Air Compessor, Cooler And Expander Patents (Class 62/172)
  • Patent number: 11273918
    Abstract: An aircraft cooling system and an aircraft having an aircraft cooling system of this type. The aircraft cooling system comprises a ram air duct, a nozzle arranged in the ram air duct and connected to a first water-conducting line, and a refrigeration device. The refrigeration device comprises a heat exchanger thermally coupled to the refrigeration device and configured to release waste heat generated by the refrigeration device to cooling air present in the ram air duct, a first water separator configured to separate off water from the air cooled by the refrigeration device, and a water outlet configured to conduct water obtained in the first water separator into the first water-conducting line. Furthermore, the water outlet has an inlet configured to be connected to a second water-conducting line, wherein the water outlet is furthermore configured to generate a negative pressure at the inlet.
    Type: Grant
    Filed: April 15, 2019
    Date of Patent: March 15, 2022
    Assignee: AIRBUS OPERATION GMBH
    Inventor: Frank Klimpel
  • Patent number: 11192655
    Abstract: An environmental control system of an aircraft includes a ram air circuit with a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, a compression device arranged in fluid communication with the ram air circuit and the at least one dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit. At least one of the compression device and the expansion device is selectively operable to supplement the ram air within the ram air circuit to meet a demand of the aircraft.
    Type: Grant
    Filed: November 3, 2017
    Date of Patent: December 7, 2021
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Louis J. Bruno, Thomas M. Zywiak
  • Patent number: 11118808
    Abstract: A method, system, and device for liquid drainage are provided. The system includes a drain tube coupled to the air distribution system, a sump coupled to the drain tube and configured to receive liquid from the drain tube, and a suction system in flow communication with the sump. The suction system is configured to create a pressure in the sump that is lower than a pressure in the air distribution system.
    Type: Grant
    Filed: December 6, 2013
    Date of Patent: September 14, 2021
    Assignee: THE BOEING COMPANY
    Inventor: Fue Chue Vue
  • Patent number: 11084592
    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, a dehumidification system arranged in fluid communication with the ram air circuit, and a compression device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor, a turbine, and a fan coupled by a shaft, wherein the fan is operable to move ram air through the ram air circuit and the turbine includes a first inlet for receiving a first flow of medium and a second inlet for receiving a second flow of medium.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: August 10, 2021
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Louis J. Bruno, Christina W. Millot
  • Patent number: 11072429
    Abstract: A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: July 27, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 10994848
    Abstract: An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a first flow of a medium and a turbine configured to receive the first flow of the medium and a distinct second flow of the medium. A dehumidification system is arranged in fluid communication with the turbine. A valve is configured to divert the second flow around the turbine and an inlet port is arranged in fluid communication with the compressor, the turbine, and the dehumidification system.
    Type: Grant
    Filed: March 19, 2019
    Date of Patent: May 4, 2021
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventor: Louis J. Bruno
  • Patent number: 10962294
    Abstract: A heat exchanger assembly for an aircraft with an environmental control system includes first and second heat exchangers, a closure bar, and a drain manifold. The first heat exchanger is in fluid communication with a source of bleed air from the aircraft. The second heat exchanger has a second hot air circuit passing through the second heat exchanger and is disposed adjacent to and in fluid communication with the first heat exchanger. The closure bar is disposed between the first and second heat exchangers such that the closure bar prevents fluid communication across the closure bar between the first and second heat exchangers. The drain manifold is mounted to a sidewall of the heat exchanger assembly. A channel of the drain manifold is in fluid communication with a surface of the closure bar.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: March 30, 2021
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, Frederick Peacos, III
  • Patent number: 10934881
    Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air flows from a source to mix with recirculated air in accordance with a high pressure mode or a recirculation chilling mode. The system and method also can also utilize the recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: March 2, 2021
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Louis J. Bruno, Thomas M. Zywiak, Donald E. Army, Jr., Harold W. Hipsky, Richard Rusich, Erin G. Kline, Eric Surawski, John M. Maljanian, Jr., Paul M. D'Orlando
  • Patent number: 10934007
    Abstract: An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: March 2, 2021
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Tony Ho, Alan Retersdorf
  • Patent number: 10906653
    Abstract: An aircraft air conditioning system comprising an air conditioning unit adapted and configured to be supplied with compressed process air and to generate cold fresh air, a mixer adapted and configured to mix the cold fresh air from the air conditioning unit with recirculation air recirculated from an aircraft region to be air conditioned, an air outlet adapted and configured to direct mixed air from the mixer into the aircraft region, a first sensor adapted and configured to detect an actual temperature in the aircraft region, a second sensor adapted and configured to detect a temperature of the mixed air directed into the aircraft region, and a control unit adapted and configured to control an operation of the air conditioning unit in dependence on a difference between the temperature of the mixed air directed into the aircraft region and the actual temperature in the aircraft region.
