Abstract: A Stirling engine includes a base member that connects a housing portion with a heater that heats a working fluid using exhaust heat of a main engine, and a support member that supports the Stirling engine at the base member is provided.

Abstract: Provided is a Stirling cycle engine capable of being downsized without decreasing an assembling efficiency. A flange section as a fitting section is formed on one end of an inner core. A retainer plate as a retaining member for the flange section, holds and fixes the same with the aid of a second side surface of a mount integrally formed on a proximal end section of a cylinder, thus substantially coaxially arranging the cylinder and inner core. Accordingly, regardless of a thermal expansion difference between the cylinder and inner core, generation of impurity gas can be prevented; deformations of the cylinder and the inner core; and tremble of the inner core. Further, a conventional proximal end portion of the cylinder is not needed for fixing the inner core, thus reducing an outer diameter of a driving mechanism, eventually, an outer diameter of a casing.

Abstract: A sub master cylinder includes a body formed with a chamber in which oil is stored; a first sub piston having one end which is secured to one end of the body and the other end which extends toward the other end of the body and is disposed to cross the chamber; and a second sub piston disposed between an inner surface of the body and an outer surface of the first sub piston to be moved in the chamber.

Abstract: A system is provided for controlling an air handling system for an internal combustion engine. A dual-stage turbocharger includes a high-pressure compressor and variable geometry turbine combination fluidly coupled to a low-pressure compressor and variable geometry turbine combination. A control circuit includes a memory having instructions stored therein that are executable by the control circuit to determine a target low-pressure compressor ratio, a target high-pressure compressor ratio, a target high-pressure compressor inlet temperature and a target high-pressure compressor inlet pressure as a function of a target outlet pressure of the high-pressure compressor and a temperature, a pressure and a target flow rate of air entering the air inlet of the low-pressure compressor, and to control the geometries of the low-pressure and high-pressure turbines as a function of the target low-pressure compressor ratio the target high-pressure compressor ratio respectively.

Abstract: PCV systems are well known in the art and commonly used in turbocharged engines. The ejector creates a pressure drop for additional pull of PCV gas under boosted conditions of the turbocharger engine. The ejector typically includes a first inlet and a second inlet and a sole outlet. The first inlet pulls air from the compressor of the PCV system. The second inlet pulls air from the cyclone separator of the PCV system. Air exiting the ejector is exited to the intake manifold. However, when the turbocharger of the system is off, fresh air can leak in from the inlet from the oil separator thereby preventing the ventilation of blowby. The unwanted air reduces the efficiency of the turbocharger system. Accordingly, an ejector preventing unwanted fresh air flow is needed in the art.

Abstract: A system and method are provided for estimating an operating parameter of an exhaust manifold of an engine. In the system, a flow value is determined that corresponds to a flow rate of exhaust gas through an EGR conduit fluidly coupled between the exhaust manifold and the intake manifold. The EGR conduit includes an exhaust gas cooler disposed in-line with the EGR conduit and a property of the exhaust gas exiting an exhaust gas outlet of the cooler is measured. The operating parameter of the exhaust manifold is estimated as a function of at least the flow value and the property of the exhaust gas exiting the exhaust gas outlet of the cooler. Illustratively, the operating parameter of the exhaust manifold may be exhaust manifold pressure and/or temperature.

Abstract: A system and method are provided for controlling an air handling system for an internal combustion engine including a turbocharger having a variable geometry turbine fluidly coupled to an exhaust manifold of the engine and a compressor fluidly coupled to an intake manifold of the engine, and an electric motor coupled to a rotatable shaft connected between the compressor and the variable geometry turbine. A target torque required to drive the compressor to achieve target compressor operating parameters is determined, a maximum available torque that can be supplied by the variable geometry turbine in response to a target exhaust gas flow through the variable geometry turbine is determined, and the electric motor is enabled to supply supplemental torque to the rotatable shaft if the target torque is greater than the maximum available torque.

