53 results about "Air cycle machine" patented technology

The invention belongs to the technical field of electrical equipment, and discloses a dust-removing and moisture-proof treatment device for an automatic element of an electrical instrument. The electrical instrument automation element dust removal and moisture prevention treatment device comprises a cabinet body, a cabinet door is arranged at an opening of the cabinet body, a partition plate is fixedly connected in the cabinet body, an inner cabinet is arranged in the cabinet body and located on the upper side of the partition plate, and an inner cabinet door is arranged at an opening of the inner cabinet. According to the dust-removing and moisture-proof treatment device for the automatic element of the electrical instrument, by means of the design of the air circulation mechanism and the air compression mechanism, dust removal and dehumidification treatment can be conducted on external air, the treated air is compressed and stored, and the air circulation mechanism extracts air from a compressed air bottle to conduct circulating heat dissipation on the electrical instrument in the inner cabinet; the direct contact between external air and the electrical instrument is effectively avoided, the adverse effect of dust and water vapor on the electrical instrument is avoided, and the problems proposed in the background technology are solved.

A system that provides a cooling liquid to a component of an aircraft, the system having: a cooling circuit that includes a fuel cell that receives a first flow and transfers first waste heat to the first flow; an air cycle machine (ACM) that transfers second waste heat to a second flow; a first heat exchanger, fluidly coupled to the cooling circuit downstream of the fuel cell, that thermally couples the first and second flows to superheat the first flow; a turbine, fluidly coupled to the cooling circuit downstream of the first heat exchanger, that extracts energy from the first flow; and a condenser, fluidly coupled to the cooling circuit downstream of the turbine, that condenses the first flow into the cooling liquid, wherein the component is fluidly coupled to the circuit downstream of the condenser.

Aircraft air cycle machines include a first stage turbine, a second stage turbine that receives air from the first stage turbine, and a duct arranged between the first stage turbine and the second stage turbine. A circular finned coalescer is arranged within the duct and includes a central body, a first fin layer wrapped about the central body, a first parting sheet wrapped about the first fin layer, and a second fin layer wrapped about the first parting sheet. Each of the fin layers include a plurality of fin elements and channels are defined between circumferentially adjacent fin elements of each of the first and second fin layers. The channels are tortuous channels such that moisture carried on a flow through the channels will impinge upon surfaces of the fin elements and coalesce into water droplets.

The application belongs to the field of aviation environmental control system design, and particularly relates to a bidirectional-ejection-based aircraft heat exchange system. The system comprises a ram air inlet channel, a heat exchanger and an air circulator. The ram air inlet channel comprises a ram air inlet section (1), a transition ejection section (4) and a ram air outlet section. The heat exchanger comprises an air-liquid heat exchanger (2), a first air-air heat exchanger and a second air-air heat exchanger. The air circulator comprises a first air circulator and a second air circulator. The bidirectional-ejection-based aircraft heat exchange system utilizes the principle of constant entropy ejection to limit the ram air flow entering the left and right ram air outlet channels, and integrates the cold side of the heat exchanger with the ram air inlet channel, and matches the dynamic pressure brought by the ram air with the flow resistance of the heat exchanger group, thereby effectively avoiding problems such as fan overspeed, windmill effect and surge of the air circulator.

A single shaft, one piece rotor having: a hub that extends from a hub aft end to a hub forward end, wherein the hub aft end defines a first diameter and the hub forward end defines a second diameter that is smaller than the first diameter; a plurality of blade stages extending from a forward end to an aft end, wherein the blade stages are stacked, one on top of the other, radially outwardly from the hub, including an inner stage that is integral with the hub and an outer stage that is radially spaced apart from the hub; and a shroud between adjacent ones of the blade stages.

An air cycle system for a gas turbine engine includes a heat exchanger having an air cycle inlet. An air cycle machine includes an air cycle machine outlet and an annular flexible interface coupling connecting the air cycle inlet to the outlet. The flexible interface coupling includes a receiving portion having a flared region across which a diameter of a heat exchanger portion increases and a landing portion across which the diameter of the heat exchanger portion is maintained. An air cycle machine portion is received in the receiving portion and includes an outlet flange and a diffuser radially inward of the outlet flange. The outlet flange includes a radially outward facing surface contacting a radially inward facing surface of the landing portion. The diffuser is configured to move axially and radially relative to the outlet flange.