    Type: Grant
    Filed: September 1, 2016
    Date of Patent: February 2, 2021
    Assignees: AIRBUS OPERATIONS GMBH, AIRBUS SAS
    Inventors: Nicolas Houis, Dariusz Krakowski, Tim Giese
  • Patent number: 10794290
    Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases 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. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nathan Snape, Joseph Brent Staubach, Frederick M. Schwarz
  • Patent number: 10760492
    Abstract: A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: September 1, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: John W. Golan, Frederick M. Schwarz
  • Patent number: 10723463
    Abstract: A method for efficient operation of an environmental control system having a plurality of air cycle machines includes disabling operation of a first air cycle machine from the plurality of air cycle machines, enabling operation of one or more additional air cycle machines from the plurality of air cycle machines, monitoring at least one operating characteristic of the environmental control system, and resuming operation of the first air cycle machine upon determining that a condition has been satisfied based on the at least one operating characteristic of the environmental control system.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: July 28, 2020
    Inventor: Wesley M. Plattner
  • Patent number: 10689121
    Abstract: An environmental control system assembly for an aircraft includes a heat exchanger assembly and a plenum. The heat exchanger assembly includes a first heat exchanger in fluid communication with a source of bleed air, a second heat exchanger disposed adjacent to the first, a third heat exchanger disposed adjacent to the second, and an end sheet. The first heat exchanger includes a first endwall, a first inlet header, a first outlet header, and a first endcap located on the first outlet header. The third heat exchanger includes a third endwall, a third inlet header connected to the third endwall, a third outlet header, and a third endcap located on the third inlet header. The end sheet includes the first, second, and third endwalls. The plenum fluidly connects the first outlet header of the first heat exchanger to the third inlet header of the third heat exchanger.
    Type: Grant
    Filed: January 24, 2018
    Date of Patent: June 23, 2020
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, Frederick Peacos, III
  • Patent number: 10681839
    Abstract: A cooling module including a first air inlet, a second air inlet, and an air discharge vent, the module having two check valves, each mounted in register with a respective inlet and arranged to allow air to pass towards the inside of the module and to oppose a flow of air in the opposite direction. An electronic unit including such a box.
    Type: Grant
    Filed: September 28, 2017
    Date of Patent: June 9, 2020
    Assignees: SAFRAN ELECTRICAL & POWER, SAFRAN ELECTRONICS & DEFENSE
    Inventors: François Guillot, Jean-Marc Blineau, Philippe Avignon, Serge Roques, Franck Albero
  • Patent number: 10633098
    Abstract: An environmental control system includes a turbo-compressor assembly and a ram air system. The turbo-compressor assembly includes a first turbine, a first compressor, and a first heat exchanger. The first heat exchanger has a first heat exchanger first side in fluid communication a first turbine outlet, a first heat exchanger second side, a first heat exchanger inlet in fluid communication a first compressor outlet, and a first heat exchanger outlet. The ram air system has a first ram air inlet in fluid communication with the first heat exchanger second side, and a second heat exchanger in fluid communication with the first ram air inlet.
