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公开(公告)号：US11732588B2
公开(公告)日：2023-08-22
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：US10941667B2
公开(公告)日：2021-03-09
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
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：US11668196B2
公开(公告)日：2023-06-06
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
CPC classification number: F01D5/145 , B64C3/10 , B64C21/10 , F01D9/041 , B64C2230/14 , F05D2220/323 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2250/183 , F05D2250/184 , F05D2260/961
Abstract: A profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.
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公开(公告)号：US11560796B2
公开(公告)日：2023-01-24
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 exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, 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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