An environmental control system (ECS) of an aircraft, having a case; a vaper compression system (VCS) having a compressor and a driven shaft coupled to the compressor, wherein the compressor and the driven shaft are sealed within the case; and a four-wheel air cycle machine (ACM) including a first turbine and a drive shaft coupled to the first turbine and which are outside the case, a second turbine connected to the first turbine via a second shaft, a second compressor connected to the second turbine via a third shaft, and a fan connected to the second compressor via a fourth shaft, wherein the drive shaft and the driven shaft are coupled to each other via a coupling.

An ACM having a motor with front and aft ends; a compressor coupled to the front end; a turbine coupled to the aft end; a shell having a shell front part that surrounds the compressor and defines a shell inlet, a shell aft part that surrounds the turbine and defines a shell outlet, and a shell middle part that surrounds the motor; an outer flow passage is defined within the shell, surrounding the compressor, the motor and the turbine; a shaft extends between the compressor and turbine to define a shaft front end coupled to the compressor, and a shaft aft end coupled to the turbine, and the motor includes a rotor that is mounted to the shaft.

The application provides a turbine transmission shaft and an air circulating machine, the turbine transmission shaft comprises a first shaft section, a second shaft section and a thrust section, the first shaft section, the thrust section and the second shaft section are sequentially arranged, the first shaft section, the thrust section and the second shaft section are integrally formed and can conduct heat between each other; the axial side surface of the thrust section towards the first shaft section is a first thrust disc surface, the axial side surface of the thrust section towards the second shaft section is a second thrust disc surface, the radial outer periphery of the thrust section can introduce cooling gas and can divide the cooling gas into at least two streams, one of which can pass through the first thrust disc surface and reach the outer peripheral wall of the first shaft section, and the other of which can pass through the second thrust disc surface and reach the outer peripheral wall of the second shaft section. According to the application, flow distribution is not needed for the cooling of the first shaft section and the second shaft section, and the problem of flow distribution involved in the cooling of the aerodynamic bearing at different positions of the existing air circulating machine is solved.

The utility model relates to plasma cleaning, and discloses an air circulation device of a plasma cleaning machine, which comprises an air circulation mechanism, the air circulation mechanism comprises an arc-shaped suction cover, an air circulation cover is sequentially arranged on the surface of the side wall of the arc-shaped suction cover, and a control box is arranged in the middle of the top end of the air circulation cover. An air suction sleeve is arranged in the middle of the top end of the control box, a base is arranged in the middle of the top end of the air suction sleeve, when the arc-shaped suction cover operates in the inner space of the plasma cleaning machine, the opened air suction sleeve and a sleeve of the air suction sleeve are arranged in a unified mode, and the base is used for being connected with a pipe body of an L-shaped guide pipe. Corresponding upper top plate structures are connected with one another according to the plate face structures of the corresponding side wall baffles, and circulation of gas in the vacuum box is achieved.

An air cycle machine (ACM), having a heat exchanger having a front end and an aft end; a compressor at the front end of the heat exchanger; a turbine at the aft end of the heat exchanger; a shell having a shell front part that surrounds the compressor and defines a shell inlet, a shell aft part that surrounds the turbine and defines a shell outlet, and a shell middle part that surrounds the heat exchanger, wherein a flow passage is defined within the shell and around the compressor, through the heat exchanger, and around the turbine; and a shaft extending between the compressor and the turbine that couples the compressor and the turbine.

A single-shaft unitary centrifugal rotor for an air cycle machine (ACM), having: a body extending from a body forward end to a body aft end; a flange intermediate the body forward and aft ends; a first rotor extending forward from the flange by a first axial length to a first rotor end at or near the body forward end, the first rotor defining a first hub and a first blade stage extending outwardly from the first hub; a second rotor extending aft from the flange by a second axial length to a second rotor end at or near the body aft end, and defining a second hub and a second blade stage extending outwardly from the second hub; a passage defined through the unitary rotor, between the body forward and aft ends, that receives a drive shaft.

