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公开(公告)号：US11313239B2
公开(公告)日：2022-04-26
申请号：US17057550
申请日：2019-05-20
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Thomas Alain De Gaillard , Alexandre Bernard Marie Boisson , Rémi Roland Robert Mercier , Alexis Thomas Chaboud
Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.
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公开(公告)号：US11021973B2
公开(公告)日：2021-06-01
申请号：US16086492
申请日：2017-03-20
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.
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公开(公告)号：US11346247B2
公开(公告)日：2022-05-31
申请号：US16809637
申请日：2020-03-05
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Cedric Zaccardi , Alexandre Bernard Marie Boisson , Christophe Marcel Lucien Perdrigeon , Catherine Pikovsky
IPC: F01D25/12
Abstract: A turbine engine of an aircraft includes: a primary air flow duct; a secondary air flow duct which is located around the primary duct, the secondary duct including a stator including a plurality of blades distributed around a main axis of the turbine engine and inter-blade platforms located between radially internal ends or between radially external ends of two adjacent blades, each platform including a wall partially delimiting the secondary duct; and a fluid circuit which includes a heat exchanger formed by at least one of the platforms. The platform includes a line that has an inlet port of the fluid and a fluid outlet port. The fluid circuit includes a distributor associated with each port of the at least one platform with the rest of the fluid circuit and of which each distributor is axially offset with respect to the platform along the main axis.
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公开(公告)号：US10267164B2
公开(公告)日：2019-04-23
申请号：US15569161
申请日：2016-04-26
Applicant: Safran Aircraft Engines
Inventor： Caroline Jacqueline Denise Berdou , Alexandre Bernard Marie Boisson , Matthieu Arnaud Gimat , Audrey Laguerre
Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).
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公开(公告)号：US10570757B2
公开(公告)日：2020-02-25
申请号：US15787838
申请日：2017-10-19
Applicant: Safran Aircraft Engines
Inventor： Thomas Alain De Gaillard , Alexandre Bernard Marie Boisson , Gilles Pierre-Marie Notarianni , Charles-Henri Claude Jacky Sullet
Abstract: A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.
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Patent Agency Ranking
公开(公告)号：US10233939B2
公开(公告)日：2019-03-19
申请号：US15205265
申请日：2016-07-08
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.
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公开(公告)号：US20180112545A1
公开(公告)日：2018-04-26
申请号：US15787838
申请日：2017-10-19
Applicant: Safran Aircraft Engines
Inventor： Thomas Alain De Gaillard , Alexandre Bernard Marie Boisson , Gilles Pierre-Marie Notarianni , Charles-Henri Claude Jacky Sullet
Abstract: A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.
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公开(公告)号：US11525366B2
公开(公告)日：2022-12-13
申请号：US17292122
申请日：2019-11-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Alexandre Bernard Marie Boisson , Kaëlig Merwen Orieux
Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).
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公开(公告)号：US11460040B2
公开(公告)日：2022-10-04
申请号：US15548040
申请日：2016-02-04
Applicant: Safran Aircraft Engines
Inventor： Guillaume Olivier Vartan Martin , Alexandre Bernard Marie Boisson , Claire Marie Figeureu , Frederic Alain Edouard Allair , Thea Claire Lancien
Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.
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公开(公告)号：US11149570B2
公开(公告)日：2021-10-19
申请号：US16512931
申请日：2019-07-16
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: An outlet guide vane for a fan of a turbomachine is provided. The outlet guide vane includes a blade made of composite material and having a radial inner end, a first metal fastener portion fastened to the radial inner end, a first platform extending transversely with respect to the blade in the vicinity of the radial inner end. The first metal fastener portion is to be mounted on and fastened to an upstream flange and to a downstream flange of a hub. The first platform is monolithic with the first metal fastener portion or with the blade. A rectifier wheel and a turbomachine including the outlet guide vane are also provided.
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