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公开(公告)号：US20210325362A1
公开(公告)日：2021-10-21
申请号：US16853972
申请日：2020-04-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis BRILLON
Abstract: The gas turbine engine can have a set of components, the components of the set all being made of material compositions of the same type having a common at least one main material element, the material compositions having distinct signatures in the form of a varying trace amount of one or more signature element, the distinct signatures varying from one component of the set to another.
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公开(公告)号：US20190234509A1
公开(公告)日：2019-08-01
申请号：US15881185
申请日：2018-01-26
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel DESJARDINS , Louis BRILLON
CPC classification number: F16H57/082 , F02C7/36 , F05D2260/40311 , F16H1/28 , F16H57/0471 , F16H57/0479
Abstract: A planet carrier for an epicyclic gear train of a gas turbine engine gearbox includes a centrally disposed torque transfer coupling, a pair of carrier plates parallel to each to each other and perpendicular to a longitudinal axis, and center arms radially extending radially outward from the torque transfer coupling to the carrier plates. A central bore is concentric with the longitudinal axis and forming a torque transmission point on the planet carrier. The center arms are axially disposed between the axially spaced apart carrier plates and have radially outer ends which terminate at an outer perimeter of the carrier plates. The center arms are thus entirely radially disposed within a radial outer perimeter of the carrier plates.
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公开(公告)号：US20220365060A1
公开(公告)日：2022-11-17
申请号：US17868062
申请日：2022-07-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis BRILLON
IPC: G01N33/2028 , G01M15/14 , G01N33/28
Abstract: The method can include analyzing the composition of the particulate polymer debris, including ascertaining a presence of at least one main polymer element and a presence or absence of at least one signature polymer element in the particulate debris; establishing a correlation between the particulate polymer debris and a set of components, including matching the ascertained presence of the at least one main polymer element to a family of polymers from which the components of the set, including the source component, are made; and determining the source component amongst the components of the set, including matching the ascertained presence or absence of the at least one signature polymer element to a polymer composition of the source component.
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公开(公告)号：US20200347882A1
公开(公告)日：2020-11-05
申请号：US16403002
申请日：2019-05-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bruno MARTIN , Louis BRILLON , Julien SIMARD-BERGERON
Abstract: 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.
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公开(公告)号：US20200277994A1
公开(公告)日：2020-09-03
申请号：US16290207
申请日：2019-03-01
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis BRILLON
Abstract: A gas turbine engine with a rotor having a shaft mounted to the engine with a plurality of electrically insulating bearings is provided. The electrically insulating bearings are coupled to the shaft to support the rotor in the engine. There is at least one electrically conductive bearing coupled to the shaft and that further support the rotor in the engine. An electrically conductive path is defined between the rotor and an electrical ground of the engine. The electrically conductive path is defined through the electrically conductive bearing to reach the electrical ground of the engine. A method for electrostatically discharging a rotor supported in the gas turbine engine is also provided.
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Patent Agency Ranking
公开(公告)号：US20140084130A1
公开(公告)日：2014-03-27
申请号：US13626160
申请日：2012-09-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Marcin REJMAN , Louis BRILLON , David GAGNON-MARTIN
IPC: F16M13/02
CPC classification number: F02C7/32 , B64D2027/266 , F02C7/20 , F05D2260/30
Abstract: A gearbox positioning device to position a gearbox relative to an engine case of a gas turbine engine. The positioning device has a first and second part, with the first part having a connecting cavity of predetermined shape and being secured to the engine case. The second part has a coupling post received in the connecting cavity and constraining displacement of the gearbox in a laterally transverse direction with respect to the central longitudinal axis of the engine. The device permits movement of the gearbox in the axial direction of the engine as well as angular movement to prevent stressing the engine case during thermal growth of the engine case or support linkage imbalance. A gearbox positioning system incorporating the positioning device and the method of attaching same to the engine casing is also included.
Abstract translation: 齿轮箱定位装置，用于相对于燃气涡轮发动机的发动机壳体定位齿轮箱。 定位装置具有第一和第二部分，其中第一部分具有预定形状的连接腔并被固定到发动机壳体。 第二部分具有接收在连接腔中的联接柱并且相对于发动机的中心纵向轴线横向横向限制齿轮箱的位移。 该装置允许齿轮箱在发动机的轴向方向上的运动以及角度运动，以防止在发动机壳体或支撑连杆不平衡的热增长期间压缩发动机壳体。 还包括结合有定位装置的齿轮箱定位系统和将其连接到发动机壳体的方法。
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公开(公告)号：US20240240592A1
公开(公告)日：2024-07-18
申请号：US18154134
申请日：2023-01-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis BRILLON , Mateusz KESEK
IPC: F16H57/031 , F02C7/25 , F02C7/32
CPC classification number: F16H57/031 , F02C7/25 , F02C7/32 , F05D2220/323 , F05D2260/30 , F05D2260/4031 , F05D2260/96
Abstract: An accessory gearbox of an aircraft engine includes a cover mounted thereto. The cover defines a centrally extending axis and has an outer surface with accessory mounts disposed thereon. First and second accessory devices are mounted to the gearbox at first and second mounts spaced apart on the cover. A planar linking member dynamically couples the first accessory device to the second accessory device. The linking member extends transversally relative to the axis and has a first side opposite a second side with a first opening extending therethrough. The first opening is aligned and matingly receiving at least a portion of the first accessory device therethrough. The linking member has a second opening extending therethrough. The second opening is aligned and matingly receiving at least a portion of the second accessory device therethrough. The linking member mechanically interconnects the first and second accessory devices independently from the cover.
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公开(公告)号：US20210324761A1
公开(公告)日：2021-10-21
申请号：US16849523
申请日：2020-04-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Guy BOUCHARD , Louis BRILLON
IPC: F01D25/18
Abstract: A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.
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公开(公告)号：US20180334964A1
公开(公告)日：2018-11-22
申请号：US15598770
申请日：2017-05-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel DESJARDINS , Jean DUBREUIL , Louis BRILLON
Abstract: A turbo propeller engine comprises a housing circumferentially extending around a longitudinal axis and disposed around a gearbox. The turbo propeller engine includes a propeller outside of the housing and a shaft surrounded in part by the housing and extending along the longitudinal axis. The shaft has a front end and a rear end. The propeller is mounted to the front end. The rear end is in a driven engagement with an output of the gearbox. The shaft is rotatably supported by a first bearing and by a second bearing separated from the first bearing by an axial distance along the longitudinal axis. The first and second bearings are disposed on opposite sides of the gearbox. The first bearing is disposed between the shaft and the housing, the second bearing is disposed between the housing and a component of the gearbox to rotatingly support the component of the gearbox.
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公开(公告)号：US20240229720A1
公开(公告)日：2024-07-11
申请号：US18151747
申请日：2023-01-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis BRILLON , Mateusz KESEK
IPC: F02C7/32
CPC classification number: F02C7/32 , F05D2220/323 , F05D2260/4031
Abstract: An accessory gearbox of an aircraft engine includes an accessory gearbox cover mounted to the accessory gearbox. The accessory gearbox cover has an outer surface with accessory mounts disposed thereon. A first accessory device is mounted to the accessory gearbox at a first mount of the accessory mounts. Aa second accessory device is mounted to the accessory gearbox cover at a second mount of the accessory mounts. The second mount is spaced apart on the accessory gearbox cover from the first mount. A link member dynamically couples the first accessory device to the second accessory device. The link member has an elongate body extending between a first end and a second end. The first end is coupled to the first accessory device and the second end is coupled to the second accessory device to mechanically interconnect the first and second accessory devices independent from the accessory gearbox cover.
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