    Type: Grant
    Filed: October 24, 2016
    Date of Patent: April 28, 2020
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Brian R. Shea
  • Patent number: 10569886
    Abstract: An aircraft air conditioning system includes an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which includes a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: February 25, 2020
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Frank Klimpel, Hans Brunswig, Steffen Golle, Ullrich Hesse, Enrico Klausner, Mario Raddatz
  • Patent number: 10571188
    Abstract: A proposed method for thermally assisted electric energy storage is intended for increase in round-trip efficiency through recovery of waste heat energy streams from the co-located power generation and industrial facilities, combustion of renewable or fossil fuels, or harnessing the renewable energy sources. In the charge operation mode, it is achieved by superheating and expansion of recirculating air stream in the liquid air energy storage with self-producing a part of power required for air liquefaction. In the discharge operation mode, it is attained through the repeated use of a stream of discharged air for production of an additional power in auxiliary discharge cycle.
    Type: Grant
    Filed: January 5, 2018
    Date of Patent: February 25, 2020
    Inventor: Stanislav Sinatov
  • Patent number: 10526967
    Abstract: A heat exchange unit (100) for hot gas recovery comprising, an inlet duct (34) to which a heat exchange duct (59) and a bypass duct (58) are connected, one being surrounded by the other, a heat exchange array (2) situated within the heat exchange duct (59) and a damper (50) arranged to direct the flow of gas through the unit (100), such that the damper (50) is situated within the inlet duct (34) and has two extreme positions, such that in a first extreme position the damper provides a first continuous surface and substantially seals one of the heat exchange and bypass ducts from the inlet duct and in the other extreme position the damper provides a second continuous surface and substantially seals the other of the ducts from the inlet duct.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: January 7, 2020
    Assignee: Heat Recovery Solutions Limited
    Inventor: Mark Wickham
  • Patent number: 10472073
    Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.
    Type: Grant
    Filed: December 30, 2016
    Date of Patent: November 12, 2019
    Assignee: Airbus Operations S.L.
    Inventor: Carlos Casado Montero
  • Patent number: 10435160
    Abstract: An aircraft air conditioning system comprises an ambient air supply line adapted to be flown through with ambient air, an ambient air cooling apparatus, which is connected to the ambient air supply line and is configured to cool the ambient air flowing through the ambient air supply line, an ambient air discharge line, which is connected to the ambient air cooling apparatus and is connectable to an aircraft cabin, in order to conduct ambient air cooled by the ambient air cooling apparatus into the aircraft cabin, a process air supply line adapted to be flown through with compressed process air, a process air cooling apparatus, which is connected to the process air supply line and is configured to cool the compressed process air flowing through the process air supply line, a process air discharge line, which is connected to the process air cooling apparatus and is connectable to the aircraft cabin, in order to conduct process air cooled by the process air cooling apparatus into the aircraft cabin, and a refrig
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: October 8, 2019
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Frank Klimpel
  • Patent number: 10429107
    Abstract: An environmental control system (ECS) includes an air cycle machine (ACM), a condenser downstream of the ACM, a reheater between the condenser and the ACM, a primary heat exchanger upstream of the reheater, a first regulated flow path between the condenser and a first environment outside of the ECS, a second regulated flow path between a second environment to be conditioned and the reheater, and a third regulated flow path between the primary heat exchanger and the reheater.
    Type: Grant
    Filed: January 12, 2017
    Date of Patent: October 1, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jan Ludvik, Martin Knob, Michael John Street
  • Patent number: 10377495
    Abstract: A ram air channel arrangement for ambient air supply into an aircraft comprises a ram air channel which has a ram air inlet channel and a ram air outlet channel arranged downstream of the ram air inlet channel and in fluid communication with the ram air inlet channel. The ram air channel arrangement further comprises a cabin exhaust air line which is adapted to have cabin exhaust air flow therethrough which has been removed from an aircraft cabin and which cabin exhaust air line is connected to the ram air inlet channel and is adapted to lead the cabin exhaust air into the ram air inlet channel.
