Abstract: Natural gas dissolved in saline ground water can be recovered for use. The process includes the pumping of water production wells, separation of gas and water at the surface, gas compression, desalination of ground water, and injection of excess water into disposal wells. A definitive test of the process was completed on Jan. 9 and 10, 2013, at Gill Ranch Gas Field, California: volumes of recovered gas were equal to predictions based on methane solubility. Analyses of the gas showed that it was equal in heat value (about 975 BTU per cubic foot) to dry gas produced from the same field. Saline water recovered during the full scale test was returned to the same aquifer from which it was produced.

Abstract: Automated systems and methods of extracting gas from groundwater aquifers are provided.

Abstract: One undeveloped alternative fuel is methane dissolved in ground water. Equipment for extracting methane from ground water is readily available. This Application presents a process to produce and use dissolved natural gas in the United States. The process includes the use of production wells, pumps, gas/water separators, compressors, low pressure gathering lines, and water disposal wells. Dissolved methane is present in virtually every basin now known to produce oil and dry gas. The Great Valley of California alone contains undeveloped dissolved methane resources of about 1,200 trillion cubic feet (TCF). Dry gas production in 150 years was about 10 TCF. The first full scale test of the extraction process was completed on Jul. 7-8, 2010 in California. Laboratory analyses of the gas produced showed that it was equal in heat value (about 940 to 975 BTU per cubic foot) to dry gas produced from the same field.

Abstract: Methods and apparatus are provided for monitoring an aircraft accessory. The apparatus comprises a processor associated with said aircraft accessory, a transducer coupled to said processor and operable to produce parametric data relating to said aircraft accessory and a memory coupled to said processor having baseline parametric data residing therein, wherein said baseline parametric data comprises the parametric data obtained during an acceptance test procedure. The method comprises installing a transducer configured to produce parametric data relating to said aircraft accessory, coupling said transducer to a processor associated with said aircraft accessory, coupling said processor to a memory associated with said aircraft accessory, recording baseline parametric data relating to said aircraft accessory in said memory during an acceptance test procedure for said aircraft accessory.

Abstract: A passive ATS lubrication system is provided that includes a starter housing, a receptacle and two valves. The starter housing is adapted to couple to a gearbox assembly and includes a supply opening and an exhaust opening that are each configured to provide fluid communication between the gearbox assembly and the starter housing. The receptacle is coupled to the starter housing proximate the supply opening to thereby define a reservoir. The first valve is disposed within the reservoir and configured to open or close the supply opening in response to a pressure differential between the starter housing and the gearbox assembly. The second valve is coupled to the starter housing proximate to the exhaust opening and configured to open or close the exhaust opening in response to the pressure differential between the starter housing and the gearbox assembly.

Abstract: A passive ATS lubrication system is provided that includes a starter housing, a receptacle and two valves. The starter housing is adapted to couple to a gearbox assembly and includes a supply opening and an exhaust opening that are each configured to provide fluid communication between the gearbox assembly and the starter housing. The receptacle is coupled to the starter housing proximate the supply opening to thereby define a reservoir. The first valve is disposed within the reservoir and configured to open or close the supply opening in response to a pressure differential between the starter housing and the gearbox assembly. The second valve is coupled to the starter housing proximate to the exhaust opening and configured to open or close the exhaust opening in response to the pressure differential between the starter housing and the gearbox assembly.

Abstract: Methods and apparatus are provided for monitoring an aircraft accessory. The apparatus comprises a processor associated with said aircraft accessory, a transducer coupled to said processor and operable to produce parametric data relating to said aircraft accessory and a memory coupled to said processor having baseline parametric data residing therein, wherein said baseline parametric data comprises the parametric data obtained during an acceptance test procedure. The method comprises installing a transducer configured to produce parametric data relating to said aircraft accessory, coupling said transducer to a processor associated with said aircraft accessory, coupling said processor to a memory associated with said aircraft accessory, recording baseline parametric data relating to said aircraft accessory in said memory during an acceptance test procedure for said aircraft accessory.

Abstract: One or more particle arrestors are mounted in a curved radial flow portion of a gas turbine starter annular flow passage, between a fluid inlet and a fluid outlet. The one or more arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the one or more arrestor rings substantially inhibit relatively high energy particles from exiting the turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Abstract: One or more particle arrestors are mounted in a curved radial flow portion of a gas turbine starter annular flow passage, between a fluid inlet and a fluid outlet. The one or more arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the one or more arrestor rings substantially inhibit relatively high energy particles from exiting the turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Abstract: One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the arrestor rings substantially inhibit relatively high energy particles from exiting the gas turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

Abstract: A decoupling apparatus for disconnecting an engine starter from an engine includes a first rotatable decoupler shaft, having a first clutch jaw, coaxially mounted with respect to a second rotatable decoupler shaft having a second clutch jaw. The two shafts can translate relative to each other from a first position in which the first and second clutch jaws are engaged to a second position in which the jaws are disengaged. A torsional shear pin with a unitary shaft has a first end in contact with a resilient member and a second end attached to the first decoupler shaft, thereby urging the first and second decoupler shafts into the first position. The torsional shear pin is frangible in response to angular movement of the first decoupler shaft relative to the second decoupler shaft to release the axially compressive force, thereby permitting the first and second decoupler shafts to move into the second position.

Abstract: An improved oil seal is provided for sealing passage of rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a slinger rotor mounted on the shaft for rotation therewith. The slinger rotor includes a radially outwardly extending slinger ring with radially open slinger ports formed therein, in combination with an axially projecting centrifuge sleeve defining an internal tapered centrifuge surface disposed in close running clearance with an axially projecting cylindrical wall segment on the end wall. During shaft rotation, the centrifuge surface pumps oil in a direction away from the end wall to the slinger ring for discharge through the slinger ports to the interior of the bearing housing.