A system for deploying a blocker door of a nacelle includes a master link configured to be coupled to a fixed structure of the nacelle and a master crank pivotally attached to the master link. The system further includes a first door crank and a first door link pivotally coupled to the first door crank. The system further includes a first blocker door coupled to the first door link and a first driveshaft coupled to the master crank and to the first door crank and configured to transfer motion from the master crank to the first door crank such that aft translation of a translating sleeve of the nacelle drives the master crank via the master link, which drives the first door link via the first driveshaft and the first door crank to move the first blocker door into a bypass air duct defined by the nacelle.

A gas turbine engine includes a turbine section that includes a fan drive turbine. A geared architecture includes a sun gear in driving engagement with the fan drive turbine. A plurality of planet gears surrounds the sun gear. A ring gear surrounds the plurality of planet gears. A deflection limiter mechanically attaches the ring gear to an engine static structure. The deflection limiter includes a first support fixed to the ring gear that has a first interlocking feature and a second support fixed to the engine static structure that has a second interlocking feature. The first and second interlocking features define at least one of a radial clearance of between 0.005 inches (0.127 mm) and 0.080 inches (2.032 mm) or a circumferential clearance of between 0.005 inches (0.127 mm) and 0.250 inches (2.032 mm). A fan section includes a plurality of fan blades in driving engagement with the geared architecture through a fan drive shaft.

The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

A variable vane assembly for a gas turbine engine having an actuating system including a rotatable face gear and a respective pinion engaged to and extending transversely from the end of each of the moveable vanes. The teeth of each pinion define land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith. A smallest axial distance between the adjacent land surfaces of the meshed pinion and face gear teeth define a backlash of the actuating system. At least one shim has a thickness adjusting an axial distance between the pinion and the face gear to set the backlash to a predetermined value. An engine with a compressor with a variable vane assembly and a method of adjusting angular variance in an actuating system for variable vanes are also discussed.

A gas turbine engine includes a turbine section that includes a fan drive turbine. A geared architecture includes a sun gear in driving engagement with the fan drive turbine. A plurality of planet gears surrounds the sun gear. A ring gear surrounds the plurality of planet gears. A deflection limiter mechanically attaches the ring gear to an engine static structure. The deflection limiter includes a first support fixed to the ring gear that has a first interlocking feature and a second support fixed to the engine static structure that has a second interlocking feature. The first and second interlocking features define at least one of a radial clearance of between 0.005 inches (0.127 mm) and 0.080 inches (2.032 mm) or a circumferential clearance of between 0.005 inches (0.127 mm) and 0.250 inches (2.032 mm). A fan section includes a plurality of fan blades in driving engagement with the geared architecture through a fan drive shaft.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

A turbocharger assembly (1) comprises a turbine (4), a compressor (6), a housing (8), one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58) and a pettier device (46). The pettier device (46) is configured to provide electrical power to the one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58).

A two piece impeller centrifugal pump comprising two halves of an impeller facing each other within a volute, a housing having two sides, one side adjacent each impeller half and having an inlet and an outlet, a motor mounted on the housing, the motor driving both impeller halves, for pumping fluid or material from the inlet to the outlet, the housing and the impeller halves having a sealing surface where they contact each other, the centrifugal force of the impeller forcing the fluid or material outward, pushing the two impeller halves outward against the housing.

A drive mechanism (10) for driving a first adjustment member (12) for adjusting the orientation of the blades (14) of a first turbomachine rectifier stage (16) and a second adjustment member (18) for adjusting the orientation of the blades (20) of a second turbomachine rectifier stage (22), which comprises a mechanism for simultaneously moving the two adjustment members (12, 18) in the turbomachine, characterised in that it comprises a single drive wheel (24) that simultaneously drives the first adjustment member (12) and the second adjustment member (18) and comprises two gear stages (26, 28) that are arranged between the drive wheel (24) and one or the other of the first adjustment member (12) and the second adjustment member (18) and that have different transmission ratios.

A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet; and a fuel gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor and an axis. The fuel gas separator further includes a stationary casing; and a separator assembly including a core and a plurality of paddles extending from the core, the separator assembly rotatable about the axis within the stationary casing to separate a fuel/gas mixture received through the fuel/gas mixture inlet into a liquid fuel flow and stripping gas flow.