Abstract: A system and method are provided for controlling an air handling system for an internal combustion engine including a turbocharger having a variable geometry turbine and a compressor having a fresh air inlet fluidly coupled to ambient and to an air outlet of an electric air pump. An air pump enable value as determined a function of target engine speed and total fuel target values and an air flow target is determined as a function of a target fresh air flow value. Operation of the electric air pump is activated to supply supplemental air flow to the fresh air inlet of the compressor if the air pump enable value is greater than a threshold air pump enable value and the air flow target does not exceed a maximum flow value.

Abstract: A waste heat recovery system is for use with a power unit that includes an internal combustion engine. The waste heat recovery system includes a Rankine cycle device in which working fluid circulates through a pump, a boiler, an expander and then through a condenser, heat exchange occurs in the boiler between the working fluid and intake fluid that is introduced into the internal combustion engine while being cooled, a determination device for determining required cooling load for the intake fluid, a pressure reducing device for reducing evaporation pressure in the Rankine cycle device, and a controller for controlling the pressure reducing device so as to reduce the evaporation pressure below a predetermined evaporation pressure if the required cooling load determined by the determination device exceeds a threshold.

Abstract: This offshore installation for producing electrical energy from thermal energy of the oceans includes a floating platform supporting a generator for producing electrical energy from the temperature difference of the water at the surface and at a depth and associated with a pipe for drawing up water from a depth, is characterized in that the pipe for drawing up water from a depth include three portions, including a first formed with a rigid pipe, the lower end of which is immersed at a great depth and the upper end of which is immersed in midwater at a reduced depth, a second portion formed with flexible pipes for connecting the upper end of this rigid suction pipe to a third portion forming a suction pipe, formed with rigid pumping pipes structuring a lattice of pipes attached under the platform.

Abstract: A cycle (100) for producing work from heat involves pressurizing a first working fluid (F1), and heating the first working fluid under pressure (102) to obtain a first vapor. A second working fluid (F2) is compressed (106) in a compressor (204a, 204b). The first vapor and the second vapor are then mixed (108) to form a third vapor (F3). Heat is thereby transferred directly between the vapors at a common pressure. The third vapor is expanded (112) to perform work. All or a portion of the third vapor is communicated (121) to a low pressure expansion zone (214, 215) where it functions as a refrigerant used to provide cooling for the third vapor, thereby facilitating the condensate of the first fluid to liquid extracted from the third vapor. Heat extracted during the condensate process is used for later performing work. The first fluid condensate is returned to the initial pressurizing step with capacity to again acquire heat that is useful for performing work.

Abstract: The present invention relates to a method of converting thermal energy into mechanical energy using a non-gaseous working medium present in an apparatus comprising a plurality of heat exchangers and an outgoing shaft. In accordance with the invention, the apparatus used comprises a multitude of chamber units, a chamber unit comprising an inlet for introducing heat exchange medium and an outlet for discharging heat exchange medium as well as a closed chamber having a heat exchanger wall for exchanging heat between working medium inside the closed chamber and the heat exchange medium introduced into the chamber unit via said inlet for introducing heat exchange medium and heat exchange medium is passed around so as to do work when it is giving off heat to a chamber unit containing relatively cool working medium and recuperate heat when it is passed through a chamber unit containing relatively warm working medium. The invention also relates to an apparatus for performing the method.

Abstract: A combustor (100) for a gas turbine engine (30) has a circumferentially extending liner (109) defining at least a portion of an interior combustion chamber (107) and a hot gas path (115). The liner includes a resonator section (112) including at least one resonator (116A, 116B) having a resonator chamber (125A, 125B) formed on an exterior of the liner. A thermal barrier coating (118) is disposed along an inner surface of the liner including an inner surface (130) of the resonator section. The resonator further includes a plurality of apertures (117) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber.

Abstract: A system including a controller. The controller may receive a signal indicative of an emissions level of a turbine. The controller may also generate at least one control signal. This control signal may control a split of diluent between a first and a second mixing chamber, whereby the first and the second mixing chambers are located in a fuel nozzle in the turbine.

