion chambers of the engine. The system may also have an auxiliary device and an exhaust manifold configured to direct exhaust from the combustion chambers of the engine through the auxiliary device to the atmosphere. The system may additionally have a conduit associated with fewer than all of the combustion chambers of the engine and extending to the auxiliary device in parallel with the exhaust manifold, and an auxiliary valve disposed within the conduit and selectively movable between a flow-passing position and a flow-blocking position.

Abstract: An internal combustion engine cylinder head is based upon a one-piece structure including a number of exhaust runners, an exhaust collector, and a turbocharger exhaust turbine housing, all formed as one-piece.

Abstract: A variable geometry turbocharger is simplified yet able to maintain pulse energy. In a first embodiment, a turbine housing is provided with a pivoting flow control valve which pivots about a point near the entry to the turbine housing. By moving the valve about the pivot point, the effective volume of the turbine housing volute is varied, thus effectively reducing the volume of exhaust gas in the volute, allowing control of exhaust gas flowing to the turbine wheel. In the second embodiment of the invention, a rotating wedge segment within the volute is rotated from a first position to a second position, changing the effective volume of the volute and allowing control of exhaust gas flowing to the turbine wheel.

Abstract: In an exhaust gas recirculation arrangement in which condensate is discharged from an exhaust gas recirculation path of an internal combustion engine, in particular of a motor vehicle, wherein, due to a pressure difference between a condensate collection region arranged in the EGR path and a condensate discharge region, collected condensate is discharged at least partially from the condensate collection region into the condensate discharge region, when the pressure level prevalent in the condensate collection region is greater than in the condensate discharge region in a secure manner and with low environmental impact.

Abstract: A pretensioner for introducing a webbing wound in a spool by explosive power obtained by exploding gunpowder when an impact is applied from the outside, the pretensioner includes: a hollow cylinder having one side surface for inserting a portion of a pinion connected to the spool; a micro gas generator (MGG) mounted in an upper end portion of the cylinder and for transferring explosive power into the cylinder while gunpowder provided at the inside explodes when an impact is applied from the outside; a rack mounted in a length direction at the inside of the cylinder and having one end portion disposed toward the MGG and having the other end portion disposed opposite to the pinion and having gear teeth provided in one side surface separated not to engage with the pinion before receiving explosive power from the MGG; and a roller for receiving explosive power from the MGG and rotatably mounted at the other side surface opposite to one side surface of the cylinder in which a portion of the pinion is inserted so t

Abstract: A method of power generation, including: igniting a biomass boiler; starting a solar concentrating collector; measuring water temperature t3 at water outlet main of the solar concentrating collector; opening a second control valve arranged between the water outlet main and the boiler drum when t3 is greater or equal to 95° C.; closing the second control valve and the third control valve to prevent water in the solar collector tube from running and to maintain the water in a heat preserving and inactive state if the water temperature t3 decreases and t3 is less than 95° C.; turning the turbonator unit into a thermal power generation mode; opening a first control valve arranged between the water outlet main and a water supply tank if the water temperature t3 continues decreasing and when t3 is between 5 and 9° C.; and turning the turbonator unit into a biomass boiler power generation mode.

Abstract: A ground high-temperature high-efficiency solar steam electricity-generating device includes a light convergence assembly (1), a heat exchanger assembly(3), a heat storage chamber assembly(5), a base assembly(2), an oil pump(15), a temperature-controlling valve(16), a steam turbine(13), temperature-controlling valve (16), a steam turbine (13), an electricity-generator (12), a system control circuit, a water pump (9) and a water tank assembly (10). The light convergence assembly (1) includes a glass plate (1-1), Fresnel lenses, a U-shaped groove (1-3), a thermal insulating material, a heat collecting pipe (1-5), high temperature heat conducting oil(6-6), a frame (1-7), a rib-plate and a spindle sleeve.

Abstract: A thermal collector tube includes a main body portion that houses a heat medium, and a coating layer provided on an outside surface of the main body portion. The coating layer has a radiation rate of 0.70 to 0.98 at room temperature and at a wavelength of 1 ?m to 15 ?m. The thermal collector tube is used in concentrated solar power generation in which solar light is collected using reflecting mirrors, the collected solar light is converted into heat using a thermal collector having the thermal collector tube, and power is generated using the heat.

