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US Patent 11268453 Lubrication system for aircraft engine reduction gearbox

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Contents

Is a
Patent
Patent
0

Patent attributes

Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
0
Patent Number
112684530
Patent Inventor Names
Michel Desjardins0
Vincent Savaria0
Date of Patent
March 8, 2022
0
Patent Application Number
172039020
Date Filed
March 17, 2021
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Patent Citations
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US Patent 10364752 System and method for an integral drive engine with a forward main gearbox
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US Patent 10371060 Compound engine assembly with confined fire zone
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US Patent 10371170 Noise reduction using IGV flow ejections
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US Patent 10378438 Reverse flow gas turbine engine with radially outward turbine
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US Patent 10385785 Air inlet for a gas turbine engine
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US Patent 10393027 Gas turbine engine shaft architecture and associated method of disassembly
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US Patent 10422243 Gas turbine engine dual towershaft accessory gearbox and starter generator assembly
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US Patent 10422286 Turbine engine with epicyclic reduction gear train
...
Patent Citations Received
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US Patent 12000344 Aircraft turbine engine with an off-axis propeller
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US Patent 11680525 Lubricant filter for a turbine engine
0
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US Patent 11971085 Gearbox assembly
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Patent Primary Examiner
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Derek D Knight
0
Patent abstract

An epicyclic gear train includes a sun gear and planet gears mounted to a carrier and engaged to the sun gear. The planet gears and the carrier are rotatable about a center axis, and the carrier is engaged with a power output at a carrier-output engagement location. Ring gears are in meshed engagement with the planet gears. Planet gear bearings are disposed between one of the planet gears and the carrier. A lubrication interface is defined between each planet gear bearing and one of the planet gears. A bearing lubrication system includes a lubricant supply conduit extending between a conduit inlet at the carrier-output engagement location and conduit outlets at the lubrication interfaces of the planet gear bearings. A lubricant strainer is mounted about the conduit inlet at the carrier-output engagement location.

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