Abstract: A system includes a gas turbine combustor. The gas turbine combustor includes a combustion liner disposed about a combustion region and a sleeve disposed about the combustion liner. The combustion liner and the sleeve define an airflow passage circumferentially about the liner. The gas turbine combustor also includes multiple axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor. The multiple axial injectors are asymmetrically configured to provide an uniform injection of the airflow circumferentially about an axis of the gas turbine combustor.

Abstract: A turbine burner is provided. The turbine burner has a secondary feed unit and a primary feed unit. The primary feed unit has a primary mixing tube and a fuel nozzle that are arranged concentrically around the secondary feed unit. The primary mixing tube and the fuel nozzle have a fluid flow connection. The fuel nozzle has an annular wall that is radially spaced in the axial direction from the secondary feed unit such that a gap height is fainted by the annular wall and the secondary feed unit. The annular wall has an inside wall directed toward the secondary feed unit and having blades with a leading edge on the upstream side. The fuel nozzle has an inlet and the blades have an axial distance from the inlet. The ratio of the distance to the gap height is greater than 1 and less than the gap height.

Abstract: A combustion liner for a combustor of a turbine engine includes a plurality of undulations which extend around the exterior circumference of the combustion liner. A plurality of rows of cooling holes are formed through the combustion liner. Each row of cooling holes is located in one of the undulations which extends around the exterior circumference of the combustion liner. The cooling holes admit a flow of cooling air into the interior of the combustion liner. The cooling holes are located and oriented to help the flow of cooling air form a film along the inner surface of the combustion liner.

Abstract: Combined cycle efficiency can be improved by heating fuel in a gas turbine fuel line in two stages using (i) hot water from an HP economizer of a heat recovery steam generator (HRSG) in a second stage and (ii) hot water from an IP economizer of the HRSG and water output flow from the second stage in a first stage. Efficiency may be further improved by adding one or more fuel preheaters using hot water from the IP feedpump and sequential injections of hot water into the fuel.

Abstract: According to one aspect of the exemplary embodiment, a turbomachine includes a compressor portion, a combustor fluidly connected to the compressor portion, and a turbine portion fluidly connected to the combustor portion and mechanically coupled to the compressor portion. The combustor portion is configured and disposed to burn ash-bearing fuel oils. The turbine portion includes a first stage having a first plurality of airfoils, and a second stage having a second plurality of airfoils. The first plurality of airfoils have a trailing edge discharge member. The second plurality of airfoils is clocked circumferentially relative to the first plurality of airfoils. The first plurality of airfoils are configured and disposed to direct an ash depleted flow upon corresponding adjacent ones of the second plurality of airfoils.

Abstract: A combustor includes an end cap having an upstream surface axially separated from a downstream surface and a cap shield circumferentially surrounding the upstream and downstream surfaces. A first circuit of tubes extends from the upstream surface through the downstream surface. A first fuel plenum is in fluid communication with the first circuit of tubes. A second circuit of tubes extends from the upstream surface through the downstream surface. A second fuel plenum downstream from the first fuel plenum is in fluid communication with the second circuit of tubes. A method for supplying fuel to a combustor includes flowing a working fluid through tubes, flowing fuel or diluent from a first fuel plenum through a first circuit of tubes, and flowing fuel or diluent from a second fuel plenum through a second circuit of tubes, wherein the second fuel plenum is downstream from the first fuel plenum.

Abstract: A gas turbine system comprises a gas turbine having a low pressure compression stage and a high pressure compression stage, a combustion chamber, and an expansion stage connected to the combustion chamber. The low pressure compression stage and the high pressure compression stage are connected with each other via an intercooling stage, wherein the low pressure compressed air stream from the low pressure compression stage is chilled to an intercooling temperature that is lower than the ambient temperature of the air source from which the air stream was supplied to the low pressure compression stage of the gas turbine.

Abstract: A compressor of a gas turbine system comprises a fluid flow control device and an impingement angle control device downstream of the fluid flow control device. The fluid flow control device controls a fluid flow rate of fluid entering an inlet of the compressor, and the impingement angle control device controls an impingement angle of the fluid flowing to rotor blades in the compressor. The fluid flow control device and the impingement angle control device are independently operable.