    Type: Grant
    Filed: September 16, 2016
    Date of Patent: August 13, 2019
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Holger Bammann, Alexander Solntsev, Frank Klimpel, Alexandre Broquet
  • Patent number: 10266034
    Abstract: A system for providing heating and cooling to an aircraft has a single compressor for compressing and heating a fluid, a first zone and a second zone. The first zone has a first expansion valve without a condenser and a first heat exchanger removing heat from or adding heat to the first zone. The compressed fluid passes through the first zone and the first expansion valve. The second zone requires cooling and has a second expansion valve without a condenser and a second heat exchanger for removing heat from the zone. The compressed fluid passes through the second expansion valve after going through the first expansion valve and before passing through the second heat exchanger.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: April 23, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Michael J. Andres
  • Patent number: 10208675
    Abstract: A hybrid drive system driven by a gas turbine engine is disclosed. The hybrid drive system includes a planetary gear set, a first motor-generator, and a second motor-generator. The planetary gear set includes a first member, a second member, and a third member. The first member is operatively coupled to the second member and the third member. The first member is operatively coupled to and transmits power from a shaft of the gas turbine engine. The first motor-generator is drivingly coupled to the third member. The second motor-generator includes an output and is drivingly coupled to the second motor-generator by the second member and the third member. The hybrid drive system is configured to transfer the power from the shaft to the output of the second motor-generator.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: February 19, 2019
    Assignee: The Boeing Company
    Inventor: Steve Mackin
  • Patent number: 10184494
    Abstract: An Environmental Control System (ECS) for an aircraft includes a ram air system having a ram inlet and a ram outlet. The ECS includes a cabin air compressor motor, a diverter valve, and a dedicated outlet. The cabin air compressor motor has a motor inlet passage and a motor outlet passage with the motor inlet passage being coupled to the ram inlet. The diverter valve includes a first diverter inlet, a first diverter outlet, and a second diverter outlet. The first diverter inlet is coupled to the motor outlet passage. The dedicated outlet is connected to the first diverter outlet in a flight mode of operation of the aircraft and the ram outlet is connected to the second diverter outlet in a ground mode of operation of the aircraft.
    Type: Grant
    Filed: June 28, 2013
    Date of Patent: January 22, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Donald E. Army, Patrick McCord, Dominique P. Sautron, Thomas M. Zywiak
  • Patent number: 10137317
    Abstract: A system for delivering oxygen enriched air to a selected location on an aircraft may include: a gas separation system configured to output a flow of the oxygen enriched air; an environmental control system configured to output a flow of conditioned air; and/or first, second, and third ducts. The first duct may be configured to direct the flow of the oxygen enriched air to the third duct. The second duct may be configured to direct the flow of the conditioned air to the third duct. The conditioned air and the oxygen enriched air may be mixed in the third duct. The third duct may be configured to direct the mixed conditioned and oxygen enriched air to at least one dispensing station at the selected location that is configured to dispense the mixed conditioned and oxygen enriched air to users of the at least one dispensing station.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: November 27, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Andrew L. Armatorio, Richard J. Loftis, Colin W. Hart, Lisa C. Thomas, Kevin R. Price
  • Patent number: 10086946
    Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: October 2, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Thomas M. Zywiak, Gregory L. DeFrancesco, David E. Hall
  • Patent number: 10071807
    Abstract: A method for controlling an aircraft air conditioning system includes the steps of detecting an operating state of an air conditioning unit of the aircraft air conditioning system and controlling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit.
    Type: Grant
    Filed: June 12, 2013
    Date of Patent: September 11, 2018
    Assignee: Airbus Operations GMBH
    Inventor: Juergen Kelnhofer
  • Patent number: 10012146
    Abstract: A turbojet comprising a low-pressure compressor, a high-pressure compressor and a bleeding system configured to bleed air in the turbojet and to deliver the air to an air system. The bleeding system comprises a first air intake configured to bleed air at low pressure, a second air intake configured to bleed air at high pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to an outlet of the second valve, a high-pressure valve connected to the second air intake, a control valve connected to the air system, and a controller to control opening and closing of the valves depending on a pressure at the first air intake.