The utility model provides a turbine shell assembly and an air circulation machine, the turbine shell assembly comprises a turbine shell body and an air outlet pipe formed on the turbine shell body, the turbine shell assembly further comprises an ultrasonic wave deicing device, the ultrasonic wave deicing device comprises an ultrasonic wave generator, and the ultrasonic wave generator is arranged on the turbine shell body. And the ultrasonic generator is arranged on the pipe wall of the air outlet pipe. Compared with a manual deicing mode in the prior art, the ultrasonic generator is used for deicing under the cavitation effect, the deicing efficiency is higher, and the inner wall face of the air outlet pipe cannot be damaged; compared with the mode of melting ice by introducing high-temperature airflow in the prior art, according to the technical scheme, the temperature of the air outlet airflow in the air outlet pipe cannot be affected in the deicing process, fluctuation of the air outlet temperature is prevented, and the refrigerating capacity of the system is not lost.

An environmental control system (ECS) of an aircraft, having: a case; a vaper compression system (VCS) having a compressor and a driven shaft coupled to the compressor, wherein the compressor and the driven shaft are sealed within the case; and an air cycle machine (ACM) including a first turbine and a drive shaft coupled to the first turbine and which are outside the case, wherein the drive shaft and the driven shaft are coupled to each other via a coupling.

The application provides a processing and manufacturing method of an air circulating machine shell and the air circulating machine. The processing and manufacturing method comprises the following steps: fixing and connecting a turbine shell and a compressor shell according to the position in the use state to be integrated, so that the first radial air bearing stator hole section on the turbine shell and the second radial air bearing stator hole section on the compressor shell are oppositely arranged; the boring cutter is penetrated from the first radial air bearing stator hole section to the second radial air bearing stator hole section along the axial direction of the first radial air bearing stator hole section, and the boring cutter is controlled to rotate to bore the first radial air bearing stator hole section and the second radial air bearing stator hole section to the design size at one time. The coaxiality of the radial air suspension bearings at the two ends of the rotating shaft in the rotor system is greatly improved, so that the eccentricity of the rotating shaft is reduced, the abnormal vibration and instability of the rotor are effectively prevented, and the occurrence probability of the bearing abrasion or damage of the air suspension bearing caused by the vibration and instability of the rotating shaft is reduced.

The present invention relates to an energy-saving vertical air circulating machine with a double-axle motor and double fans, which comprises: a housing, an indoor air supply part provided on the upper part of the front face, an indoor air exhaust port provided on each lower part of the two side faces, a first outdoor air supply port, a second outdoor air supply port and an outdoor air exhaust port provided on the upper part of the rear face; a first heat exchange device and a second heat exchange device, which are respectively located on the lower part of the indoor side of the housing, and respectively realize the heat exchange of indoor air and outdoor air; an air supply double fan assembly for generating air flow to supply external air to the indoor through the indoor air supply part; an exhaust fan assembly for generating air flow to exhaust indoor air to the outdoor through the outdoor air exhaust port; a first rear side air supply pipe provided on the rear face of the indoor side of the housing to guide the external air supplied to the first outdoor air supply port to flow into the first heat exchange device; a second rear side air supply pipe; and a flow path forming exhaust pipe.

The utility model discloses an automatic power-off protection device for an expansion machine of a deep cooling air separation plant, which comprises a rectangular cold box, an air circulation mechanism is arranged in the rectangular cold box and is connected with an electric power transmission line, a power-off detection box is arranged on the electric power transmission line, a controller is arranged on the power-off detection box, and the controller is connected with the rectangular cold box. The controller is connected with a buzzer, an alarm lamp and a pneumatic ball valve, the buzzer, the alarm lamp and the pneumatic ball valve are connected with a first storage battery arranged in the mounting box, the buzzer and the alarm lamp are fixedly mounted on the outer side of a positioning plate, and a connecting block is arranged on the other side of the positioning plate. According to the automatic power-off protection device for the expansion machine of the deep cooling air separation plant, the problem that an existing automatic power-off protection device for the expansion machine of the deep cooling air separation plant cannot give an alarm to workers when the power-off condition occurs is solved, and an air circulation mechanism is arranged in a rectangular cold box.

The utility model relates to the technical field of calendaring machines, and discloses a calendaring machine for producing a high-flatness floor wear-resistant layer, which comprises a calendaring roller, a rack and a power device, a heating cavity and a heater are arranged in the calendaring roller, and the calendaring roller can heat the floor wear-resistant layer, has flowability, improves flatness and physical properties, and avoids deformation and warping. A hollow shaft is further fixed in the calendering roller and communicated with the heating cavity, and an air circulation mechanism is arranged on the outer side of the machine frame and can extract high-temperature air in the heating cavity and convey the high-temperature air into the machine frame to preheat a floor abrasion-resistant layer. And the heater comprises a plurality of heating rods which are uniformly distributed on the side wall of the calendering roller. One end of the calender roller is provided with a conductive slip ring which can ensure stable work of the heating rod. The air circulation mechanism comprises an air pump, a first multi-way pipe, a second multi-way pipe and a rotary valve and can drive hot air to circulate, so that the interior of the rack is kept at a stable preheating temperature. An air outlet plate is arranged on the inner side of the feeding hole, so that the temperature loss can be further reduced.