Abstract: An estimation unit can estimate, on a real-time basis, a maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. For example, the actual power output and the maximum power generation capacity can be calculated relying on a mathematical process model. Subsequently, the calculated actual power output can be compared with the measured power output yielding a model-estimation error. Based on the model-estimation error, a correction signal can be deduced, to correct the calculated maximum power generation capacity. A controller can maintain a specified power reserve. The controller can use an estimate of the maximum power generation capacity as a reference, subtract a load offset, and apply the resulting signal as upper limit of the load set-point.

Abstract: Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface.

Abstract: According to one aspect of the invention, a method for providing a fuel supplied to a combustor in a gas turbine engine system includes partially oxidizing a fraction of primary fuel in a fuel circuit of the gas turbine engine system, in the absence of a catalyst, with a non-catalytic fuel reformer to form a reformate, wherein the fraction of primary fuel and an oxidant are mixed and burned in a predetermined ratio in the non-catalytic fuel reformer. The method also includes causing a water-gas shift reaction in a non-catalytic reaction passage in the non-catalytic fuel reformer by directing a selected amount of secondary fuel and a selected amount of steam into the partially oxidized fraction of fuel, thereby producing a reformate and mixing the reformate with a remaining fraction of fuel to produce a mixed fuel stream and supplying the mixed fuel stream to the combustor.

Abstract: A gas turbine engine arrangement comprising a first engine section (2), the first engine section (2) comprising a first compressor (4) and a first turbine (6) mounted on a first shaft (8), the gas turbine engine arrangement further comprising at least one further turbine (20) mounted on a second shaft (22) and arranged such that gases exiting the first engine section (2) are ducted to the further turbine (20), wherein said first and second shafts (8, 22) are not mechanically coupled to one another and have respective axes which are offset from each other.

Abstract: A forward mount assembly for connecting a pylon to an intermediate case of a gas turbine engine, the forward mount assembly includes a forward mount platform, a wiffle tree assembly, and first and second A-arms. The platform is connected to the pylon and is disposed adjacent the intermediate case. The wiffle tree assembly is connected to the forward mount platform through a first ball joint. The first A-arm is connected to a first side of the intermediate case and the second A-arm is connected to a second opposing side of the intermediate case. The first and second A-arms are mounted to the forward mount platform and are mounted to opposing ends of the wiffle tree. The aforementioned arrangement allows the first and second A-arms to react a thrust load at the intermediate case substantially parallel to a centerline axis of the gas turbine engine.

Abstract: An assembly for use with a gas turbine engine includes a tie rod and a connector. The tie rod, which is for extending radially outwardly from a latitudinal axis of the gas turbine engine, has a hollow length having a longitudinal axis and a base having a width in parallel to the latitudinal axis. The base has a counterbore disposed therein and is wider than a width of the length. The connector, for attaching the base of the tie rod to a bearing assembly of the gas turbine engine, has a hollow body having a shaft removably attaching, at a first end portion thereof, to the counterbore. The shaft and the counterbore are disposed in parallel with the longitudinal axis.

Abstract: Methods and apparatus are provided for controlling an auxiliary power unit (APU) inlet door. A plurality of APU operational parameters and a plurality of aircraft operational parameters are sensed. The APU operational parameters and the aircraft operational parameters are processed to determine a minimum APU inlet door position that will maintain APU turbine inlet temperature at a predetermined value. The APU inlet door is then moved to the determined minimum APU inlet door position.

Abstract: An apparatus comprises a cooling structure that includes a first plate, a second plate separated from the first plate, and an inlet adapted to receive a cooling fluid. The apparatus also comprises a first cooling portion coupled to the first plate and adapted to maintain a first temperature. The apparatus also includes a second cooling portion coupled to the second plate and adapted to maintain a second temperature, different from the first temperature.

Abstract: There is provided an ice making method capable of forming ice to an intended level although a sensing unit configured to sense whether or not a formation of ice has reached the intended level malfunctions. The ice making method includes: an ice making initiation step S100 of forming ice by an ice formation unit; an ice release time determining step S200 of determining a point in time at which ice is to be released in consideration of a signal from a detection unit for detecting whether the formation of ice has reached an intended level and an ice making lapse time which has lapsed after the formation of ice was initiated by the ice formation unit; and an ice releasing step S300 of releasing the formed ice when a point in time at which ice is to be released is determined in the ice releasing time determining step.