    Type: Grant
    Filed: February 16, 2015
    Date of Patent: July 3, 2018
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Olivier Pelagatti, Thomas Deguin, Ronan Bodet
  • Patent number: 9994323
    Abstract: A replacement system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The replacement system employs a subsystem to treat the medium from the low-pressure location of the engine before it is received by the inerting system.
    Type: Grant
    Filed: March 4, 2015
    Date of Patent: June 12, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Louis J. Bruno, Thomas M. Zywiak, Erin G. Kline, Christina W. Millot, Harold W Hipsky, Jr., Donald E. Army, Jr., Paul M. D'Orlando
  • Patent number: 9976684
    Abstract: A method for controlling the operation of an auxiliary power unit supplying an aircraft air conditioning system with compressed process air includes determining a heating or cooling requirement of an aircraft region to be air-conditioned, determining a desired value of at least one process air flow parameter in dependence on the determined heating or cooling requirement of the aircraft region to be air-conditioned, controlling the operation of the auxiliary power unit in dependence on the determined process air flow parameter desired value, acquiring an actual value of the at least one process air flow parameter, comparing the process air flow parameter actual value with the process air flow parameter desired value and controlling the operation of the auxiliary power unit in dependence on the result of the comparison of the process air flow parameter actual value with the process air flow parameter desired value.
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: May 22, 2018
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Jurgen Kelnhofer, Dariusz Krakowski
  • Patent number: 9971969
    Abstract: A method of predicting a fault in an air-conditioning pack of an aircraft is disclosed. The air-conditioning pack includes one or more sensors outputting data related to air-conditioning pack temperature, air-conditioning pack pressure, or air-conditioning pack valve or actuator positions. The method includes transmitting data from at least one of the sensors operably coupled to the air-conditioning pack, comparing the transmitted data to a predetermined threshold, and predicting a fault in the air-conditioning pack based thereon.
    Type: Grant
    Filed: February 21, 2014
    Date of Patent: May 15, 2018
    Assignee: Taleris Global LLP
    Inventors: Robert William Horabin, Julia Ann Howard, Frank Beaven
  • Patent number: 9957052
    Abstract: An Environmental Control System includes sensors, an air purification subsystem, and a controller in communication with the sensors and air purification subsystem. The sensors detect contaminants in outside air supplied through engine and APU bleeds or other air sources including ground supplies and electric compressors, contaminants in recirculated air, particulates in outside air, carbon dioxide in recirculated air, temperature in an environment, and pressure in an environment. These sensed parameters are compared against thresholds. Based on the comparisons, changes to the outside air and/or recirculated air are made.
    Type: Grant
    Filed: January 27, 2015
    Date of Patent: May 1, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard B. Fox, Bijan F. Hagh, Mike Koerner, Stephen Yates, Peter M. Michalakos, Russell W. Johnson
  • Patent number: 9885284
    Abstract: A turbojet comprising a high-pressure compressor with several compression stages in which the pressure rises in a direction of air flow, from a low pressure to a high pressure, passing through intermediate pressures, and a system to bleed air in the turbojet and deliver the air to an air system. The bleeding system comprises a first air intake to bleed air at low pressure, a second air intake to bleed air at an intermediate pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to the second valve outlet, a high-pressure valve connected to the second air intake, and a control valve connected to the air system, and a controller to control the opening and closing of the valves depending on the pressures at the first and second air intakes.
    Type: Grant
    Filed: February 16, 2015
    Date of Patent: February 6, 2018
    Assignee: Airbus Operations (SAS)
    Inventors: Olivier Pelagatti, Thomas Deguin, Ronan Bodet
  • Patent number: 9878794
    Abstract: A method for providing recirculation air to an environmental control system is provided. The method includes supplying via an inlet a flow of bleed air to the environmental control system at a first energy, providing the bleed air from the environmental control system at a second energy into a chamber, and providing the recirculation air to the environmental control system by recirculating the bleed air at a third energy from the chamber to an air cycle machine.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: January 30, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Louis J. Bruno
  • Patent number: 9856026
    Abstract: A system that comprises a nozzle arrangement is provided. The nozzle arrangement includes at least one nozzle configured to supply a medium at a nozzle flow rate to a fan of an air cycle machine. The nozzle flow rate provides a pneumatic power assist or a power augmentation to a fan of an air cycle machine. The power augmentation, in accordance with the nozzle flow rate, reduces a need for a flow across a turbine of the air cycle machine.
