United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

David Allen Stachowiak

Todd A Davis

Mark Ronski

Paul R Hanrahan

Jonathan F Zimmitti

William G Sheridan

Marc J Muldoon

Hung Duong

Benjamin T Mylrea

Lakshminarayan S Bettagere

Wesley P Long

Timothy Webb

Brian V Abedon

Francis Parnin

Brian Abedon

An assembly is provided for an aircraft. This assembly includes a geartrain, a first propulsor rotor and a rotating structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The ring gear circumscribes the sun gear and is rotatable about an axis. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The carrier is rotatable about the axis. The first propulsor rotor is coupled to the carrier. The rotating structure is coupled to the ring gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.

Aircraft propulsion system geartrain

An aircraft assembly includes a geartrain with a first gear system and a second gear system. The first gear system includes a first sun gear, a first ring gear, a plurality of first intermediate gears and a first carrier. The first sun gear and the first ring gear are each rotatable about an axis. The first intermediate gears are between and meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the first carrier. The second gear system is interconnected with the first gear system. The second gear system includes a second sun gear, a second ring gear, a plurality of second intermediate gears and a second carrier. The second intermediate gears are between and meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the second carrier.

A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft rotatable about an axis. A plurality of intermediate gears are coupled to the sun gear, a ring gear is coupled to the plurality of intermediate gears, and a carrier supports rotation of the plurality of intermediate gears. The carrier includes a gear portion and an accessory component that is coupled to and driven by the gear portion of the carrier.

Component mounting and drive in a geared turbofan architecture

A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft that is rotatable about an axis. The sun gear includes a first gear portion and a second gear portion. A plurality of intermediate gears are coupled to the first gear portion of the sun gear, a ring gear is coupled to the plurality of intermediate gears, a carrier supports rotation of the plurality of intermediate gears, and an accessory component is coupled to the second gear portion of the sun gear.

A fan drive gear system for a turbine engine includes a carrier that supports rotation of the plurality of intermediate gears and is configured for rotation about the axis. A rotating oil inlet and rotating gutter are attached to the carrier. A transfer bearing is fixed to a static engine structure and engaged to communicate oil to the rotating oil inlet. A static baffle that is disposed radially outward of the transfer bearing and configured to direct oil that is expelled from the transfer bearing into the rotating gutter.

Rotating carrier oil manifold

A first gear system includes a first sun gear, a first ring gear, first intermediate gears and a first carrier. The first intermediate gears are between and meshed with the first sun gear and the first ring gear. Each first intermediate gear is rotatably mounted to the first carrier. A second gear system includes a second sun gear, a second ring gear, second intermediate gears and a second carrier. The second ring gear is coupled to the first carrier. The second intermediate gears are between and meshed with the second sun gear and the second ring gear. Each second intermediate gear is rotatably mounted to the second carrier. A first propulsor rotor is coupled to the first carrier. A rotating structure is coupled to the first ring gear and includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.

A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft that is rotatable about an axis, a plurality of intermediate gears that are intermeshed with the sun gear, a ring gear assembly that is engaged with the plurality of intermediate gears, the ring gear configured for attachment to a static structure, a carrier that supports rotation of the plurality of intermediate gears, the carrier configured for rotation about the axis, a fixed gutter system that is configured to receive expelled lubricant and to direct the expelled lubricant to an auxiliary reservoir, at least one ejector that is disposed within the fixed gutter and configured to utilize a motive flow to generate a lubricant flow through at least one outlet, and a fan shaft that is rotatable about the axis and configured to be driven by the carrier.

Fan drive gear system gutter ejector system

A fluid filtration assembly (FFA) includes a housing having a thickness defined between an internal surface and an external surface, the housing receiving a filter and defining an outer annular flow passage between an outer surface of the filter and the internal surface of the housing; an inlet pipe communicates with the FFA and injects a fluid into the housing to impart a centrifugal force; an outlet pipe communicates with the FFA and discharges the fluid from the housing; and a collection area disposed towards an end of the outer annular flow passage collects particulate matter from the fluid; wherein a width of the outer annular flow passage increases towards the collection area.

Centrifugal debris pre-separator for turbine engine oil filter

A fluid tank system comprises a fluid container that includes a sensor opening in a fluid container wall defined by a rim, and a fluid level sensor comprising a radial flange on a proximate end of a longitudinally extending electronics stem that includes a distal end. The distal end of the electronic stem is inserted into the fluid container via the sensor opening and the radial flange seats on the rim. The distal end of the electronics stem is guided via a first radial support and a second radial support to a seat that is located coaxial with the sensor opening, where the first and second radial supports are longitudinally separated and radially spaced apart to allow the electronics stem to longitudinally pass between the first and second radial supports until the flange seats on the rim ensuring that the distal end of the electronic stem is longitudinally positioned adjacent to the seat.

Oil level sensor guide

An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

Oil tank mount arrangement on a geared turbofan engine

An oil tank for a gas turbine engine includes a top and a bottom disposed vertically beneath the top. An overfill return passage extends from the bottom of the oil tank toward the top of the oil tank. An outlet is formed on the bottom of the oil tank and inside the overfill return passage. A check valve is inside the overfill return passage and is connected to the outlet. The check valve includes a seat circumscribing the outlet and a plug inside the overfill return passage. The plug has a lower density than an oil disposed inside the oil tank. The check valve does not include a spring such that the plug is configured to translate freely inside the overfill return passage.

Check valve for overflow oil line when pressure fill fittings are remote

A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor operable to drive rotation of a starting spool of the gas turbine engine through the gear train at a substantially constant speed upon engine shutdown until an energy storage source is depleted.

Auxiliary drive bowed rotor prevention system for a gas turbine engine

A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor. The gear train is coupled through an engine accessory to an engine accessory gearbox that is further coupled to a starting spool of the engine. The bowed rotor prevention motor is operable to drive rotation of the starting spool of the gas turbine engine through the gear train upon engine shutdown.

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Manchester, CT, United States of America

David Allen Stachowiak