Abstract: A cryogenic refrigerator includes a Scotch yoke mechanism including a Scotch yoke and a bearing movably engaged with the Scotch yoke, and a displacer caused to reciprocate in a cylinder by the Scotch yoke mechanism, so that a refrigerant gas inside an expansion space formed in the cylinder is expanded by the reciprocation of the displacer to generate cold temperatures. The Scotch yoke includes a concave part at a position corresponding to a top dead center of the displacer.

Abstract: A cryogenic refrigerator includes a cylinder, a displacer configured to be moved back and forth in the cylinder by a drive unit, an inlet valve configured to be opened in supplying a refrigerant gas into the cylinder, an exhaust valve configured to be opened in exhausting the refrigerant gas from the cylinder, and an expansion space formed in the cylinder and configured to generate a cooling by expanding the refrigerant gas caused by back and forth movement of the displacer. A moving speed of the displacer in the vicinity of a bottom dead center is set to be faster than the moving speed of the displacer in the vicinity of a top dead center.

Abstract: A disclosed device cryogenic refrigerator includes a first stage displacer; a first stage cylinder configured to form a first expansion space between the first stage cylinder and the first stage displacer; a second stage displacer connected to the first stage displacer; and a second stage cylinder configured to form a second expansion space between the second stage cylinder and the second stage displacer, wherein a helical groove is formed on an outer peripheral surface of the second stage displacer so as to helically extend from a side of the second expansion space toward the first stage displacer, wherein the second stage cylinder includes a first flow resistor communicating with a side of the first stage displacer in the helical groove, and a buffer portion communicating with a side of the first stage displacer in the first flow resistor.

Abstract: A thermal management system and method of use are provided, the system including a heat exchanger, a refrigeration system, a coolant loop thermally coupled to the heat exchanger, and a by-pass valve that regulates the amount of coolant within the coolant loop that either passes through the heat exchanger or is diverted away from the heat exchanger. The coolant loop is thermally coupled to the battery pack of an electric vehicle.

Abstract: A method for controlling transitions between activating and deactivating a vehicle air conditioner compressor is disclosed. In one example, displacement of the air conditioner compressor is adjusted before the air conditioner is coupled to an energy conversion device. The method may provide smooth transitions between different air conditioner compressor control modes.

Abstract: There is provided an ice making method capable of reducing the required number of gyrations of a gyration member used for making ice to have a high level of transparency and determining a point in time at which ice is to be released. The ice making method for making highly transparent ice by revolving a gyration member provided in a tray member in which water is put such that a plurality of dipping members, on which ice is generated or from which generated ice is released, are immersed, wherein a method for driving the gyration member in making ice to be supplied to a user and a method for driving the gyration member in making ice to be used for generating cold water are different in order to reduce the number of gyrations of the gyration member.

Abstract: An air dehumidification unit of a heating, ventilating, and air conditioning system includes an air flow channel configured to guide a flow of air through an evaporator disposed therein, and a drainage channel coupled to the air flow channel. The drainage channel has an internal volume configured to receive a fluid condensed at the evaporator from the flow of air. The air dehumidification unit further includes a heating device configured to heat the internal volume of the drainage channel from outside of the internal volume of the drainage channel to militate against a formation of ice therein. The invention also relates to a method for dehumidifying the air in the heating, ventilating, and air conditioning system of a motor vehicle using the air dehumidification unit.

Abstract: A method for controlling torque of an air conditioner compressor is disclosed. In one example, the air conditioner compressor is a variable displacement compressor. The method may provide may improve vehicle acceleration response while at the same time providing cooling capacity to a vehicle cabin.

Abstract: A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Abstract: Disclosed is a method and device for a refrigerant-based thermal energy storage and cooling system with integrated multi-mode refrigerant loops. The disclosed embodiments provide a refrigerant-based thermal storage system with increased versatility, reliability, lower cost components, reduced power consumption and ease of installation.