The invention relates to the technical field of industrial tunnel furnace waste heat recovery equipment, in particular to a basin-type insulator tunnel furnace demolding waste heat recovery device which comprises a tunnel furnace demolding waste heat recovery device body, a conveying mechanism, an air circulation mechanism, a terminal controller, a sealing pneumatic door, a heating tray and a connecting table. The tunnel furnace demolding waste heat recovery device body and the outlet end of the tunnel furnace are connected with a connecting table, and a conveying mechanism is arranged in the tunnel furnace demolding waste heat recovery device body. The port of the tunnel furnace is externally connected with the double-layer gradient heat preservation cavity and the automatic conveying system, the heat preservation uniformity problem is effectively solved, the heat preservation section is of an upper-lower-layer independent temperature control structure, accurate temperature control is achieved, and the heat preservation efficiency is improved. The micropore air supply design of the gap between the top air duct and the bottom roll shaft ensures that the convex surface and the concave surface of the die receive uniform hot air flow at the same time, and the local stress concentration phenomenon is effectively reduced.

Aircraft air cycle machines include a first stage turbine, a second stage turbine, and a duct arranged between the first stage turbine and the second stage turbine. A plate-fin coalescer is arranged along the duct. The plate-fin coalescer includes a housing, a first fin layer arranged within the housing, a second fin layer arranged within the housing, and a first parting sheet arranged between the first fin layer and the second fin layer. Each of the first fin layer and the second fin layer include a plurality of fin elements arranged in substantially parallel orientation relative an axis through the housing, and channels are defined between adjacent fin elements of the plurality of fin elements of each of the first fin layer and the second fin layer. Moisture carried on a flow through the channels will impinge upon surfaces of the fin elements and coalesce into water droplets for removal.

The utility model discloses a general assembly positioning device for an aircraft air circulation refrigeration assembly. Comprising a supporting frame (70), a positioning flat plate (701) is arranged on the supporting frame (70), and a pair of two-stage radiator fixing supporting columns (10) used for positioning a two-stage radiator in the aircraft air circulation refrigeration assembly, a radiator supporting seat (20) used for supporting the two-stage radiator and a supporting base (30) used for supporting an air circulation machine in the aircraft air circulation refrigeration assembly are installed on the positioning flat plate (701). The air circulation machine fixing supporting column (40) is used for positioning an air circulation machine, and the condenser fixing supporting column (50) and the heat regenerator fixing supporting column (60) are used for positioning and supporting a heat regeneration condenser assembly in the aircraft air circulation refrigeration assembly. According to the utility model, the final assembly positioning of the refrigeration assembly is realized while the final assembly tool efficiency of the refrigeration assembly is improved, and the requirement of the refrigeration assembly on the final assembly size precision is met.

A thermal expansion absorbing coupler configured to join individual pipes includes a multi-segment retaining shell having a V-shaped cross-section inner surface configured to draw together adjoining pipe ends. The coupler also includes a high-temperature material sealing ring configured to be arranged between the retaining shell and outer diameter of the adjoining pipes and block leakage of airflow from between the adjoining pipe ends. A test stand configured to position thereon an air cycling machine (ACM) having a compressor and a turbine may employ such a thermal expansion absorbing coupler. On the test stand, the coupler connects the ACM to a duct assembly and / or joins individual pipes of the duct assembly and absorbs thermal expansion of the duct assembly.

This utility model discloses a novel temperature control device for salt spray testing, relating to the technical field of salt spray testing equipment. It includes: a housing, a partition plate, a temperature and humidity regulating mechanism, and multiple radiant heating plates. The partition plate is disposed within the housing to divide it into a salt spray testing area and an equipment area. The temperature and humidity regulating mechanism includes an air circulation mechanism, a heater, and a humidifier. The air circulation mechanism is disposed in the equipment area, with both its inlet and outlet connected to the salt spray testing area to facilitate air exchange between the two areas. The heater is disposed in the equipment area to heat the air entering the area, and the humidifier is disposed in the equipment area to humidify the air entering the area. Each radiant heating plate is disposed in the salt spray testing area to maintain its temperature. This utility model effectively improves the temperature control response speed, enhances the accuracy of temperature control, and improves the efficiency and accuracy of salt spray testing.

