Pratt-Whitney Canada Corp

Michel Desjardins

Vincent Savaria

Hervé Turcotte

Eric Durocher

Jean Dubreuil

Louis Brillon

Guillaume Landry-Drolet

Eugene Gekht

Keith Morgan

Mark Cunningham

Paul Weaver

Bruno Martin

Roberto Brito

Francois Bisson

Guo Rong Yan

Francis Bonacorsi

Lazar Mitrovic

Johnny Vinski

Bruno Chatelois

Alain Lewis

John Wilson

Daniel Ouimette

A lubrication system of a gas turbine engine includes a lubricant reservoir with a housing having a volume of oil located therein. A reservoir passage extends through the housing. One or more side passages extend from the reservoir passage and are configured to selectably fill or drain the volume of oil. An output passage is separate and distinct from the reservoir passage, and a separator wall extends into the interior of the housing from the first housing wall toward the second housing wall and between the reservoir passage and the output passage. When the lubricant reservoir is in a first orientation, the lubricant reservoir is filled via oil flowed through the reservoir passage from the first housing end, and when operated in a negative G orientation, the lubricant reservoir is drained via oil flowed through the reservoir passage and out of the second housing end.

Oil feed management system

A system is provided for an aircraft. This aircraft system includes a powertrain and a first lubrication system. The powertrain includes a powerplant, a bladed rotor and a clutch system operatively coupling the powerplant to the bladed rotor. The powerplant is configured to drive rotation of the bladed rotor through the clutch system when the clutch system is engaged. The first lubrication system is fluidly coupled with and is configured to deliver first lubricant to the powerplant and the clutch system.

Lubrication system for aircraft powerplant and clutch system

An engine assembly for an aircraft propulsion system includes a gas turbine engine, a gearbox, and a first drive shaft. The gas turbine engine includes an engine output shaft, an air intake, and a compressor. The air intake includes an air intake body forming an air inlet, an air outlet, and an air plenum extending between and connecting the air inlet and the air outlet. The air plenum extends circumferentially about the engine output shaft between and to a first circumferential end of the air intake and a second circumferential end of the air intake. The first circumferential end and the second circumferential end form a circumferential gap. The compressor is connected in fluid communication with the air intake. The gearbox includes a gear assembly operably connected to the engine output shaft. The first drive shaft is operably connected to the gear assembly. The first drive shaft extends through the circumferential gap.

Air intake for an aircraft propulsion system engine assembly

A method of performing maintenance on an aircraft engine includes removing a propeller shaft of the aircraft engine to form an access volume at a center of the aircraft engine. The access volume extends axially and radially relative to a center axis of the aircraft engine. The method includes performing maintenance on a lubricant strainer positioned at a location of the access volume where a carrier of the aircraft engine engages an output of the aircraft engine.

Lubrication system for aircraft engine reduction gearbox

A reduction gearbox is provided that includes a planetary gear arrangement disposed in a casing and a lubrication handling system. The planetary gear arrangement includes a sun gear, planet gear assemblies, and independent fore and aft ring gears. Each planet gear assembly has fore and aft lateral gears respectively disposed on opposite sides of a main gear and rotating therewith. The main gear has a main gear pitch diameter and the fore and aft lateral gears having a lateral gear pitch diameter. The fore ring gear is meshed with the fore lateral gears. The aft ring gear is meshed with the aft lateral gears. The planet gear assemblies are in communication with an output. The lubrication handling system includes a fore ring gear baffle and an aft ring gear baffle.

Reduction gearbox for gas turbine engine with lubrication control system

A system is provided for an aircraft. This aircraft system includes a powertrain, a lubrication system and a casing. The powertrain includes a powerplant, a power transmission, a clutch system and a bladed rotor. The power transmission operatively couples the powerplant to the clutch system. The clutch system operatively couples the power transmission to the bladed rotor. The powerplant is configured to drive rotation of the bladed rotor through the power transmission and the clutch system when the clutch system is engaged. The lubrication system includes a lubricant reservoir and a lubricant circuit. The lubrication system is configured to direct lubricant from the lubricant reservoir to the powerplant and the power transmission through the lubricant circuit. The casing houses the power transmission and the lubricant reservoir.

Aircraft power system module with integral lubricant reservoir

An assembly for an aircraft propulsion system includes a planetary gear assembly, a torque sensor, and a controller. The planetary gear assembly includes a sun gear, a plurality of planet gears, a first ring gear, and a second ring gear. Each planet gear of the plurality of planet gears includes a main gear, a first lateral gear, and a second lateral gear. The main gear is engaged with the sun gear, the first lateral gear is engaged with the first ring gear, and the second lateral gear is engaged with the second ring gear. The torque sensor assembly contacts the second ring gear. The torque sensor assembly is configured to generate an output signal corresponding to an axial deflection of the second ring gear. The controller is configured to calculate a torque applied to the output shaft by the planetary gear assembly using the output signal.

