Abstract: A lube system is provided and includes an air-oil tank including a deaerator configured to remove a first quantity of oil from a first air-oil supply to generate a second air-oil supply having a second quantity of oil, which is smaller than the first quantity of oil, the air oil tank being configured to output the second air-oil supply to an air vent line, a de-oiler disposed along the air vent line and configured to remove from the second air-oil supply oil mist including oil droplets of a minimum size and a pressure regulating valve (PRV) disposed along the air vent line between the air-oil tank and the de-oiler to regulate fluid pressures within the air-oil tank, the PRV being configured to encourage formation of the oil droplets of at least the minimum size.

Abstract: A deaerator includes a case defining a vortex chamber and a fluid inlet for allowing a mixture of lubricating liquid and air to pass through the case into the vortex chamber. An air outlet allows air flow out of the deaerator, and a liquid outlet allows lubricating liquid flow out of the deaerator. A porous diffuser is positioned proximate the liquid outlet for slowing the flow of lubricating liquid.

Abstract: A deaerator includes a case defining a vortex chamber and a fluid inlet for allowing a mixture of lubricating liquid and air to pass through the case into the vortex chamber. An air outlet allows air flow out of the deaerator, and a liquid outlet allows lubricating liquid flow out of the deaerator. A porous diffuser is positioned proximate the liquid outlet for slowing the flow of lubricating liquid.

Abstract: A rotator drive connection for a gas turbine engine accessory box has a shaft connected to be driven by a main shaft in a gas turbine engine through a gear train. A first drive connection allows selective drive of the shaft. A biased drive member includes a second drive connection selectively brought into contact with the first drive connection to allow rotation of the main shaft. The biased drive member biases the second drive connection out of contact with the first drive connection. A gas turbine engine accessory box and a method of borescopic inspection are also disclosed and claimed.

Abstract: An apparatus is provided and includes a rotatable shaft on which a first bevel gearbox is disposed, a layshaft on which a second bevel gearbox is disposed, the first and second bevel gearboxes being coupled to transmit shaft rotation to the layshaft, an accessory gearbox to which the layshaft and one or more accessories are coupled and a generator operably disposed on the layshaft between the second bevel gearbox and the accessory gearbox.

Abstract: A gearbox that includes an inlet configured to receive a mixture of air and oil from an external source and a deoiler. The deoiler includes a shaft including an outlet passage formed on an inner portion of the shaft, a separator unit coupled to and surrounding a portion of the shaft and including an inlet port, and a synchronizer including one or more blades and that is coupled to the shaft proximate the inlet port.

Abstract: A gearbox includes an outer housing including manual rotation access passage and a manual rotation shaft coupled to a spool of an engine to rotate the engine spool. The gearbox also includes coupled to the outer housing that includes a flapper valve that, in a closed position, prevents a lubricant from escaping from the outer housing via the manual rotation access passage.

Abstract: A breather assembly for use with a gas turbine engine includes a static housing for accepting a fluidic mixture of substances, a rotatable separator having one or more fluid inlets and arranged about an axis of rotation, an exhaust outlet defined in the housing and positioned coaxially with the rotatable separator to accept fluidic exhaust from the rotatable separator, and a static diffuser supported by the housing at or near the exhaust outlet downstream from the rotatable separator. A portion of the static diffuser extends within the rotatable separator. The static diffuser includes a flow-straightening structure configured to reduce vortex flows in fluid flows passing through the exhaust outlet.

Abstract: An air turbine starter and accessory gearbox assembly, the accessory gearbox includes a gear shaft and the air turbine starter includes an output shaft and a clutch assembly. The output shaft extends from the accessory gearbox and is coupled to and supported by the gear shaft. The accessory gearbox is adapted to receive the air turbine starter such that the clutch assembly and the output shaft are disposed within a casing of the accessory gearbox when the air turbine starter is mounted to the accessory gearbox.

Abstract: A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing.

Abstract: An accessory gearbox system for a gas turbine engine includes an accessory compressor mounted to a gearbox housing. The gearbox housing defines a seal air core, and the gearbox housing communicates a seal airflow through the seal air core.

Abstract: A bootstrap accumulator system includes an actuator cylinder that drives an accumulator piston through a multiple of nested actuator sleeves, comprising a multistage actuator cylinder.

Abstract: A rotator drive connection for a gas turbine engine accessory box has a shaft connected to be driven by a main shaft in a gas turbine engine through a gear train. A first drive connection allows selective drive of the shaft. A biased drive member includes a second drive connection selectively brought into contact with the first drive connection to allow rotation of the main shaft. The biased drive member biases the second drive connection out of contact with the first drive connection. A gas turbine engine accessory box and a method of borescopic inspection are also disclosed and claimed.

Abstract: An accessory gearbox assembly for an aircraft includes one or more intermeshed gears disposed in a gearbox housing and configured to transfer rotational energy from an engine core. An accessory component has a spur gear located at least partially in an accessory housing. The spur gear is meshed with a gear of the one or more gears thereby transferring rotational energy from the gearbox to the accessory component. A method for providing rotational energy to an accessory component at an accessory gearbox includes providing rotational energy to one or more intermeshed gears of an accessory gearbox and locating an accessory component at the accessory gearbox. The accessory component includes a spur gear disposed at least partially in an accessory housing. The spur gear is meshed with a gear of the one or more gears and rotational energy is transferred to the accessory component via the spur gear.

Abstract: An apparatus is provided and includes a rotatable shaft on which a first bevel gearbox is disposed, a layshaft on which a second bevel gearbox is disposed, the first and second bevel gearboxes being coupled to transmit shaft rotation to the layshaft, an accessory gearbox to which the layshaft and one or more accessories are coupled and a generator operably disposed on the layshaft between the second bevel gearbox and the accessory gearbox.

Abstract: A gearbox for an aircraft has a first side wall, a second side wall, a gear train, and an aircraft accessory. The aircraft accessory has a housing, an input attaching to the gear train for receiving rotative input from the gear train, and a first shaft for selectively coupling and uncoupling the gear train from the input. The housing attaches to the first side wall and the second side wall.

Abstract: A seal body for use to seal on a rotating shaft has a generally cylindrical central bore for receiving a shaft, and is formed of an open-celled material. In addition, a shaft and seal combination and a gear box are disclosed and claimed.

Abstract: An accessory gearbox system for a gas turbine engine includes a accessory compressor mounted to a gearbox housing.

Abstract: This inventive provides a multiple level cache structure and multiple level caching method that distributes I/O processing loads including caching operations between processors to provide higher performance I/O processing, especially in a server environment. A method of achieving optimal data throughput by taking full advantage of multiple processing resources is disclosed. A method for managing the allocation of the data caches to optimize the host access time and parity generation is disclosed. A cache allocation for RAID stripes guaranteed to provide fast access times for the XOR engine by ensuring that all cache lines are allocated from the same cache level is disclosed. Allocation of cache lines for RAID levels which do not require parity generation and are allocated in such manner as to maximize utilization of the memory bandwidth is disclosed.

Abstract: An improved single engine military aircraft is provided through the use of an improved secondary power system which incorporates an additional accessory drive, and utilizes improved multi-path system architecture together with optimal distribution of accessories to thereby enhance partial operational flexibility of the secondary power system in both normal and partial failure modes of operation. The additional accessory drive also provides an aircraft in which the engine can be removed with minimal disruption of the EMAD or AMAD and accessories mounted thereon to thereby enhance both initial manufacturability and repairability of the aircraft and secondary power system.