Abstract: A nucleic acid loading device, including a housing, a carrying module, a motion module, a liquid circuit module and a control module. The motion module includes a support platform, first and second driving mechanisms, and a carrying member. The liquid circuit module is configured to control a reagent to flow into and out of a reactor. The control module is connected with the motion module and the liquid circuit module, and the control module is configured to control the first and second driving mechanisms, the liquid circuit module and the temperature control unit. A first face of a semiconductor cooler heats or refrigerates during operation, providing heat for an accommodating seat through a heat conducting body such that the reactor can be at different ambient temperatures. The cooperation between the motion and liquid circuit modules may achieve automation and industrialization of loading a sample into the reactor.

Abstract: An aircraft environmental control system includes means for mixing and conditioning bleed air from a bleed air input and recirculation air from an aircraft interior to provide mixed, conditioned air to the aircraft interior. The system also includes a first contaminant removal device and a second contaminant removal device arranged in a path of at least part of the recirculation air, prior to the means for mixing and conditioning, and a valve (SV1) arranged to alternate flow of recirculation air through the first and second contaminant removal devices.

Abstract: A ventilation fan includes a shaft, a rotor, a motor housing, a bearing housing, and an air bearing. The shaft has a shaft body that extends between a first shaft end and a second shaft end. The shaft body defines a first port and a bore. The rotor is disposed about the shaft. The motor housing is disposed about the shaft and is axially spaced apart from the rotor. The bearing housing is disposed about the shaft. The air bearing is disposed proximate the second shaft end and is disposed between the bearing arm and the second shaft end.

Abstract: A system includes a first fluid flow path configured to condition a pressurized medium and deliver the pressurized medium to one or more loads. The first fluid flow path including an air cycle machine. A second fluid flow path is configured to circulate a working fluid. The second fluid flow path includes a heat exchanger thermally coupled to the first fluid flow path. Within the heat exchanger, heat extracted from the pressurized medium is transferred to the working fluid. The second fluid flow path additionally includes a turbine operably coupled to the air cycle machine, a condenser, and a pump operable to circulate the working fluid through at least a portion of the second fluid flow path. The turbine is rotationally driven by expanding the working fluid across the turbine.

Abstract: This disclosure describes novel hybrid energy storage systems for providing short-term and long-term storage and delivery of electricity generated by any energy source including renewable energy sources such as solar energy and wind energy. The hybrid energy storage systems described herein have a higher overall real-world efficiency than energy storage systems currently available.

Abstract: A vehicle comprising a compressor and a manifold physically and fluidly coupled to the compressor.

Abstract: A compressor includes three suction pipes. A first center of a first suction pipe, a second center of a second suction pipe, and a third center of a third suction pipe are positioned at vertices of a triangle. A first distance between the first center and a center of a compressor main body is smaller than a second distance between the second center and the center of the compressor main body and a third distance between the third center and the center of the compressor main body. A second flow path cross section and a third flow path cross section are positioned on opposite sides of a center connection line sandwiched therebetween. The first suction pipe is connected to a suction port which is at an uppermost position among three suction ports provided in a case.

Abstract: A waste-heat recovery system includes a compressor main body; a gas piping, a waste-heat-recovery heat exchanger, a circulation circuit, and a tank with a water inlet piping and a water outlet piping that stores water that exchanges heat with the heat medium by connecting to the circulation circuit. The waste-heat recovery system also includes an inlet valve, a circulation pump, and a gas temperature sensor that detects the temperature of the compressed gas by arranging in the gas piping. The waste-heat recovery system also includes a water temperature sensor that detects the temperature of the water in the tank, and a control device that controls the inlet valve and the outlet valve according to detection temperature of the gas temperature sensor and the water temperature sensor.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system.

