Patent application number | Description | Published |
20100064701 | HYBRID ENVIRONMENTAL CONDITIONING SYSTEM - An environmental conditioning system has a compressor for compressor air in an air flow path. A turbine drives the compressor and is coupled to the compressor. An evaporator is in communication with the compressor. The evaporator is configured to cool air from the compressor. | 03-18-2010 |
20110108239 | HYBRID COOLING SYSTEM FOR AIRCRAFT APPLICATIONS - An aircraft cooling system includes a refrigerant cycle including a first heat exchanger. A liquid cycle passes a liquid through the first heat exchanger, at which it is cooled by a refrigerant in the refrigerant cycle. An air cycle compresses air and delivers the compressed air into a second heat exchanger. The liquid passes through the second heat exchanger at a location downstream of the first heat exchanger. The liquid cools the air in the second heat exchanger. Air downstream of the second heat exchanger passes to be utilized by a use on an aircraft. | 05-12-2011 |
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 |
20120297780 | ACTIVE FUEL TEMPERATURE CONTROL - A system for managing fuel temperature in an engine includes a source of hot pressurized air and a turbine for converting hot pressurized air into cool expanded air. The system further includes a fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel tank, and a first heat exchanger located on the fuel conduit. The first heat exchanger places the cool expanded air from the turbine in a heat exchange relationship with the fuel, thereby cooling the fuel. | 11-29-2012 |
20130036730 | HYBRID POWER SYSTEM ARCHITECTURE FOR AN AIRCRAFT - A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft. | 02-14-2013 |
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 |
20130306790 | HYBRID POWER SYSTEM ARCHITECTURE FOR AN AIRCRAFT - A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft. | 11-21-2013 |
20140196469 | LOW PRESSURE COMPRESSOR BLEED EXIT FOR AN AIRCRAFT PRESSURIZATION SYSTEM - An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level. | 07-17-2014 |
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 |
20150065023 | INTERCOMPRESSOR BLEED TURBO COMPRESSOR - A bleed system that comprises a bleed inter-compressor fluidly coupled to a low pressure port of the bleed system and configured to utilize a portion of a medium received from the low pressure port to increase the pressure of another portion of that medium. A turbine of the bleed inter-compressor is coupled to a compressor of the bleed inter-compressor and drives the compressor via a shaft, so as to regulate the pressure of the medium. | 03-05-2015 |
20150065025 | ENVIRONMENTAL CONTROL SYSTEM INCLUDING A COMPRESSING DEVICE - A compressing device added to a cabin air conditioning system to increase a pressure of air in the cabin air conditioning system itself and, thus, allow for lower pressure air to be bled from the engine. For instance, the compressing device allows air to be bled from a low, rather than a high, pressure locations of the engine. | 03-05-2015 |