| Patent application number | Description | Published |
|---|
| 20120138737 | AIRCRAFT POWER DISTRIBUTION ARCHITECTURE - An aircraft power distribution architecture including an Auxiliary Power Unit, a power distributor, and an electric generator distributes power to multiple aircraft systems. | 06-07-2012 |
| 20130118190 | TURBO AIR COMPRESSOR - A method for operating an air-conditioning system for an aircraft including receiving an available power level from a control system of the aircraft, forwarding air from a first compressed air source to an aircraft cabin and forwarding air from a second compressed air source to the aircraft cabin if the available power level exceeds a threshold value. | 05-16-2013 |
| 20130118191 | TURBO AIR COMPRESSOR WITH PRESSURE RECOVERY - 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. | 05-16-2013 |
| 20130230409 | ENVIRONMENTAL CONTROL SYSTEM HAVING PARALLEL COMPRESSORS AND METHOD OF CONTROLLABLY OPERATING - An environmental control system having parallel compressors includes a first compressor driven by a first motor, the first compressor being operable for fluidly directing a first flow at a first flow rate through the first compressor. Also included is a second compressor driven by a second motor, the second compressor being operable for fluidly directing a second flow at a second flow rate through the second compressor. Further included is a monitoring component configured to compare the first flow rate to the second flow rate. | 09-05-2013 |
| 20140083647 | PRIMARY HEAT EXCHANGER CROSSOVER BYPASS MANIFOLD - An aircraft is provided including an environmental control system (ECS) having a first ECS pack and a second ECS pack. A duct couples the first ECS pack to the second ECS pack. The duct includes a first bypass conduit configured to form a bypass around a first primary heat exchanger of the first ECS pack. A second bypass conduit configured to form a bypass around a second primary heat exchanger of the second ECS pack. The duct includes a crossover conduit extending between the first bypass conduit and the second bypass conduit. The duct includes a plurality of valves for selectively controlling a flow between the first bypass conduit and the second bypass conduit. | 03-27-2014 |
| 20140299296 | GALLEY COOLING - A cooling module of a galley chiller system is provided including an internal chamber. A heat exchanger assembly has air and a liquid coolant flowing there through. The heat exchanger assembly includes a first heat exchanger core and a second heat exchanger core. The first heat exchanger core and the second heat exchanger core are arranged generally sequentially within the internal chamber. Heat transfer within the first heat exchanger core is limited such that a temperature of the air in the first heat exchanger core remains above freezing. | 10-09-2014 |
| 20140305610 | METHOD OF MONITORING A HEAT EXCHANGER ARRANGEMENT AND HEAT EXCHANGER MONITORING SYSTEM - A method of monitoring a heat exchanger arrangement is provided. The method includes detecting a rotational speed of a ram air fan configured to draw air through the heat exchanger arrangement. The method also includes detecting a power input from a motor to the ram air fan to maintain a commanded rotational speed of the ram air fan. The method further includes comparing the power input detected to a predetermined power limit for the commanded rotational speed. The method yet further includes decreasing the rotational speed of the ram air fan with a controller if the power input detected exceeds the predetermined power limit. | 10-16-2014 |
| 20140326005 | Galley Cooling Heat Exchanger Defrost Mechanism - A galley chiller system configured to operate in a defrost mode is provided including a cooling module, a heating element, and a fan module. The cooling module is configured to provide cool air to at least one galley monument. The cooling module includes a heat exchanger configured to have both air and a liquid coolant flow there through in a heat transfer relationship. The heating element is arranged generally adjacent a coolant inlet of the heat exchanger. The fan module is configured to circulate warm return air from the at least galley monument to the cooling module. When the galley chiller system is in the defrost mode, only liquid coolant flows through the heat exchanger. The liquid coolant is locally heated by the heating element. | 11-06-2014 |
| 20140345991 | ACTIVE AIRCRAFT BRAKE COOLING SYSTEM - An active aircraft brake cooling system includes an air intake and conditioning system having an outlet portion that is fluidically exposed to a landing gear bay. | 11-27-2014 |
| 20150059356 | AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM SELECTIVELY POWERED BY THREE BLEED PORTS - A bleed air supply system configured to supply bleed air from an engine to an environmental control system (ECS) pack is provided including a high pressure port configured to bleed air from a high spool of the engine. An intermediate pressure port is configured to bleed air from the high spool of the engine. The bleed air at the intermediate pressure port has a pressure less than the bleed air at the high pressure port. A precooler is fluidly coupled to the ECS pack, the high pressure port and the intermediate pressure port. Bleed air from the high pressure port and the intermediate pressure port is conditioned in the precooler before being provided to the ECS pack. A low pressure port is configured to bleed air from a low spool of the engine. The bleed air from the low pressure port bypasses the precooler and is supplied directly to the ECS pack. | 03-05-2015 |
| 20150059397 | METHOD OF OPERATING A MULTI-PACK ENVIROMENTAL CONTROL SYSTEM - 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. | 03-05-2015 |