Abstract: In the two-cylinder hermetic compressor, a first compression mechanism unit includes a first cylinder and a first piston, and a second compression mechanism unit includes a second cylinder and a second piston. A main bearing is disposed on one surface of the first cylinder, and an intermediate plate is disposed on another surface of the first cylinder. The intermediate plate is disposed on one surface of the second cylinder, and an auxiliary bearing is disposed on another surface of the second cylinder. A shaft is constituted by a main shaft portion which has a rotor attached thereto and is supported by the main bearing, a first eccentric portion having a first piston attached thereto, a second eccentric portion having a second piston attached thereto, and an auxiliary shaft portion supported by the auxiliary bearing. The diameter of the auxiliary shaft portion is set larger than the diameter of the main shaft portion.

Abstract: A method of operating a RAM inlet header (RIH) is provided. The method includes determining a temperature of RAM air flows in a body through which RAM air flows from an inlet toward a heat exchanger, determining a temperature of excess air for use in an environmental control system (ECS) and, in an event the temperature of the excess air is less than the temperature of the RAM air flows, directing a curtain of the excess air from a nozzle body and along a wall of the body into flows of the RAM air and toward the heat exchanger.

Abstract: A cryogenic refrigerator system with heaters is constructed in modular form to serve as a portable servicing system to warm up and then cool down a target object by circulating a gaseous cryogen through a target object cryostat without moving the target object or breaking its vacuum. The main module is a refrigerator cryostat containing a fan that circulates gas through one or more heat exchangers which can warm or cool the gas by heaters and by one or more GM or Brayton cycle expanders. Additional components including one or more compressors, a gas charge and vent assembly, a control system, gas lines, power lines, and vacuum jacketed transfer lines can be assembled in the main module or additional modules. An example is a system that can be wheeled through a hospital to service a MRI cryostat.

Abstract: An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.

Abstract: Disclosed is a method for ventilating a ram air channel for a vehicle—in particular an aircraft—including at least one heat exchanger. The ram air channel is provided with a jet pump including a plurality of compressed air inlets connected to a plurality of separate compressed air sources of the vehicle, and a plurality of compressed air outlet nozzles. At least two nozzles are independently connected to at least two separate compressed air sources of the vehicle.

Abstract: An integrated fuel and environmental control system is provided and includes a first heat exchanger in which fuel and oil thermally communicate and a second heat exchanger disposable in a super-cooled fluid flow. The second heat exchanger is receptive of at least one of the fuel and oil from the first heat exchanger whereby the at least one of the fuel and oil thermally communicate with the super-cooled fluid flow. The second heat exchanger is also receptive of a second fluid whereby the second fluid thermally communicates with the super-cooled fluid flow downstream from the thermal communication of the super-cooled fluid flow with the at least one of the fuel and oil.

Abstract: An exhaust system for an aircraft galley chiller is provided. The exhaust system includes a galley having a chiller that includes an inlet, a condenser fan inlet, a condenser fan outlet proximate to chiller inlet, and a first flow of air through the condenser, an air ventilation outlet conduit that includes a second flow of air therethrough, and an ejector pump. The ejector pump includes a first airflow inlet, a second airflow inlet and an airflow outlet, wherein the first airflow inlet is coupled in flow communication with the condenser fan outlet, the second inlet is coupled in flow communication with the air ventilation outlet conduit. As the second airflow increases, the first velocity increases in a direction away from the galley chiller facilitating a decrease in temperature at the condenser fan inlet.

Abstract: A system comprising a cryogenic engine system and a refrigeration system, wherein the cryogenic engine system and the refrigeration system are mechanically and/or thermally coupled with each other. The refrigeration system is driven by the cryogenic engine system and the cryogenic engine system enhances cooling of the refrigeration system.

Abstract: A method and apparatus for cooling compressed air include the following. Compressed air is introduced into a vortex tube where cold air and warm air are generated. The cold air and warm air are introduced into a pressure vessel where the temperature and moisture of the compressed air are adjusted. The adjusted compressed air is fed to a downstream side of the pressure vessel. Before the generated cold air and warm air are introduced into the pressure vessel, the warm air is introduced into a pre-pressure vessel disposed at an upstream side of the pressure vessel. The cold air is introduced into a cooling tube or cooling chamber which is disposed inside the pre-pressure vessel which is disposed at the upstream side of the pressure vessel. The warm air is adjusted by cooling. The adjusted warm air is introduced into the pressure vessel from the pre-pressure vessel together with the cold air.