    Type: Grant
    Filed: April 16, 2015
    Date of Patent: January 2, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Harold W. Hipsky, Donald E. Army, Jr., Erin G. Kline, Louis J. Bruno, Christina W. Millot
  • Patent number: 9849990
    Abstract: 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.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: December 26, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Louis J. Bruno
  • Patent number: 9840333
    Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air directly flows from a source to mix with recirculated air downstream of a compressor of the air cycle machine in accordance with a high pressure mode or a recirculation chilling mode. The system and method can also utilize the recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: December 12, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Louis J. Bruno, Paul M. D'Orlando, Donald E. Army, Jr., Thomas M. Zywiak, Harold W. Hipsky, Erin G. Kline, Richard Rusich, John M. Maljanian, Jr., Eric Surawski
  • Patent number: 9809314
    Abstract: An aircraft air conditioning system comprises a process air line configured to supply compressed process air provided by a process air source to an air conditioning unit of the aircraft air conditioning system and a trim air line branching off from the process air line upstream of the air conditioning unit and being configured such that trim air flows through the trim air line, the trim air having been branched off from the compressed process air flowing through the process air line. A compressor is arranged in the trim air line and is configured to compress the trim air flowing through the trim air line. A turbine of the aircraft air conditioning system is configured to drive the compressor. A cabin exhaust air line is configured to supply cabin exhaust air discharged from an aircraft cabin to the turbine for driving the turbine.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: November 7, 2017
    Assignees: Airbus Operations S.L., Airbus Operations GmbH
    Inventors: Holger Bammann, Frank Klimpel, Dariusz Krakowski, Anton Mendez-Diaz
  • Patent number: 9783307
    Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air directly flows from a source to either a compressor of the air cycle machine or the at least one heat exchanger in accordance with a high pressure, low pressure, or pressure boost operation mode. The system and method also can also utilize recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: October 10, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Louis J. Bruno, Eric Surawski, Donald E. Army, Jr., Thomas M. Zywiak, Harold W. Hipsky, Erin G. Kline, Richard Rusich, John M. Maljanian, Jr., Paul M. D'Orlando
  • Patent number: 9752834
    Abstract: A cooling system cools at least one heat producing device provided in a unit of transport, and a method is provided for cooling at least one heat producing device provided in a unit of transport. The cooling system includes at least one first liquid circuit and at least one first heat exchanger assigned to the first liquid circuit, the first liquid circuit, for cooling the at least one first heat producing device, being configured to absorb heat of the first heat producing device via a cooling liquid circulating in the first liquid circuit and dissipate heat to the first heat exchanger, the first heat exchanger being coupled in such a manner to a first air-guiding system available on board the unit of transport, that exhaust air extracted from the first air-guiding system can be supplied to the first heat exchanger in order to recool the cooling liquid.
    Type: Grant
    Filed: March 28, 2013
    Date of Patent: September 5, 2017
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Robert Schöll, Cherif Terzi
  • Patent number: 9738389
    Abstract: A cooling system for use with a galley monument having at least one galley compartment includes a heat exchanger supplying cooled air to at least one galley compartment. An airflow supply and return system has a supply duct that couples the heat exchanger in flow communication with the at least one galley compartment. A diverter mechanism is positioned at least partially within the supply duct for controlling flow of the cooled air. The diverter mechanism is movable between a first position in which the cooled air flows from the heat exchanger through the supply duct to the at least one galley compartment and a second position in which at least a portion of the cooled air from the heat exchanger is discharged from the supply duct to the passenger compartment of the aircraft.
