Profiled structure for an aircraft or turbomachine for an aircraft

Patent metadata

Field	Value
Publication number	US-2023123376-A1
Application number	US-202218076976-A
Country	US
Kind code	A1
Filing date	Dec 7, 2022
Priority date	Oct 18, 2018
Publication date	Apr 20, 2023
Grant date	—

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.

First claim

1 . A turbomachine comprising a rotor and a stator, the stator comprising 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, the serrations 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, wherein, defined with reference to a radial distribution of the integral scale of the turbulence, the geometric pattern evolves in a non-periodic manner: in the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and/or transversely to the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution.

2 . The turbomachine according to claim 1 , wherein the successive scaling varies so that said geometric pattern evolves homothetically.

3 . The turbomachine according to claim 1 , wherein a part of the length is free of serrations and a series of at least three peaks and three troughs, consecutively, starting from said part of the length which is free of serrations, has an increasing distance, along said direction of elongation, between two tops of consecutive peaks or troughs.

4 . The turbomachine according to claim 1 , having a longitudinal axis around which extend blades of the rotor, and comprising an outer casing and a hub between which a vein is defined in which the airflow can flow from upstream to downstream, the outer casing extending around the hub, both extending around the longitudinal axis, the profiled structures extending in said vein, individually between the outer casing and the hub, the direction of elongation along which extend the serrations, on the leading edge, being angled with respect to a radial axis, perpendicular to said longitudinal axis.

5 . A turbomachine comprising a rotor and a stator, one of which comprises 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, the serrations 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, wherein, defined with reference to a radial distribution of the integral scale of the turbulence, the geometric pattern evolves in a non-periodic manner: in the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and/or transversely to the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and, wherein the successive scaling varies so that said geometric pattern evolves homothetically.

6 . The turbomachine according to claim 5 , wherein a part of the length is free of serrations and a series of at least three peaks and three troughs, consecutively, starting from said part of the length which is free of serrations, has an increasing distance, along said direction of elongation, between two tops of consecutive peaks or troughs.

7 . The turbomachine according to claim 5 , having a longitudinal axis around which extend blades of the rotor, and comprising an outer casing and a hub between which a vein is defined in which the airflow can flow from upstream to downstream, the outer casing extending around the hub, both extending around the longitudinal axis, the profiled structures extending in said vein to be connected to both the outer casing and the hub, the direction of elongation along which extend the serrations, on the leading edge, being angled with respect to a radial axis, perpendicular to said longitudinal axis, so that the respective connections of said profiled structures to the outer casing is located further downstream than the respective connections of said profiled structures to the hub.

8 . A turbomachine comprising a rotor and a stator, the stator comprising outlet guide vanes and inlet guide vanes, one of the outlet guide vanes and the inlet guide vanes comprising 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, the serrations 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, wherein, defined with reference to a radial distribution of the integral scale of the turbulence, the geometric pattern evolves in a non-periodic manner: in the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and/or transversely to the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution.

9 . The turbomachine according to claim 8 , wherein the successive scaling varies so that said geometric pattern evolves homothetically.

10 . The turbomachine according to claim 8 , wherein a part of the length is free of serrations and a series of at least three peaks and three troughs, consecutively, starting from said part of the length which is free of serrations, has an increasing distance, along said direction of elongation, between two tops of consecutive peaks or troughs.

11 . The turbomachine according to claim 8 , having a longitudinal axis around which extend blades of the rotor, and comprising an outer casing and a hub between which a vein is defined in which the airflow can flow from upstream to downstream, the outer casing extending around the hub, both extending around the longitudinal axis, the profiled structures extending in said vein to be connected to both the outer casing and the hub, the direction of elongation along which extend the serrations, on the leading edge of the outlet guide vanes, being angled with respect to a radial axis, perpendicular to said longitudinal axis, so that the respective connections of said profiled structures to the outer casing is located further downstream than the respective connections of said profiled structures to the hub.

Assignees

• Safran Aircraft Engines
• Office National Detudes Rech Aerospatiales

Inventors

• Gea Aguilera Fernando
• Barrier Raphaël
• Gruber Mathieu Simon Paul
• Polacsek Cyril
• Posson Hélène Dominique Jeanne

Classifications

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• B64C21/10

  using other surface properties, e.g. roughness · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title