Abstract: A Steam power plant comprising a steam turbine (3) and a condenser (5), wherein the condenser (5) is disclosed, comprising a first heat sink being a ground heat exchanger (29) is connected to the condenser during times when ground temperature is lower than air temperature; and a second heat sink being an above-ground heat exchanger is connected to the condenser during times when ground temperature is not lower than air temperature.

Abstract: A compressed air energy storage module including an integrated thermal energy storage and recovery apparatus is provided. The compressed air energy storage module contains no moving parts and is constructed onsite, underground and out-of-sight. The compressed air energy storage module comprises a first regenerative heat exchanger including a first tank filled with a first particulate material that stores thermal energy and adsorbs air, and a second regenerative heat exchanger including a second tank filled with a second particulate material that stores thermal energy. A first end of the first tank is connected to a first end of the second tank via a first piping system. A second end of the first tank is connected to a second end of the second tank via a second piping system. The first piping system and the second piping system form a circular path for the air to circulate through the first and second regenerative heat exchangers.

Abstract: A centrifugal compressor comprising an impeller having an input drive, the impeller having an impulse turbine positioned around the periphery of the impeller to be driven by the gas exiting the impeller, the output of the turbine being coupled to the drive of the impeller.

Abstract: A boiler unit comprises an enclosure including: a first circuit of a first fluid heat exchange medium, the first circuit N having a heating device to heat the first medium, a boost heat exchanger, a valve and a first manifold; a second circuit of a second heating system fluid heat exchange medium, the second circuit having a flow and return port of the boiler unit, a second manifold and said boost heat exchanger for exchange of heat between said first and second heat exchanger media when said valve is open; a space in the enclosure receiving an auxiliary unit to be driven substantially exclusively by said first fluid heat exchange medium; and a boiler control unit to control operation of the heating device according to heat demand of the heating device and otherwise irrespective of the auxiliary unit when connected; and an organic rankine cycle (ORC) unit comprising: a third fluid heat exchange medium circuit, the circuit including a condenser adapted for connection to said second manifold to provide heat to

Abstract: A gas turbine engine has an engine core and an annular by-pass duct, within a surrounding nacelle. An exhaust nozzle of the nacelle includes a selectively deployable noise-reduction section on an inner surface thereof. The noise-reduction section includes an inflatable envelope comprising a fixed outer wall and a displaceable inner wall. At least projections on the inner wall are inwardly displaced when the envelope is pressurized and retracted radially outwardly when the envelope is de-pressurized. When the envelope is pressurized, the inner wall includes portions that project to form a rough surface on the inner surface of the nacelle exhaust nozzle. This thickens the boundary layer and reduces the speed of the gas flow at the outer radius of the nozzle, thus reducing the differential velocity with the ambient air, which reduces the gradient throughout the shear layer thus reducing the noise level of the engine.

Abstract: A power plant control system monitors a flame holding boundary indicator, such as Damköhler number, to determine a lowest amount of a quenching agent that can prevent flame holding in a predefined region of a gas turbine. In embodiments, the amount of quenching agent used may be minimized to reduce operating costs while ensuring safe operation of the gas turbine.

Abstract: The combustor of the present invention is provided with a combustor basket to which air A is supplied from outside, first nozzles which are installed in a plural number annularly along an inner circumference of the combustor basket to individually supply premixed gas M of the air (A) with a fuel (f) into the combustor basket, and a transition piece, a base end of which is connected to the combustor basket, and which burns the premixed gas (M) supplied from the first nozzles to form a flame front (F) which spreads to an outer circumference toward the leading end in an axial direction. Each of the first nozzles supplies the premixed gas (M) by changing the fuel concentration around the center axis of the first nozzle so that the flame front (F) is made uniform in temperature in the axial direction.

Abstract: A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.

Abstract: A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits.

Abstract: The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel.

Abstract: A combustion chamber including a diverging portion. The combustion chamber extends along a longitudinal axis and includes a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat. The chamber further includes a tubular element surrounding the wall at least in part and configured to take up most of forces generated during operation of the chamber on the downstream end of the wall to transfer the forces to a structure situated upstream from the chamber.