    Type: Grant
    Filed: September 18, 2014
    Date of Patent: August 22, 2017
    Assignee: The Boeing Company
    Inventors: Steven George Mackin, Francesco Balestra
  • Patent number: 9650967
    Abstract: A method for decreasing a throttle setting at which a gas turbine-powered aircraft must switch from low-pressure bleed air to a high-pressure bleed air. The method includes flowing low-pressure bleed air from a compressor at a first pressure. A first portion of the low-pressure bleed air is directed to an air-to-air heat exchanger and cooled in the air-to-air heat exchanger. The first portion of the low-pressure bleed air is flowed from the air-to air heat exchanger into a cooled bleed air line. A second portion of the low-pressure bleed air is directed to a low-pressure bypass line. The second portion of the low-pressure bleed air is flowed from the low-pressure bypass line into the cooled bleed air line upstream of an environmental control system.
    Type: Grant
    Filed: May 15, 2015
    Date of Patent: May 16, 2017
    Assignee: Hamiilton Sundstrand Corporation
    Inventor: Gregory L. DeFrancesco
  • Patent number: 9623974
    Abstract: An environmental control system including a turbomachine assembly having a shaft, motor, turbine and compressor, the compressor outputting a compressed air stream, a first valve that splits the compressed air stream into first and second compressed air streams, a heat exchanger to cool the first compressed air stream and output a cooled air stream, a second valve positioned to receive the cooled air stream and split the cooled air stream into first and second cooled air streams, wherein the first cooled stream is expanded in the turbine to produce an expanded air stream that is combined with the second compressed air stream and the second cooled air stream to provide a combined air stream having a temperature and a flow rate, and a controller that communicates control signals to the compressor, motor and first and second valves to control the temperature and flow rate of the combined air stream.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: April 18, 2017
    Assignee: The Boeing Company
    Inventor: Andrew T. Johnson
  • Patent number: 9617005
    Abstract: A system and method of altering the air conditioning system in an aircraft so that the air conditioning system is electrically powered rather than engine powered. The aircraft is rid of the air conditioning components that are dedicated to the engine powered system. A new electric compressor, evaporator and condenser blower assembly are then installed. Heat exchanger units are installed in the areas of the aircraft that are to be cooled. The new air conditioning system has two circulatory loops. In a refrigerant loop, refrigerant is circulated between the electric compressor, evaporator and condenser. This cools the evaporator. The evaporator is then used to cool circulating liquid coolant. The coolant is circulated to the heat exchange units.
    Type: Grant
    Filed: July 31, 2013
    Date of Patent: April 11, 2017
    Inventor: Peter Schiff
  • Patent number: 9611752
    Abstract: A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 4, 2017
    Assignee: General Electric Company
    Inventors: Steven William Tillery, David August Snider
  • Patent number: 9580180
    Abstract: 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.
    Type: Grant
    Filed: March 7, 2014
    Date of Patent: February 28, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Michel A. Jonqueres, Roy Araki
  • Patent number: 9493243
    Abstract: Embodiments relate to adjusting cabin pressure based on ambient conditions to achieve a target aircraft inflow. An aspect includes receiving a number of occupants on an aircraft. The ambient conditions on the aircraft are monitored and an occupant threshold limit is determined for the aircraft based on the ambient conditions. If it is determined that the number of occupants exceeds the occupant threshold limit, the cabin pressure is reduced in the aircraft according to embodiments. The cabin pressure in the aircraft is reset in response to the occupant threshold limit being increased due to changing ambient conditions.
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: November 15, 2016
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Brendon W. Lewis, Young K. Park, Allison Mainelli, Cuiye Chen
  • Patent number: 9457908
    Abstract: An nitrogen generation system for an aircraft is provided. The system includes a RAM air circuit, a motor driven compressor (MDC) having a rotor, a stator to drive rotor rotation and a compressor rotatably coupled to the rotor and a cooling system. The cooling system directs cooling air from the RAM air circuit to an inlet of the compressor and an alternative low pressure environment such that the cooling air removes heat from the stator.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: October 4, 2016
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Eric Surawski