Abstract: A pressure regulating system that is suited to regulate the pressure of a gas includes a regulating device suited to regulate the pressure of a first gas stream, provided with an inlet for the gas at a supply pressure and with an outlet for the gas at a regulated pressure that is lower than the supply pressure; a vortex tube suited to receive a gas stream through an inlet, separate it into a hot portion and a cold portion and deliver the hot and cold portions through corresponding outlets; a heat exchanger coupled with the vortex tube in order to heat the first gas stream before it flows into the regulating device; a recovery duct suited to collect a first portion of the first gas stream at a collection point located downstream of the heat exchanger and to convey it to the inlet of the vortex tube.

Abstract: An aircraft air conditioning system comprising an ambient air supply line with a first end connected to an ambient air inlet and a second end connected to a mixing chamber. A first electrically driven ambient air compressor in the ambient air supply line compresses the ambient air flowing therethrough. A first ambient air branch line branches off from the ambient air supply line upstream of the first ambient air compressor and rejoins the supply line downstream of the air compressor. A second ambient air compressor in the first ambient air branch line compresses the ambient air flowing therethrough. A cabin exhaust air line has a first end connected to an air conditioned aircraft area. A cabin exhaust air turbine in the exhaust air line is driven by the exhaust air flowing through the cabin exhaust air line and is coupled to drive the second ambient air compressor.

Abstract: An on-board aircraft inert gas system includes a source of hydrocarbon, a source of gas comprising oxygen, and a first fluid flow path between the source of gas comprising oxygen and an inert gas output. A reactor is disposed along the first fluid flow path that reacts oxygen and hydrocarbon from the fuel tank gas space to produce an oxygen-depleted gas. A heat exchanger condenser removes some water from the oxygen-depleted gas. A water-permeable gas membrane separator receives the oxygen-depleted gas from the heat exchanger and outputs dried oxygen-depleted gas.

Abstract: A combination includes a selectively driven fan and a bypass flow passage for bypassing the fan. The bypass flow passage communicates with a first check valve to allow air to flow from the bypass passage to a downstream location. A second check valve allows air driven by the fan to pass into a return passage and return to an inlet of the fan in the event that the discharge pressure from the fan overcomes a spring force associated with the second check valve. A heat exchanger pack and an environmental control system for use on an aircraft, and a method are all also disclosed.

Abstract: An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

Abstract: Closed thermodynamic cycle systems, such as closed Brayton cycle systems, with regenerative heat exchangers are disclosed. Embodiments include dual regenerators and regenerators with buffer tank systems. Regenerators may be used instead of or in addition to one or more recuperators within the systems, and may be used as a means of gas-gas heat exchange for different streams of a working fluid.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: An environmental control system (ECS) pack is provided including a primary heat exchanger, a secondary heat exchanger, and an air cycle machine. The air cycle machine includes a compressor and a turbine. The compressor is fluidly coupled to an outlet of the primary heat exchanger and to an inlet of the secondary heat exchanger. The outlet of the secondary heat exchanger is fluidly coupled to the turbine. A first conduit connects the outlet of the primary heat exchanger and the inlet of the secondary heat exchanger. The first conduit includes a first valve. A second conduit connects the outlet of the secondary heat exchanger to an air load. The second conduit includes a second valve.

Abstract: A mist cooling system that includes a casing and a liquid inlet. The casing is configured to receive a liquid flow from a source through the liquid inlet and then provide the liquid flow as a mist to a housing of a motor so as to increase a cooling of the motor and prevent any failure of the motor due to overheating.

