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公开(公告)号：US11208957B2
公开(公告)日：2021-12-28
申请号：US16861770
申请日：2020-04-29
发明人： Michel Desjardins , Hervé Turcotte
摘要： A planetary gear train for an aircraft engine, has a sun gear rotatable about a rotation axis, planet gears meshed with the sun gear and circumferentially distributed about the rotation axis, and a ring gear meshed with the planet gears, a planet carrier having first and second disk members axially offset from one another relative to the rotation axis, the planet carrier having planet bearings secured to the first and second disk members and extending axially therebetween, the planet gears rotatably supported by the planet bearings, the planet carrier having connecting members secured to both of the first and second disk members, the connecting members located circumferentially between the planet bearings, a lubrication network extending within the planet carrier and in fluid flow communication with the planet bearing and extending within the connecting members, the connecting members defining outlets of the lubrication network, the outlets oriented toward the sun gear.
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公开(公告)号：US11525371B2
公开(公告)日：2022-12-13
申请号：US17165046
申请日：2021-02-02
发明人： Hervé Turcotte , Gabriel Naccache , Adam Logan
摘要： Cooling a torque probe involves an elongated sleeve extending along a sleeve axis between a first sleeve end and a second sleeve end. The sleeve is mountable about the torque probe to define a flow passage between an inner surface of the sleeve and an outer surface of the torque probe. The flow passage is in fluid communication with a flow passage inlet of the sleeve and with a flow passage outlet of the sleeve spaced apart along the sleeve axis from the flow passage inlet. A cooling airflow is configured to flow into the flow passage via the flow passage inlet, through the flow passage along the outer surface of the torque probe to cool the torque probe, and out of the flow passage via the flow passage outlet.
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公开(公告)号：US10662879B2
公开(公告)日：2020-05-26
申请号：US15672014
申请日：2017-08-08
发明人： Michel Desjardins , Hervé Turcotte
摘要： The epicyclic gear stage has a carrier body receiving the planet gears via corresponding planet bearings, a first bearing plane where a first axial end of the planet bearings are received by the carrier body, a second bearing plane where a second axial end of the planet bearings are received by the carrier body, a torque transfer body made integral to the carrier body externally to the sun gear, at a balanced torque transfer plane located between the first bearing plane and the second bearing plane, and extending away therefrom to a shaft coupler, for transferring torque between the carrier body and a shaft, and an oil network extending within the carrier, the oil network having an inlet in the torque transfer body, extending within the torque transfer body and into the carrier body, and extending within the carrier body and into the planet bearings.
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公开(公告)号：US11885242B2
公开(公告)日：2024-01-30
申请号：US17662143
申请日：2022-05-05
发明人： Hervé Turcotte , Kenneth Parkman , Oleg Morenko , Nicholas Guglielmin , Gavin Kisun , Ryan Miskie
CPC分类号： F01D9/065 , F01D25/162 , F05D2220/323 , F05D2240/12 , F05D2240/53 , F05D2260/60
摘要： An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.
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公开(公告)号：US11788427B2
公开(公告)日：2023-10-17
申请号：US17343838
申请日：2021-06-10
发明人： Hervé Turcotte
CPC分类号： F01D15/08 , F01D25/20 , F04C15/0061 , F05D2220/323 , F05D2240/60 , F05D2260/311 , F05D2260/4031
摘要： Lubricant pump systems and associated methods for aircraft engines are provided. The method includes receiving an input torque, dividing the input torque between a first load path receiving a first portion of the input torque, and a second load path receiving a second portion of the input torque. A first lubricant pump of the aircraft engine is driven via the first load path using the first portion of the input torque. A second lubricant pump of the aircraft engine is driven via the second load path using the second portion of the input torque. When a malfunction of the second lubricant pump occurs, the method includes ceasing to drive the first lubricant pump and the second lubricant pump using the input torque.
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公开(公告)号：US11359512B1
公开(公告)日：2022-06-14
申请号：US17165033
申请日：2021-02-02
发明人： Hervé Turcotte , Gabriel Naccache , Adam Logan
摘要： Cooling a torque probe involves an elongated sleeve extending along a sleeve axis between a first sleeve end and a second sleeve end. The sleeve is mountable about the torque probe to define a flow passage between an inner surface of the sleeve and an outer surface of the torque probe. The flow passage is in fluid communication with a flow passage inlet of the sleeve and with a flow passage outlet of the sleeve spaced apart along the sleeve axis from the flow passage inlet. A cooling fluid is configured to flow into the flow passage via the flow passage inlet, through the flow passage along the outer surface of the torque probe to cool the torque probe, and out of the flow passage via the flow passage outlet.
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