Pratt-whitney Canada Corp

Forensic Technology Wai, Inc.

Bruno Martin

Michel Desjardins

Louis Brillon

Julien Simard-Bergeron

François Godbout

A reduction gearbox is provided that includes a sun gear, planet gear assemblies, first and second ring gears, and a ring gear positional alignment system. Each planet gear assembly includes a main gear and first and second lateral gears coupled to one another. The ring gear positional alignment system includes a system controller, a ring gear actuator, and a sensor. The ring gear actuator is engaged with the first ring gear and is configured to rotate the first ring gear relative to the second ring gear. The system controller is in communication with the sensor, the ring gear actuator, and a non-transitory memory storing instructions. The instructions when executed cause the system controller to receive and process signals from the sensor relating to the position of the first ring gear, and control the ring gear actuator to selectively position the first ring gear using the signals from the sensor.

Method and system for mitigating ring gear misalignment within a reduction gearbox

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between an inner side and an outer side. The journal bearing includes a bore, a passage and a groove. The bore extends axially within the journal bearing and is formed by the inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove is arranged at the outer side. The groove extends longitudinally within the journal bearing between a first end and a second end. The groove extends axially within the journal bearing between a first side and a second side. An axial distance between the first side and the second side changes as the groove extends longitudinally between the first end and the second end.

Shaped cavity at interface between journal bearing and rotor

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between a bearing inner side and a bearing outer side. The journal bearing includes a bore, a passage, a groove and a slot. The bore extends axially within the journal bearing and along the bearing inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove extends longitudinally within the journal bearing at the bearing outer side between a groove first end and a groove second end. At least a portion of the slot extends circumferentially about the axis within the journal bearing at the bearing outer side from the groove first end to the groove second end.

Feed circuit with slot(s) at interface between journal bearing and rotor

A powerplant system is provided that includes a gas turbine engine system and an actuation system. The gas turbine engine system includes a rotating structure, a stationary structure and one or more bearings rotatably mounting the rotating structure to the stationary structure. The actuation system is configured to passively rotate the rotating structure about a rotational axis during transportation of the gas turbine engine system.

Passively rotating a rotating structure of a gas turbine engine during transportation

An assembly is provided for a turbine engine. This turbine engine assembly includes a journal bearing and a filter. The journal bearing has an internal bearing bore. The filter is arranged within the internal bearing bore. The filter includes a tubular filter element and a first end cap. The tubular filter element extends axially along an axis between a first end and a second end. A perforated portion of the tubular filter element is radially disposed away from the journal bearing by a cavity. The first end cap is mounted to the tubular filter element at the first end. The first end cap is sealed radially against the journal bearing by a first interference fit.

Lubricant filter for a turbine engine

An active de-aerator for an aircraft engine is provided, with a housing having an air-oil inlet, an oil outlet and an air outlet. An impeller is received within and rotatable relative to the housing about a central axis. The active de-aerator has a first journal bearing on a first side of the impeller for rotatably supporting the impeller relative to the housing and a second journal bearing on a second side of the impeller for rotatably supporting the impeller relative to the housing, the second side being opposite the first side.

Double journal bearing impeller for active de-aerator

A journal bearing assembly for rotatably supporting a gear in a gear system. The journal bearing assembly comprises a journal bearing for rotatably supporting the at least one gear. The journal bearing includes an engagement feature at a distal end thereof. The distal end is insertable into an opening in a gear carrier of the gear system. The opening includes an anti-rotation feature engageable with the engagement feature to block the journal bearing from rotating about an axis extending longitudinally through the center of the journal bearing. The journal bearing assembly further includes a fastening feature for fastening the journal bearing to the gear carrier.

Carrier journal with anti-rotation feature

A seal runner assembly for a gas turbine engine includes a non-rotational annular wear seal, and an annular seal runner having an annular body defining an annular front face contacting the wear seal, the annular body defining an aperture extending axially through the seal runner, the aperture configured for receiving therein a part of a shaft of the gas turbine engine, the seal runner having a plurality of axially-extending slots at locations that are distributed around a wall of the seal runner that extends circumferentially about at least a portion of the annular front face and extends from the front face in a direction away from the wear seal. A method for sealing a gap between a part of a machine and a rotatable shaft of the machine is also provided.

Seal runner and method

A gas turbine engine comprising a gearbox, the gearbox having gear(s). A journal bearing assembly rotatably supports the gear, the journal bearing assembly having at least a pin, and a journal having a tubular body defining a pin-receiving inner cavity having an inner surface, a first cavity and a second cavity defined in the inner surface of the pin-receiving inner cavity, a rib support located between the first cavity and the second cavity, the rib support being aligned with a longitudinal center of the tubular body, with the first cavity and the second cavity on opposed axial sides of the rib support.

Journal bearing assembly with dual oil cavities

A method and apparatus for an automated system to extract a high quality signature from an image having areas not relevant for specific identification purposes which can lead to misleading image signatures, the method comprising: identifying at least one region of interest within the image by determining local orientation information at each pixel position in the image, the at least one region of interest comprising elements useful for the specific identification purposes; creating and applying a mask for the image wherein only the at least one region of interest is exposed; extracting a signature for the image taking into account the at least one region of interest exposed by the mask.

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Saint-Jean-sur-Richelieu, Canada

Bruno Martin