Abstract: 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.

Abstract: An aircraft landing gear wheel-drive system includes a first wheel drive unit for driving a first landing gear wheel of the aircraft and a second wheel drive unit for driving a second landing gear wheel of the aircraft. The first wheel drive unit has a first range of torque to speed (T/S) ratios. The second wheel drive unit has a second range of T/S ratios. The first range of T/S ratios is greater than the second range of T/S ratios.

Abstract: An aircraft landing gear wheel-drive system includes a first wheel drive unit for driving a first landing gear wheel of the aircraft and a second wheel drive unit for driving a second landing gear wheel of the aircraft. The first wheel drive unit has a first range of torque to speed (T/S) ratios. The second wheel drive unit has a second range of T/S ratios. The first range of T/S ratios is greater than the second range of T/S ratios.

Abstract: An in-line centrifuge-separator pump includes a shaft, a shroud, and a plurality of spaced-apart corrugated, and concentrically disposed separator structures. The shaft is adapted to receive a drive torque and is configured, upon receipt thereof, to rotate. The shroud is spaced apart from and is coupled to the shaft to be rotated thereby. The separator structures are at least partially disposed within the shroud and are coupled to both the shroud and the shaft to simultaneously rotate therewith. Each separator structure has a plurality of perforations formed therein.

Abstract: A fuel cooled cooling air heat exchanger includes a fuel injector and an airflow body. The fuel injector has a fuel flow passage formed therein that includes a fuel inlet port and a fuel outlet port. The airflow body is coupled to and surrounds at least a portion of the fuel injector. The airflow body has an inner surface that is spaced apart from the fuel injector to define an airflow passage between the airflow body and the fuel injector, and the airflow passage includes an air inlet port and an air outlet port.

Abstract: A fuel flow control system includes a centrifugal pump, a gas inlet valve, and a control. The centrifugal pump has a fuel inlet, a gas inlet, and an outlet. The gas inlet valve is disposed upstream of the gas inlet and is responsive to valve position commands to move between a closed position, in which inert gas is prevented from flowing into the gas inlet, and a plurality of open positions, in which inert gas may flow into the gas inlet. The control is coupled to the gas inlet valve and is configured to supply the valve position commands to the gas inlet valve to command the gas inlet valve to selectively move to the closed position, such that the centrifugal pump is configured to operate as a fuel pump, or any open position, such that the centrifugal pump is configured to operate as a fuel-gas mixer.

Abstract: An aircraft fuel deoxygenation system includes a boost pump, a contactor-separator, and a centrifuge-separator pump. The boost pump is adapted to receive fuel from a fuel source and inert gas from an inert gas source, and is configured to mix the fuel and inert gas and supply a fuel/gas mixture. The contactor-separator is coupled to receive the fuel/gas mixture and is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel with entrained purge gas and separated purge gas. The centrifuge-separator pump is coupled to receive the deoxygenated fuel with entrained purge gas and is configured to separate and remove the entrained purge gas from the deoxygenated fuel and supply the deoxygenated fuel and additional purge gas.

Abstract: Techniques for performing location logging and location and time based filtering are described. In one design of location logging, a terminal periodically determines its location, e.g., during its paging slots. The terminal determines whether there is a change in its location and stores its location if a change in location is detected. In one design of location and time based filtering, the terminal obtains a location and time criterion with a target area and a time period. The terminal determines its location during the time period, e.g., based on the location log. The terminal evaluates the location and time criterion based on the target area and its location during the time period, e.g., based on at least one sector ID for the target area and one or more sector IDs for its location. The terminal determines whether to download and/or present broadcast information based on the result of the evaluation.

Abstract: 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.

Abstract: The resilient delta ring seal for use in a seat for a ball valve is held in the seat having an annular opening for receiving and holding the delta ring seal. An apex of the seal is pointed radially inward toward the ball valve and a base of the seal is orientated radially away from the ball valve. The seal base is wider than the apex. The seal is placed in the seat apposite an annular resin insert having a surface disposed toward the ball valve. The seal apex is truncated obliquely to define a substantially flat apical surface that extends beyond the opening toward the ball valve and terminates at the resin insert.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present invention is a resilient delta ring seal for use in a seat for a ball valve. The seat has an annular opening for receiving and holding the delta ring seal therein so that an apex of the seal is pointed radially inward toward the ball valve and a base of the seal is orientated radially away from the ball valve. The seal base is wider than the apex and the apex protrudes beyond the opening and toward the valve. The seal apex is truncated to level the apex while the seal still extends beyond the opening and toward the valve.

Abstract: 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.

Abstract: 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.

Abstract: 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.