Patent application number | Description | Published |
20130145744 | SYSTEM FOR DIRECTING AIR FLOW TO A PLURALITY OF PLENA - A system for directing air flow to separate plena of a compartment that is defined at least by a compartment wall includes a NACA scoop, and a Pitot scoop. The NACA scoop is formed in the compartment wall, and includes two side walls, a bottom wall, and an entrance lip that is defined by the compartment wall and is spaced apart from the bottom wall to form a NACA scoop air inlet. The Pitot scoop is longitudinally aligned with the NACA scoop, includes a Pitot scoop air inlet, a Pitot scoop air outlet, and a Pitot scoop flow passage. | 06-13-2013 |
20130186102 | GAS TURBINE ENGINE IN-BOARD COOLED COOLING AIR SYSTEM - A system for supplying turbine cooling air flow includes a turbofan engine, a heat exchanger, and a door. The turbofan engine includes an engine case that has an inner volume within which at least a gas turbine engine is mounted, and a bypass flow passage that is defined by an outer fan duct and an inner fan duct and that is configured to direct fan air flow therethrough. The heat exchanger is disposed within the turbofan engine, is coupled to receive fluid and cooling air from the bypass flow passage, and is configured to transfer heat between fluid and the cooling air. The door is movably mounted in the turbofan engine and is movable between a closed position, in which the cooling air will not flow through the heat exchanger, and an open position, in which the cooling air may flow through the heat exchanger. | 07-25-2013 |
20130236299 | TUBULAR HEAT EXCHANGE SYSTEMS - A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion. | 09-12-2013 |
20130247587 | BI-METALLIC ACTUATOR FOR SELECTIVELY CONTROLLING AIR FLOW BETWEEN PLENA IN A GAS TURBINE ENGINE - A system for selectively supplying air between separate plena of a gas turbine engine includes a gas turbine engine, a door, and a bi-metallic door actuator. The gas turbine engine comprises at least a first plenum and a second plenum, and has an opening between the first plenum and the second plenum. The is door mounted in the gas turbine engine and is movable between a closed position, in which air is prevented from flowing through the opening, and an open position, in which air may flow though the opening. The bi-metallic door actuator is coupled to the door and is configured to selectively move the door between the closed position and the open position. | 09-26-2013 |
20150023638 | LOW LOSS PASSIVE OPTICAL HUB FOR USE IN THE PLASTIC OPTICAL FIBER NETWORKS - A node for a low loss passive optical hub is provided. The low loss passive optical hub includes a 1:N-split fiber and a plastic-optical fiber. The 1:N-split fiber has a fused-fractional end and N second-fractional ends. The 1:N-split fiber is formed from N sub-fibers. The N sub-fibers each have a first-fractional end and a second-fractional end. The N first-fractional ends are fused to form the fused-fractional end. The plastic-optical fiber has a first end and a second end. The first end of the plastic-optical fiber is optically coupled to the fused-fractional end of the 1:N-split fiber. | 01-22-2015 |
20150314229 | FUEL DEOXYGENATION AND FUEL TANK INERTING SYSTEM AND METHOD - An aircraft fuel deoxygenation and tank inerting system includes an inert gas source, a fuel deoxygenation system, and an air/fuel heat exchanger. The inert gas source is configured to supply inert gas having an oxygen concentration of less than 3%. The fuel deoxygenation system is adapted to receive fuel from a fuel source and the inert gas from the inert gas source. The fuel deoxygenation system is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas. The air/fuel heat exchanger is adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system. The air/fuel heat exchanger is configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel. | 11-05-2015 |
20160129372 | FUEL DEOXYGENATION SYSTEM CONTACTOR-SEPARATOR - A fuel deoxygenation system contactor-separator includes a fuel-gas mixture inlet section, a fuel outlet section, a gas outlet, a spiral contactor-separator, and a valve element. The fuel-gas mixture inlet section has a fuel-gas mixture inlet port. The fuel outlet section has a fuel outlet port. The gas outlet section has a gas outlet port. The spiral contactor-separator conduit has an inner wall and an outer wall that defines a spiral contactor-separator flow passage. The spiral contactor-separator conduit is coupled to, and is in fluid communication with, the fuel-gas mixture inlet section, the fuel outlet section, and the gas outlet section. The valve element is disposed between the fuel outlet port and the gas outlet port and is movable between a first position and a second position. | 05-12-2016 |