Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.

Bleed air systems for use with aircrafts and related methods

Some embodiments of the invention provide a novel prediction engine that (1) can formulate predictions about current or future destinations and/or routes to such destinations for a user, and (2) can relay information to the user about these predictions. In some embodiments, this engine includes a machine-learning engine that facilitates the formulation of predicted future destinations and/or future routes to destinations based on stored, user-specific data. The user-specific data is different in different embodiments. In some embodiments, the stored, user-specific data includes data about any combination of the following: (1) previous destinations traveled to by the user, (2) previous routes taken by the user, (3) locations of calendared events in the user's calendar, (4) locations of events for which the user has electronic tickets, and (5) addresses parsed from recent e-mails and/or messages sent to the user. In some embodiments, the prediction engine only relies on user-specific data stored on the device on which this engine executes. Alternatively, in other embodiments, it relies only on user-specific data stored outside of the device by external devices/servers. In still other embodiments, the prediction engine relies on user-specific data stored both by the device and by other devices/servers.

Warning for frequently traveled trips based on traffic

An epicyclic gear assembly includes a ring gear, a sun gear, at least one star gear enmeshed between the ring gear and sun gear, a carrier and a journal bearing. The carrier is disposed adjacent the rotatable sun gear and star gear. The journal bearing is disposed in the at least one star gear and connected to the carrier. The journal bearing has an outer radial surface with an amorphous surface finish of less than about 5 micro inches (127 micro mm) measured on an R a scale and the outer surface of the journal bearing interfaces with an inner surface of the star gear.

Epicyclic gear system with superfinished journal bearing

Some embodiments provide a method for an application executing on a mobile device. The method renders an animated navigation presentation for output to an external display screen not part of the mobile device. The navigation presentation includes an animated map showing at least a portion of a route to a destination. The method simultaneously displays information regarding a maneuver along the route on a display screen of the mobile device without displaying a same animated map on the mobile device. In some embodiments, the displayed information regarding the maneuver comprises a graphical instruction and a text instruction for a next maneuver along the route.

Mapping application with turn-by-turn navigation mode for output to vehicle display

A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft.

Epicyclic gear train for turbo fan engine

A lubrication system includes an auxiliary lubricant tank 48 , a supply conduit 58 extending from a source of lubricant 26 to the auxiliary lubricant tank. A reduced-G bypass line 108 branches from the conduit and enters the auxiliary tank at a first elevation E 1 . The system also includes an auxiliary tank discharge conduit 116 , a portion of which resides within the tank. The resident portion has an opening 122 at least partially at a second elevation E 2 higher than the first elevation.

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Lubrication system with tolerance for reduced gravity

A turbine engine includes an input shaft and a fan shaft rotatable about an axis. The fan shaft supports fan blades. An epicyclic gear train is connected between the input shaft and the fan shaft. The epicyclic gear train includes a plurality of star gears, a carrier supporting the plurality of star gears, a sun gear that meshes with the plurality of star gears and a ring gear surrounding and meshing with the plurality of star gears such that the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions include respective recesses facing one another to provide an internal annular cavity.

Ring gear mounting arrangement with oil scavenge scheme

A method of assembling an epicyclic gear train includes the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears is inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend through the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear. A gear reduction is also disclosed.

Method of assembly for gas turbine fan drive gear system

A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.

Gas turbine engine front architecture modularity

A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.

Michael E. McCune

Papers

Lubrication system with tolerance for reduced gravity

Ring gear mounting arrangement with oil scavenge scheme

Method of assembly for gas turbine fan drive gear system

Gas turbine engine front architecture modularity

Turbofan engine bearing and gearbox arrangement