Abstract: A Brayton cycle type refrigerating apparatus using multiple stages of compressors and having a good response without reduction in efficiency due to change in heat load of the object to be cooled is provided. The Brayton cycle type refrigerating apparatus includes on a refrigerant line on which multiple stages of compressors are arranged in series. The apparatus also includes a temperature sensor for detecting heat load of an object to be cooled and a buffer tank provided between a low pressure line and a high pressure line. A flow rate of the refrigerant in the refrigerant line is controlled by controlling opening degrees of valves to adjust the cooling capacity.

Abstract: A method of controlling an outlet temperature of a heat exchanger of an aircraft includes operating an air cycle machine at a first operating speed. The air cycle machine is operatively coupled to an air cycle machine bypass valve at a first position. The air cycle machine is fluidly connected to a first heat exchanger disposed adjacent to a second heat exchanger. In response to a second heat exchanger outlet temperature less than a second heat exchanger outlet temperature threshold while the aircraft is operating at an altitude less than an altitude threshold, the method moves the air cycle bypass valve from the first position toward a second position.

Abstract: It is a purpose for the invention to provide a rotating device (107) to generate heat, cold and pressure from the outlet at the rotation axis, by centrifugation pressurized fluid in that it include at least two under-supported U-channel structures (107) where one of the channels (104, 105) from each U-channel structure (107) toward the periphery (107) is in thermal contact, forming a heat exchanger (106) where one of the channels (105) contains a compressible cooling fluid which develops heat from the centrifugal compression in the channel (105), and the heat is transferred to a heating fluid with a lower temperature in the second channel (104) in heat exchanger (106) toward the periphery (107) where heat exchanging ceases, and the U-channels (107) is connected to its inlet—(101, 102) and outlet channels (111, 112) at the rotation axis for the transport of said fluid through the U-channels (104, 105, 108, 109) via the periphery (107), which after the outlet (111) for heating fluid is heat-exploited, and cooli

Abstract: The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Abstract: An environmental control system, includes an air cycle machine for conditioning an interior space with cooling air, the air cycle machine including a fan coupled to a shaft that rotates about a shaft axis, the fan being located at a distal end of the air cycle machine; a speed sensor module having a speed sensor for sensing a rotational speed of the shaft; wherein the speed sensor module includes an outer portion having a first bore aligned on the shaft axis, an intermediate portion having a second bore aligned on the shaft axis, and an inner portion aligned on the shaft axis; and a diffuser assembly including a cylindrical assembly for ducting a first portion of the cooling air to an inlet side of the fan and for communicating a second portion of the cooling air directly to a discharge side of the fan without passing the inlet side.

Abstract: A method for operating an air-conditioning system for an aircraft includes compressing ambient air with a compressor driven by a shaft in communication with a motor and a turbine. The method includes forwarding the compressed air to an aircraft cabin for circulation and removing circulated compressed air from the aircraft cabin. The method also includes forwarding the circulated compressed air to the turbine, depressurizing the circulated compressed air in the turbine and capturing energy created by depressurizing the circulated compressed air.

Abstract: The apparatus has a cooling arrangement with an expander/compressor system, condenser and evaporator primarily for air conditioning. An external heat source is provided for transfer of heat to the expander housing. For example, this heating medium is an electrical heat source in thermal contact with the outer side of the expander housing. Alternatively, the expander is provided inside an externally heated liquid buffer tank.

Abstract: An aircraft system for improved cooling efficiency comprises at least one air conditioning pack, coupled to an aircraft, having at least one air compression device powered by at least one power source and having an air compression device inlet. The system further comprises at least one air flow path for redirecting a first portion of a first volume of aircraft interior outflow air from an aircraft interior to the air compression device inlet. The air flow path includes a shutoff valve to enable the air flow path during ground operation of the aircraft and to disable the air flow path for flight operation of the aircraft. The air compression inlet mixes the first volume of aircraft interior outflow air with a second volume of aircraft exterior inflow air to form an air mixture. The air conditioning pack conditions and circulates the air mixture into the aircraft interior.