Abstract: In a method for operating a cooling system for cooling food on board an aircraft, a partial amount of refrigerant, which, in the rest state, is stored in a receiving space of a refrigerant container in the gaseous state of aggregation, is discharged from the receiving space of the refrigerant container into a cooling circuit of the cooling system. The partial amount of the refrigerant is directed into a liquefier arranged in the cooling circuit and converted to the liquid state of aggregation. The partial amount of the refrigerant liquefied by the liquefier is directed through a heat exchanger arranged in the receiving space of the refrigerant container. The remaining refrigerant, stored in the receiving space of the refrigerant container in the gaseous state of aggregation, is converted to the liquid state of aggregation by heat energy transfer to the partial amount of the refrigerant flowing through the heat exchanger.

Abstract: According to one embodiment, an air conditioning system includes a compressor, a condenser, an expansion valve, a switching valve, an evaporator, a pump, a radiator, and a heat storage unit. The switching valve performs switching so that a first heat medium flows through either a first flow path or a second flow path. The pump supplies a second heat medium to the heat source. The heat storage unit has a heat storage material. The heat storage unit has a first heat exchange region in which heat is exchanged between the first heat medium flowing through the first flow path and the heat storage material. The heat storage unit has a second heat exchange region which is provided upstream of the radiator and in which heat is exchanged between the second heat medium supplied to the heat source and the heat storage material.

Abstract: One aspect, as provided herein, is directed to a multi-stage fluid control system for a fluid source heat pump system. This embodiment comprises compressors configured to operate as separate, heat exchange stages, condensers each being fluidly coupled to at least one of the compressors by refrigerant tubing and having intake ends coupled together by a fluid intake manifold. This embodiment further includes output conduits coupled to each of the condensers and that are couplable to a distal location. Further included is a modulating valve control system interposed the output conduits. The modulating valve control system is configured to stage a flow of fluid through the condensers based on a number of operating compressors.

Abstract: A vapour compression system comprises a compressor, a condenser, an expansion device, e.g. in the form of an expansions valve, and an evaporator arranged along a refrigerant path. A method for operating the vapour compression system comprises the steps of: obtaining a superheat value being representative for the superheat of refrigerant entering the compressor; obtaining a subcooling value being representative for the subcooling of refrigerant entering the expansion device; and operating the expansion device on the basis of the obtained superheat value and on the basis of the obtained subcooling value. The subcooling value is taken into account when operating the expansion device, because variations in the subcooling value have significant influence on the refrigerating capacity of the evaporator at a given opening degree of the expansion device, thereby resulting in a more stable operation of the system. The system may further comprise an internal heat exchanger.

Abstract: The subject of the invention is a device (5) for expanding a refrigerant fluid comprising, on the one hand, a first inlet (8) of the expansion device and a first outlet (9) of the expansion device which are connected by a first refrigerant circulation duct (11), the first refrigerant circulation duct (11) comprising an upstream part (22) and a downstream part (25) which parts are placed in communication by a first communication passage (18) and, on the other hand, a second inlet (12) of the expansion device and a second outlet (13) of the expansion device which are connected by a second refrigerant circulation duct (14).

Abstract: A method for controlling torque of an air conditioner compressor is disclosed. In one example, the air conditioner compressor is a variable displacement compressor. The method may provide smooth transitions between different air conditioner compressor torques.

Abstract: A display system for ice rinks comprises a panel having at least one enclosure containing a plurality of LEDs for displaying any indicia or images etc. The panel is adapted to be placed under the ice when in use. The panel is provided with a cooling apparatus for circulating a coolant through the at least one enclosure to remove heat generated by the LEDs. In one aspect, the panel includes at least one channel, within which a plurality of light emitting diodes, LEDs, are provided. The LEDs are controlled to display any indicia or images from under the ice when the panel is in use. The panel includes a manifold system for distributing a coolant through the channels so as to dissipate any heat generated by the LED, thereby, avoiding affecting the temperature of the ice.