Profiled structure for an aircraft or turbomachine for an aircraft

Patent metadata

Field	Value
Publication number	US-11560796-B2
Application number	US-201916657278-A
Country	US
Kind code	B2
Filing date	Oct 18, 2019
Priority date	Oct 18, 2018
Publication date	Jan 24, 2023
Grant date	Jan 24, 2023

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.

First claim

The invention claimed is:

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
transversely to which the profiled structure has 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 profiled structure being such that, along the leading edge and/or trailing edge, the serrations have 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,

wherein the respective directions of elongation of at least some of the profiled structures radially extend about an axis of revolution, from a radially inner end to a radially outer end, and,
wherein, on said at least some of the profiled structures, a distance and/or an amplitude of the serrations is greater at the radially outer end than at the radially inner end.

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 2 , 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 , 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.

5. The turbomachine according to claim 1 , wherein the stator comprises:
stationary guide vanes for guiding the secondary flow, which define said profiled structures, and/or
outlet guide vanes and inlet guide vanes at least some of said outlet guide vanes and inlet guide vanes showing said profiled structures.

6. A turbomachine comprising a stator and a rotor, the rotor comprising a fan adapted to rotate around an axis, the stator comprising, about said axis, an annular separation wall for separating, downstream of the fan, an airflow into a primary flow and a secondary flow, the annular separation wall having a perimeter about the axis and a profiled leading edge extending along said perimeter,
wherein the profiled leading edge has serrations defined by a succession of peaks and troughs,
wherein the serrations have a geometric pattern transformed, over at least a part of said perimeter, by successive scaling, via multiplicative factors, in the direction of said perimeter and/or transverse to the perimeter,
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 said perimeter, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and/or
transversely to the perimeter, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and

wherein the successive scaling vary so that said geometric pattern evolves homothetically.

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

• F01D5/141 Primary

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

• B64C11/18

  Aerodynamic features · CPC title

• F01D9/041

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

• B64C3/10

  Shape of wings · CPC title

• B64C21/10

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