Abstract: A refrigeration system includes a refrigerant circuit including a compressor and an expander which expands a refrigerant and generates power, for performing a refrigeration cycle. The refrigeration system includes a compressor control section and an expander control section which, when an operation stop signal is output during operation, reduces a rotational speed of the compressor and increases a rotational speed of the expander to increase the ratio of the rotational speed of the expander to the rotational speed of the compressor.

Abstract: The air conditioning system uses an air cycle thermodynamic process. The system comprises a centrifuge. This centrifuge includes at one of its ends, an axial inlet that funnels air into a centrifugal compressor rotating in unison with the centrifuge. The air is compressed, adiabatically heated and directed to a heat exchanger mounted in the rim of, and rotating with the centrifuge. The air is accelerated with respect the centrifuge by varying the centrifuge radius or by using forward leaning impeller blades. The air is cooled by the heat exchanger and directed to an expander also rotating with the centrifuge. The air is expanded and adiabatically further cooled. The cold air exits the centrifuge through an axial outlet located at the second end of the centrifuge.

Abstract: An aircraft cooling system includes a refrigerant cycle including a first heat exchanger. A liquid cycle passes a liquid through the first heat exchanger, at which it is cooled by a refrigerant in the refrigerant cycle. An air cycle compresses air and delivers the compressed air into a second heat exchanger. The liquid passes through the second heat exchanger at a location downstream of the first heat exchanger. The liquid cools the air in the second heat exchanger. Air downstream of the second heat exchanger passes to be utilized by a use on an aircraft.

Abstract: A method and a device for compressing a gas-phase medium, particularly hydrogen or natural gas, in a single-stage or multistage process using at least one piston compressor, wherein the medium may have a water content up to total saturation with water. The medium to be compressed is heated before the compression at least to such point that the water is unable to condense out during the compression process, and the compressed medium undergoes a water separation process.

Abstract: An assembly for an environmental control system includes a primary air-to-air heat exchanger and an aft manifold. The aft manifold is mounted to the primary heat exchanger and is adapted with a first duct to receive air flow from the primary heat exchanger. The aft manifold has a bypass duct and the bypass duct is configured to selectively allow air flow to bypass the primary heat exchanger.

Abstract: A ram air fan inlet housing for containing a ram air fan rotor. The inlet housing includes a flanged surface and an interior surface. The flanged surface is perpendicular to an axis of the inlet housing and defines a flange plane at an axial end of the inlet housing. The interior surface is symmetric about the axis of the inlet housing and includes a flange section, a transition section, an outlet section, a rotor section, and an inlet section.

Abstract: An environmental control apparatus includes (A) a condensation air flow loop in which a fan driven when the aircraft is moved on the ground or flies performs a thermal exchange with a condenser of a cooling/heating flow loop; (B) the cooling/heating flow loop, including an evaporator, a compressor configured to have a rotating shaft coupled to the shaft of a ram air turbine, a condenser configured to perform a thermal exchange by the condensation air flow loop, and an expansion valve configured to expand the refrigerant condensed by the condenser, wherein the evaporator, the compressor, the condenser, and the expansion valve are interconnected by a refrigerant circulation line; (C) an air circulation loop for circulating and supplying cooled or heated air to a camera/electronic unit so that the camera/electronic unit maintains a constant temperature; and (D) a controller for controlling the driving of the elements in each of the loops.

Abstract: A cabin air compressor assembly includes a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is located at a first end of the cabin air compressor motor substantially opposite a second end whereat the cabin air compressor is located. The cooling flow inlet is configured to direct a cooling flow across the cabin air compressor motor. A blower is operably connected to the cabin air compressor and is configured to urge a cooling flow from across the cabin air compressor motor toward a cooling flow outlet, thereby increasing the cooling flow across the cabin air compressor motor.