Abstract: A system for reducing moisture in a burner pressure sensing line in a gas turbine engine. A water trap is mounted on the burner pressure sensing line with an inlet for receiving burner pressure air and an outlet for transferring burner pressure air to the sensor. A heat sink is positioned inside the water trap for condensing moisture contained in the burner pressure air. Finned tubes are used to passively control the temperature of the burner pressure line. A deadheaded chamber provides an alternative location for the moist air to condense when the gas is compressed at higher pressure.

Abstract: Disclosed is a gas turbine combustor for stably burning low-BTU gases, such as blast furnace gases, that are heavily laden with CO2. The gas turbine combustor includes a double-swirling burner with an inner swirler and an outer swirler, the burner having a configuration with gas fuel injection holes and air injection holes arranged at alternate positions in the inner swirler and with gas injection holes arranged in the outer swirler. In addition, fuel injection holes for enhancing flame stability are provided at positions radially inward of the inner swirler. An inner flame by the inner swirler and an outer flame by the outer swirler interact with each other to stably burn the low-BTU gas. In the inner swirler, the gas injection holes and air injection holes arranged at alternate positions contributes to raising a temperature of the inner flame to a level required for flame stabilization.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

Abstract: A method and architecture to reduce specific fuel consumption of a twin-engine helicopter without compromising safety conditions regarding minimum amount of power to be supplied, to provide reliable in-flight restarts. The architecture includes two turbine engines each including a gas generator and with a free turbine. Each gas generator includes an active drive mechanism keeping the gas generator rotating with a combustion chamber inactive, and an emergency assistance device including a near-instantaneous firing mechanism and mechanical mechanism for accelerating the gas generator. A control system controls the drive mechanism and emergency assistance devices for the gas generators according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory of the system.

Abstract: A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter.

Abstract: A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

Abstract: A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

Abstract: A fuel purging system for a turbine assembly includes a fuel delivery system. The fuel delivery system includes a fuel source for providing a fuel to the turbine assembly, a control valve for regulating a fuel flow of the fuel, a flow divider for selectively distributing the fuel to at least one combustor, and a combustor valve located upstream of the at least one combustor. The fuel purging system also includes a steam source for distributing a steam to the fuel delivery system at a location upstream of the combustor valve.

Abstract: A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.

Abstract: Disclosed is a combustion system for a gas turbine engine, which includes a combustor and a plurality of fuel injector nozzles within the combustor. The plurality of fuel injector nozzles include at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle. The combustion system further includes a fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting.

Abstract: A combustor includes an end cap. The end cap includes a first surface and a second surface downstream from the first surface, a shroud that circumferentially surrounds at least a portion of the first and second surfaces, a plate that extends radially within the shroud, a plurality of tubes that extend through the plate and the first and second surfaces, and a first purge port that extends through one or more of the plurality of tubes, wherein the purge port is axially aligned with the plate.

Abstract: A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described.

Abstract: A fuel conditioning apparatus for de-oxygenating a liquid hydrocarbon fuel has a catalyst portion which, in turn, has an inlet portion and an outlet portion. A hydrocarbon fuel stream is fed through the inlet portion and into the catalyst portion where it passes over a catalytically active component. The catalytically active component promotes the reaction of the fuel with the dissolved oxygen in the fuel stream, converting it into less chemically reactive forms and thereby reducing the fuel's propensity to form carbonaceous deposits.

Abstract: A fuel air heat exchanger for a gas turbine engine having fuel and air conduits in heat exchange relationship with one another, and a distribution conduit in heat exchange relationship with a component to be cooled. The distribution conduit is in fluid communication with the outlet of each air conduit. The heat exchanger also includes a secondary air inlet in fluid communication with the distribution conduit and a flow selection member selectively movable between first and second configurations. In the first configuration, the flow selection member closes the fluid communication between the secondary inlet and the distribution conduit. In the second configuration, the flow selection member opens the fluid communication between the secondary air inlet and the distribution conduit.

Abstract: According to one aspect of the invention, a method for conditioning air received by a power generation system includes flowing ventilation air through a turbine system to control a temperature of the turbine system and receiving the ventilation air from the turbine system and mixing the ventilation with an ambient air to form an intake air to be directed to a compressor, wherein a temperature of the ventilation air is greater than the ambient air.