Vehicle cooling air supply system and method A system and method for supplying cooled air to a vehicle, such as an aircraft, is disclosed. The system includes an air cycle machine (ACM) configured to compress and cool a flow of air to generate a cooled flow of air, an air flow path configured to direct the cooled air from the ACM to one or more portions of the vehicle, and a phase change material (PCM) heat exchanger positioned to further cool the air before it reaches at least one of the one or more portions of the vehicle in addition to the cooling provided by the ACM.

To provide an ingot preheater which enables reduction of energy consumption.SOLUTION: An ingot preheater according to an embodiment includes: a housing; a lower sprocket and an upper sprocket provided within the housing; a chain combined with the lower sprocket and the upper sprocket; a plurality of ingot holding parts which are fixed to the chain and on each of which an ingot may be placed; a rotation mechanism which rotates at least one of the lower sprocket and the upper sprocket; a partition plate which is provided at the inner side of the chain and partitions the housing into a first area where the chain moves up and a second area where the chain moves down; a first heater provided at the side of the first area of the partition plate; a second heater which is provided at the side of the second area of the partition plate and can be controlled independently of the first heater; an air circulation mechanism which circulates air in the housing; an ingot carry-in port; and an ingot carry-out port.SELECTED DRAWING: Figure 1

An environmental control system of an aircraft, having a first flow circuit that transports a first flow to a cabin; a second flow circuit that transports a second flow away from the cabin and is fluidly separated from the first flow circuit; wherein the first flow circuit includes: a first compressor that is a cabin air compressor; an air cycle machine (ACM) downstream of the first compressor; and a primary heat exchanger between the first compressor and the ACM, and wherein the second flow circuit directs the second flow to the primary heat exchanger to condition the first flow prior to reaching the ACM.

The invention discloses an electric compressor high-humidity environment endurance test device, which comprises a mounting frame, a test box arranged at the top of the mounting frame, a test cavity arranged in the test box, a plurality of humidity sensors arranged in the test cavity, a sealing cabin door arranged at the front end of the test cavity in the test box, and an assembly seat arranged at the bottom of the inner side of the test cavity, limiting frames are installed on the two sides of the top of the assembly base, a driving motor is installed in the installation frame, the power output end of the driving motor is connected with a transmission assembly, the power output end of the transmission assembly is arranged in the test cavity, a spraying assembly is installed on the top of the test cavity, the input end of the spraying assembly is connected with a water storage tank, and the water storage tank is installed on the installation frame. An air circulation mechanism is mounted at the top of the test box, and the output end of the air circulation mechanism is arranged at the top of the test cavity.

The application provides an air circulating machine rotor axial force adjusting structure and an air circulating machine. The air circulating machine rotor axial force adjusting structure comprises a compressor volute and a driving shaft. The first end of the driving shaft is supported in the bearing chamber of the compressor volute through a radial bearing. A fan impeller is connected to the first end face of the driving shaft. The driving shaft between the radial bearing and the fan impeller is provided with a pressure regulating ring. The compressor volute is further provided with a first through hole communicating with the bearing chamber. The first through hole is located on the side of the bearing chamber close to the fan impeller. The pressure regulating ring comprises a connecting ring and a comb tooth pressure reduction structure on the outer circumferential wall of the connecting ring to form a pressure reduction annulus between the pressure regulating ring and the hole wall of the first through hole. The application can effectively reduce the axial resultant force of the driving shaft, reduce the bearing wear and improve the operation stability of the equipment.

In accordance with at least one aspect of this disclosure, a system includes an airflow line, a main compressor disposed in the airflow line configured to receive a ram air flow and supply a compressed air flow to the air flow line, and a motor operatively connected to drive the main compressor. An air cycle machine is disposed in the airflow line downstream of the main compressor configured to receive the compressed airflow and supply a cooled cabin airflow to an aircraft cabin. A cooling line tap disposed in the airflow line downstream of the air cycle machine configured to communicate a flow of cooling air to the motor from the airflow line to supply a portion of the cooled cabin airflow to one or more portions of the motor as motor cooling air via a first cooling airflow line.