Abstract: The invention relates to a desalination method and system that uses freeze crystallization technology that incorporates the use of compressed air energy as the source for freezing temperatures. When compressed air is released by a turbo expander, chilled air is produced as a by-product, wherein the chilled air is introduced into a crystallization chamber. Also injected into the chamber is a spray cloud of seawater droplets, which has been pre-chilled by heat exchange with the cold chamber walls, and which is then circulated and exposed to the chilled air in the chamber. The sizes of the droplets can vary, but are preferably predetermined, along with the relative temperatures, flows and speeds of the spray and chilled air, such that when the droplets are circulated within the chilled air, and settle at the bottom of the chamber, they are deposited at slightly above the eutectic temperature.

Abstract: A method for providing a flow control system for an aircraft. A compressor is removed from an existing air cycle machine, along with compressor ducting that is connected to a primary stage outlet of the heat exchanger and a secondary stage inlet of the heat exchanger in the existing air cycle machine. A first connector duct is provided and connected to the primary stage outlet of the heat exchanger and the secondary stage inlet of the heat exchanger. The turbine is removed from the existing air cycle machine, and a second connector duct is provided and connected to the upstream turbine duct directly and the downstream turbine duct.

Abstract: A mixer has an internal bore with an inlet to a chamber, and an outlet at an opposed end/A duct is connected to receive a recirculated air flow. The duct communicates air into the chamber through recirculating air ports such that the recirculating air can mix with the air from the inlet. The mixer housing has a cockpit outlet for delivering air to a second outlet, with the cockpit output being located axially upstream from the recirculating air ports. An isolator is mounted at an outer periphery of the mixer housing, and has flat sides on each of two circumferentially spaced sides. A belly band is bolted to an outer periphery of the mixer housing and to flat sides of the isolator.

Abstract: The present invention provides a refrigeration cycle apparatus using a first compressor and a second compressor driven by an expander and including a high and low pressure heat exchanger, in which a low-pressure-side outlet of the high and low pressure heat exchanger is bypassed to a low pressure portion or an intermediate pressure portion to adjust an inlet density at the expander and thereby provide high efficiency. The high and low pressure heat exchanger of the refrigeration cycle apparatus of the present invention changes an amount of heat exchange between a high-pressure refrigerant and a reduced-pressure refrigerant branched from the high-pressure refrigerant at an inlet portion of the high and low pressure heat exchanger and reduced in pressure to adjust the density of the refrigerant flowing in the expander so that power recovered by the expander and power required by the second compressor match.

Abstract: A cooling system for an aircraft includes an air inlet through which air from the environment of the aircraft enters a ram air channel, and an air outlet through which air emerges from the ram air channel. A heat exchanger is arranged in the ram air channel. A ventilation device is in fluid communication with the ram air channel. Also connected to the ram air channel is a distribution line to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

Abstract: Environmental control systems and methods to control environmental temperature of an enclosed space by integrating a passive heat exchange subsystem (e.g., a loop heat pipe (LHP) heat exchange subsystem) having a closed loop heat exchange fluid circuit in heat-exchange relationship with the enclosed space for providing environmental temperature control therewithin, a RAM-air subsystem having a RAM-air circuit for circulating RAM cooling air, and a vapor compression cycle machine (VCM) subsystem having a VCM fluid circuit having a compressor, an evaporator, a condenser and an expansion valve.

Abstract: The invention is directed to processes and apparatuses for gas treatment, in particular for the purification of methane rich gas streams, such as gas obtained from the conversion from organic matter (“biogas”). In accordance with the present invention there is provided an apparatus and a process for producing a purified methane comprising gas stream (P) from a methane containing gas stream (A), comprising the steps of: (a) pressurising said methane containing gas stream (A) and subsequently cooling it, whereby a stream comprising condensed contaminants (C) and a methane comprising stream (B) are obtained; (b) optionally feeding said methane comprising stream (B) to an adsorption unit and/or a catalytic conversion unit, whereby the concentration of contaminants in stream (B) is further decreased; and (c) cooling the methane comprising stream (B) to a temperature which is sufficient to condensate CO2 from said stream (B), whereby said purified methane comprising gas stream (P) is obtained.