Abstract: A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.

Abstract: A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

Abstract: A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.

Abstract: A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.

Abstract: A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a region of the transition (420) to cool the transition region upon circulation of the air flow within the cowling (460). The cooling system further includes a manifold (121) to directly couple the air flow (111) from the compressor section outlet to an inlet (462) of the cowling (460). The cowling (460) is configured to circulate the air flow (111) within an interior space (426) of the cowling (460) that extends radially outward from an inner diameter (423) of the cowling to an outer diameter (424) of the cowling at an outer surface.

Abstract: A fan section for a gas turbine engine has a fan rotor with a plurality of fan blades. A plurality of exit guide vanes are positioned to be downstream of the fan rotor. The fan rotor is driven through a gear reduction relative to a turbine section. The exit guide vanes are desired to address resultant sound from interaction of wakes from the fan blades across exit guide vanes. A gas turbine engine incorporating a fan section is also disclosed.

Abstract: A cryogenic refrigerator includes a first cylinder and a second cylinder, a first displacer and a second displacer configured to reciprocate inside the first cylinder and the second cylinder, respectively, an intake and outlet system configured to alternately perform a first operation of supplying gas to the first cylinder and discharging the gas from the second cylinder and a second operation of discharging the gas from the first cylinder and supplying the gas to the second cylinder, a communication path configured to communicate the first cylinder with the second cylinder, and an opening and closing part configured to open and close the communication path.

Abstract: A cryopump includes: a first panel to be cooled by a first stage of a refrigerator; a second panel to be cooled by a second stage of the refrigerator; a panel temperature sensor provided with the first panel and/or the second panel; a stage temperature sensor provided with the first stage and/or the second stage; and a control unit that controls vacuum pumping based on the temperature measured by the stage temperature sensor. The control unit controls regeneration including a heating process of a cryopanel, and uses the temperature measured by the panel temperature sensor exclusively in the regeneration. The control unit completes the heating process based on the temperature measured by the panel temperature sensor.

Abstract: Blast chiller apparatus (1) comprising a chilling chamber (3) structured for housing food to be cooled/frozen, a chilling circuit (6) comprising at least a first heat exchanger (8) designed to rapidly cool/freeze the chilling chamber (3); a defrost system (12) designed to defrost said at least first heat exchanger (8); at least an UV source (14) designed to irradiate ultraviolet radiations the inner space of said chilling chamber (3); and a control system configured to control the defrost system (12) to heat the first heat exchanger (8) so as to have the temperature of the chilling chamber (3) within a prefixed optimum temperature range of operating of said UV source (14).

Abstract: The present invention relates to a centrifuge and a method for cooling a centrifuge. The centrifuge according to the invention includes a cooling device which is improved in that its required installation space is reduced such that the centrifuge can be of a more compact design with the centrifugation capacity remaining unchanged, or the centrifugation capacity can be increased with the installation space remaining unchanged. Further, the number of components can be reduced and thus cost and assembly time can be saved.

Abstract: Provided is an air conditioner. The air conditioner including a compressor, an outdoor heat exchanger, an indoor heat exchanger, and an expansion device includes a supercooling device for supercooling a refrigerant condensed in the outdoor heat exchanger or the indoor heat exchanger, an injection passage through which the refrigerant passing through the supercooling device is introduced into an injection inflow part of the compressor, a bypass passage extending from the injection passage to a suction part of the compressor to bypass the refrigerant, and a passage opening/closing part disposed in at least one of the injection passage and the bypass passage to selectively block a flow of the refrigerant.

Abstract: A refrigerant charging method includes installing, cooling, confirming, and moving steps. In the installing step, a refrigeration device is installed on site. In the cooling step, a container is cooled to 31° C. or below using a cooling medium. In the confirming step, it is confirmed that the container has reached 31° C. or below. In the moving step, the refrigerant is moved to the intended charging space from the container upon confirming that the container has reached 31° C. or below via the cooling step. When moving the refrigerant from the container to the intended charging space, first, refrigerant that is in a gas phase within the container is moved into the intended charging space, whereupon refrigerant that is in a liquid phase within the container is moved into the intended charging space.