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公开(公告)号：US20170369153A1
公开(公告)日：2017-12-28
申请号：US15535773
申请日：2015-12-17
Applicant: Safran Aircraft Engines
Inventor： Laurence Francine VION , Mathieu Simon Paul GRUBER
CPC classification number: B64C11/48 , B64C11/18 , B64C11/306 , F01D7/00 , Y02T50/66
Abstract: A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.
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公开(公告)号：US20230123376A1
公开(公告)日：2023-04-20
申请号：US18076976
申请日：2022-12-07
Inventor： Fernando GEA AGUILERA , Raphaël BARRIER , Mathieu Simon Paul GRUBER , Cyril POLACSEK , Hélène Dominique Jeanne POSSON
Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.
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公开(公告)号：US20210291962A1
公开(公告)日：2021-09-23
申请号：US17341277
申请日：2021-06-07
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.
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公开(公告)号：US20240308647A1
公开(公告)日：2024-09-19
申请号：US18577064
申请日：2022-07-04
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Fernando GEA AGUILERA , Anthony BINDER , Adrien Clément Marcel DUBOIS , Mathieu Simon Paul GRUBER , Norman Bruno André JODET , Eva Julie LEBEAULT , Josselin David Florian REGNARD
Abstract: An aeronautical thruster having a longitudinal axis and having a hub and at least two annular rows of unducted blades including an upstream annular row and a downstream annular row which are spaced apart from one another along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, and the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade.
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公开(公告)号：US20200148325A1
公开(公告)日：2020-05-14
申请号：US16657278
申请日：2019-10-18
Inventor： Fernando GEA AGUILERA , Raphaël BARRIER , Mathieu Simon Paul GRUBER , Cyril POLACSEK , Hélène Dominique Jeanne POSSON
Abstract: The invention relates to a profiled structure, elongated in a direction in which the structure has a length (L1) exposed to an airflow (U), and transversely to which the structure has a leading edge (164) and/or a trailing edge (165), at least one of which is profiled and has, along said direction of elongation, geometric serration patterns (28) defined by a succession of peaks (30) and troughs (32). Along the profiled leading edge and/or trailing edge, the serration patterns (28) have a geometric pattern that is repeated in the direction of elongation (L1), the shape of which is stretched and/or contracted: transversely to the direction of elongation, and/or in the direction of elongation.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20180065727A1
公开(公告)日：2018-03-08
申请号：US15551921
申请日：2016-02-18
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Mathieu Simon Paul GRUBER , Norman Bruno Andre JODET
Abstract: A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.
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公开(公告)号：US20210388725A1
公开(公告)日：2021-12-16
申请号：US17286751
申请日：2019-09-24
Inventor： Fernando GEA AGUILERA , Raphaël BARRIER , Mathieu Simon Paul GRUBER , Cyril POLACSEK , Hélène Dominique Jeanne POSSON
Abstract: The invention relates to a profiled structure, elongated in a direction in which the structure has a length exposed to an airflow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations (28a) defined by successive teeth (30) and depressions (32). Along the profiled leading edge and/or profiled trailing edge, the successive teeth (30) and depressions (32) extend only over a part of said length exposed to the flow over which the amplitude and/or spacing of the teeth varies monotonically except for the few teeth nearest each end of said part, a remaining part (280) of said length being smooth.
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公开(公告)号：US20190170003A1
公开(公告)日：2019-06-06
申请号：US16174553
申请日：2018-10-30
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Claire Marie FIGEUREU , Eric Pierre Georges LEMARECHAL , Benjamin BULOT , Mathieu Simon Paul GRUBER , Raphael BARRIER , Cyril POLACSEK
IPC: F01D9/04
Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.
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公开(公告)号：US20170284205A1
公开(公告)日：2017-10-05
申请号：US15507071
申请日：2015-08-28
Applicant: Safran Aircraft Engines
CPC classification number: F01D5/147 , B64C11/06 , B64C11/30 , B64D2027/005 , F01D1/26 , F01D5/06 , F01D7/00 , F02K3/072 , F05D2220/30 , F05D2220/325 , F05D2250/314 , F05D2260/74 , F05D2260/79 , F05D2260/961 , Y02T50/66 , Y02T50/673
Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.
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公开(公告)号：US20170274980A1
公开(公告)日：2017-09-28
申请号：US15506937
申请日：2015-08-28
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B64C11/30 , B64C11/06 , B64C11/48 , B64D2027/005 , F01D1/26 , F01D7/00 , F02K3/072 , F04D29/362 , F05D2220/325 , F05D2250/314 , F05D2260/74 , F05D2260/79 , F05D2260/961 , Y02T50/66 , Y02T50/673
Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.
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