216 results about "Air cycle machine" patented technology

An environmental control system for an aircraft cabin includes a plurality of electrically-driven ported shroud cabin air compressors, each cabin air compressor compressing ram air received from the aircraft exterior, a heat exchange circuit comprising a primary heat exchanger receiving airflow from at least one of the cabin air compressors, and the secondary heat exchanger supplying airflow to the aircraft cabin, and an air cycle machine comprising a compressor adapted to receive airflow from the primary heat exchanger and supply compressed air to the secondary heat exchanger. The environmental control system may further comprise an air recirculation system, having an aft recirculation fan adapted to receive a portion of recirculation air from the aircraft cabin, and a recirculation heat exchanger, disposed in the heat exchange circuit in series with the primary and secondary heat exchangers, and adapted to receive airflow from the aft recirculation fan.

An aircraft environmental control system (ECS) may be configured to operate in first mode and a second mode. The ECS may include an air cycle machine (ACM), a by-pass valve positioned to allow bleed air to by-pass the air cycle machine so that when the by-pass valve is open, the ECS operates in the first mode with bleed air at a first pressure and when the by-pass valve is closed the ECS operates in the second mode at a second bleed air pressure, higher than the first bleed air pressure. A bleed air system controller and ECS controller may be configured to selectively couple high pressure or low pressure bleed air ports of an engine of an aircraft to the ECS and control the by-pass valve position.

The present invention provides an air generation unit (AGU) including a pressurized air source, such as an engine providing pressurized air. First and second air cycle machine (ACM) are fluidly connected to the pressurized air source for receiving the air. A heat exchanger interconnects the first and second ACMs. The heat exchanger mechanically supports the first and second ACMs by flexible isolators, which accommodates the thermo expansion of the heat exchanger through out the operation of the AGU. The heat exchanger includes a primary heat exchanger that cools the air from the air source. The ACMs each include a compressor receiving the air from the primary heat exchanger to provide compressed air. The compressed air is sent to a secondary heat exchanger to be cooled. The compressed air is passed through a condenser and a water collector to remove moisture from the air for being sent to a first turbine. The first turbine expands the dehumidified air to produce a first conditioned air having a first temperature. A second turbine further expands the conditioned air to produce a second conditioned air having a second temperature.

A bleed air system for an aircraft has a gas turbine engine and operating method. The system includes an environmental control system (ECS) for providing cabin airflow to the aircraft, including operating modes such as first and second air cycle machine operating modes and heat exchanger operating modes. The ECS includes first, second and third bleed ports each configured to provide engine bleed air from gas turbine engine compressors to the ECS. The ECS includes a bleed air system sensor arrangement configured to sense one or more bleed air system conditions, an environmental control system controller that selects an environmental control system operating mode that provides required cabin air flow and temperature at an optimal specific fuel consumption of the gas turbine engine at the sensed system conditions, and a bleed port valve controller which determines an operating pressure required to operate the environmental control system in the selected mode.

An air cycle machine includes a housing having a compressor housing portion. A shaft is supported by the housing and includes a thrust runner. A hydrodynamic thrust bearing is arranged adjacent to the thrust runner and includes upstream and downstream sides. A compressor rotor is mounted on the shaft. A seal is arranged between the compressor rotor and the compressor housing portion. An orifice is provided in the compressor housing portion at the downstream side of the hydrodynamic bearing. The orifice vents hot compressed air that may leak past the seal prior to reaching the hydrodynamic thrust bearing.

An air cycle machine for extracting bleed air from a gas turbine engine of an aircraft is provided. The air cycle machine extracts a stream of low pressure bleed air and a stream of high pressure bleed air from a compressor section of the gas turbine engine. The air cycle machine includes a compressor that receives the stream of low pressure bleed air and a turbine that receives the stream of high pressure bleed air. The stream of high pressure bleed air is expanded as it drives the turbine, and the stream of low pressure bleed air is compressed by the compressor. The resulting streams of bleed air are substantially the same pressure, such that they may be merged using a junction into a combined bleed air stream having a temperature and pressure suitable for use by a variety of aircraft accessory systems, such as an environmental control system. The air cycle machine may further power or be powered from an electrical storage device or generator on the fan.

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.

The following invention relates to an air conditioning system, in particular for aircraft, comprising at least one heat exchanger, arranged in a ram air duct, for cooling compressed air by means of a fluid, and comprising at least a first and a second air cycle machine which at the compressed-air end are connected to the heat exchanger. A particularly compact, reliable, redundant and economical arrangement is achieved in that the heat exchanger comprises at least one first heat exchanger unit and a second heat exchanger unit, of which one each is connected at the compressed-air end to one of the air cycle machines, and in that ram air outlet ducts which are fluidically separate from each other are provided, of which one is connected to the first heat exchanger unit and another is connected to the second heat exchanger unit.

An air cycle machine (ACM) pack system for an aircraft with an improved low inlet pressure cooling performance is provided. The ACM pack system has an air cycle machine (ACM) with at least one compressor mechanically coupled to at least one turbine in series on an ACM shaft. The ACM pack system further has a pack heat exchanger coupled to and in fluid communication with the at least one compressor of the ACM. The ACM system further has a bypass air flow assembly coupled in a parallel operation path to the ACM and has a bypass air flow regulating element. The bypass air flow assembly transfers energy extracted by the bypass air flow assembly to the ACM to aid the ACM pack system in cooling performance at a low inlet pressure, resulting in an improved low inlet pressure cooling performance of the ACM pack system.