Torque sensor for an aircraft propulsion system gearbox assembly

The power plant can have a structure; an output shaft connectable to a load, the output shaft rotatable about an axis relative the structure; a thermal engine secured to the structure, the thermal engine having a thermal engine shaft; an electric motor having a stator and a rotor shaft, the stator secured to the structure; an epicyclic gearing having a sun gear coaxial to a ring gear, a plurality of planet gears meshed between the sun gear and the ring gear, and a carrier coaxial to the sun gear and to the ring gear, the sun gear, carrier, and ring gear being rotatable relative the casing structure, the output shaft and the rotor shaft both coupled to the carrier, and the thermal engine shaft coupled to sun gear and the carrier; and an overrunning clutch operable to prevent the rotation of the ring gear in one angular direction.

Hybrid aircraft power plant

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

A planetary gearbox is provided that includes a sun gear, a plurality of planet gear assemblies, each planet gear assembly having a main gear meshed with the sun gear, a fore lateral gear and an aft lateral gear disposed on opposite sides of the main gear and rotating therewith, a planet carrier rotatably supporting at least some of the planet gear assemblies, and at least one fore ring gear meshed with the fore lateral gears, at least one aft ring gear meshed with the aft lateral gears, wherein one of the sun gear, the planet carrier, and the ring gears is configured to be operatively connected to an input, one is configured to be operatively connected to an output, and rotation of a remaining one is limited.

Planetary gearbox for gas turbine engine

An assembly for an aircraft propulsion system includes an output shaft and a gear assembly. The gear assembly is configured to drive rotation of the output shaft. The gear assembly includes a sun gear, a plurality of planet gears, a first ring gear, and a second ring gear. The sun gear is rotatable about a rotational axis. The sun gear includes a first double helical gear pattern. Each planet gear of the plurality of planet gears includes a main gear, a first lateral gear, and a second lateral gear. The main gear includes a second double helical gear pattern engaged with the first double helical gear pattern. The first lateral gear is engaged with the first ring gear. The second lateral gear is engaged with the second ring gear. The first ring gear is axially spaced from the second ring gear relative to the rotational axis.

Gearbox assembly for an aircraft propulsion system

A method of assembling a reduction gearbox is provided that includes: a) aligning first and second ring gears by mounting the first ring gear in a first casing section in a first predetermined position and mounting the second ring gear in a second casing section in a second predetermined position, wherein the first and second casing sections mate with one another in a defined orientation; b) angularly aligning a plurality of planet gear assemblies relative to one another, each planet gear assembly having a main gear, a first lateral gear, and a second lateral gear coupled to one another; c) disposing the aligned planet gear assemblies between the first and second casing sections; and d) coupling the first and second casing sections together in the defined orientation with the first lateral gears meshed with the first ring gear and the second lateral gears meshed with the second ring gear.

Method and system for assembling a reduction gearbox

A reduction gearbox is provided that includes a planetary gear arrangement disposed in a casing. The planetary gear arrangement includes a sun gear, planet gear assemblies, and fore and aft ring gears. The sun gear is configured for communication with an input. Each planet gear assembly has a main gear meshed with the sun gear, fore and aft lateral gears disposed on opposite sides of the main gear and rotating therewith. The main gear has a main gear pitch diameter and the fore and aft lateral gears having a lateral gear pitch diameter. The fore ring gear is meshed with the fore lateral gears. The aft ring gear is meshed with the aft lateral gears. The aft ring gear is independent of the fore ring gear. The planet gear assemblies are in communication with an output. The fore and aft ring gears are mechanically engaged with the casing.

Reduction gearbox for gas turbine engine

A reduction gearbox is provided that includes a planetary gear arrangement disposed in a casing. The planetary gear arrangement includes a sun gear, planet gear assemblies, and a fore and aft ring gears. The sun gear is configured in communication with a cantilevered end of an input. Each planet gear assembly has a main gear meshed with the sun gear, a fore lateral gear and an aft lateral gear disposed on opposite sides of the main gear and rotating therewith. The main gear has a main gear pitch diameter and the fore and aft lateral gears having a lateral gear pitch diameter. The fore ring gear is meshed with the fore lateral gears. The aft ring gear is meshed with the aft lateral gears. The aft ring gear is independent of the fore ring gear. The planet gear assemblies are in communication with an output.

The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.

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St-Hubert, Canada

Michel Desjardins