An example journal air bearing for a rotatable shaft of an air cycle machine includes a top foil configured to receive a rotatable shaft, and an intermediate foil radially outboard the top foil. A journal sleeve is radially outboard the intermediate foil. The top foil and the intermediate foil establish apertures configured to communicate fluid between a first position radially inboard the top foil and a second position radially outboard the intermediate foil.

An environmental control system comprising that utilizes recirculation air. The environmental control system includes an inlet configured to supply bleed air at a first energy from a source to the environmental control system, where the environmental control system supplies the bleed air at a second energy to a chamber. The environmental control system also includes an air cycle machine comprising a compressor and a turbine, where the air cycle machine receives the recirculation air from the chamber and the recirculation air is bleed air at a third energy flowing from the chamber to the air cycle machine.

The invention relates to an air-conditioner mattress which can automatically adjust temperature. Two sides of the mattress are drilled with ventholes; the inside of the mattress is provided with a hollow pipe frame which is formed by hollow pipes connected together; small air holes are drilled on the hollow pipe frame; the hollow pipe frame is communicated with an air circulator; the air circulator is controlled by a circuit board which is provided with a temperature sensing head, a control panel and a computer board; when a temperature in the mattress is lower than a set temperature on the control panel, the air circulator automatically starts up and transports heated air to the mattress through the hollow pipe frame so as to rapidly heat up the mattress. When the temperature in the mattress is higher than the set temperature on the control panel, the air circulator is changed from an air blow state to an air exhaust state and exhausts hot air in the mattress by the hollow pipes in order to rapidly cool down the mattress, thereby ensuring that the mattress is warm in winter and cool in summer and is suitable for four seasons.

An air cycle machine includes two turbines and a compressor mounted on an integral shaft. The integral shaft includes a plurality of shaft sections that are welded together and machined in a single set-up process into a desired shaft shape to provide highly aligned bearing surfaces. The shaft includes three stops that cooperate with three fasteners to secure the two turbines and the compressor on the shaft.

The invention discloses a device for cooling and purifying air in an automobile, arranged on a platform behind a back of a seat in a back row of the automobile. The device comprises an air circulating mechanism and a power supply, wherein the power supply comprises a storage battery (1) and a solar cell panel (2); the air circulating mechanism comprises a fan (3), an air inlet pipe (4) and an air outlet pipe (5), wherein the fan (3) is connected at one side of the air outlet pipe (5), an air inlet hole and an air outlet hole are arranged at the bottom of a trunk of the automobile, one end of the air inlet pipe (4) is communicated with the air inlet hole, one end of the air outlet pipe (5) is communicated with the air outlet hole, one side of the solar cell panel (2) is connected with a motor (6) which drives the solar cell panel (2) to turn over, wherein one side of the solar cell panel (2) is radially connected with an output shaft of the motor; and a storage battery (1) is electrically connected with the fan (3) and the motor (6), and the solar cell panel (2) is electrically connected with the storage battery (1). By adopting the device disclosed by the invention, the solar cell panel turns over to realize sunshading and generating, and the effects of purifying and cooling in the automobile can be realized by virtue of the air circulating mechanism and a multi-purification mechanism.

According to one aspect, an air cycle machine includes a fan rotor, a diffuser cone axially aligned with the fan rotor, and a strut plate assembly. The strut plate assembly includes a first strut plate and a second strut plate with an ejector formed between the first strut plate and the second strut plate. The first strut plate is axially positioned between the fan rotor and the ejector, and the second strut plate is axially positioned between the fan rotor and the diffuser cone. The first strut plate includes a plurality of outer struts and is absent inner struts between the fan rotor and the ejector. The second strut plate includes a plurality of inner struts and outer struts, where the inner struts are axially positioned between the ejector and the diffuser cone.

An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage is fluidly coupled to a bleed port of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system includes a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine in fluid communication to outputs of the cooling stages to selectively receive the cool bleed air or the intercooled cooling air.

An aircraft environmental conditioning system is disclosed having an air cycle machine for conditioning an airflow comprising hot compressed air by reducing its temperature and pressure. The air cycle machine is disposed in a housing in an unpressurized area of the aircraft, and produces conditioned pressurized air for delivery to a pressurized area of the aircraft. The system also includes a vibration sensor disposed within the housing, and a controller in communication with the vibration sensor that is configured to respond to vibration detected by the vibration sensor.

Environmental control system bleed air is cooled by a heat exchanger. A fan pulls ambient air from a ram inlet duct across the at least heat exchanger and to an outlet. An air cycle machine drives the fan. The bleed air passes downstream of the at least heat exchanger to a compressor, and then drives a first stage turbine. The first stage turbine has an outlet communicating with a condenser, and then a second stage turbine. An icing control system taps hot air downstream of the compressor. An add heat valve is selectively moveable between a first position blocking flow from the tap passage. A second position where it passes air from the tap passage to the condenser inlet, and to a point downstream of the condenser and to the second stage turbine. In a third position, the valve only communicates air from the tap passage into the condenser.