Turbine engine with an airfoil having a set of dimples

Patent metadata

Field	Value
Publication number	US-11933193-B2
Application number	US-202117529685-A
Country	US
Kind code	B2
Filing date	Nov 18, 2021
Priority date	Jan 8, 2021
Publication date	Mar 19, 2024
Grant date	Mar 19, 2024

Abstract

A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

First claim

What is claimed is:

1. An airfoil comprising:
an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction; and
a set of dimples provided on the outer wall, with each dimple of the set of dimples having a non-perforated section including:
a dimple leading edge;
a dimple trailing edge provided aft of the dimple leading edge in the stream-wise direction; and
at least one lateral edge extending between the dimple leading edge and the dimple trailing edge, the at least one lateral edge converging from the dimple leading edge and towards the dimple trailing edge.

2. The airfoil of claim 1 , wherein the set of dimples are arranged in rows in the stream-wise direction, and at least one row is staggered with respect to the other rows.

3. The airfoil of claim 2 , wherein the set of dimples are arranged in columns in the span-wise direction.

4. The airfoil of claim 1 , wherein the non-perforated section constantly increases in depth in the stream-wise direction.

5. The airfoil of claim 4 , wherein each dimple of the set of dimples extends a stream-wise length between the leading edge and the trailing edge, and a depth of each dimple first increases from the dimple leading to a maximum depth and then the depth then decreases from the maximum depth to the dimple trailing edge.

6. The airfoil of claim 5 , wherein a steam-wise location of the maximum depth of each dimple of the set of dimples is provided within an area of the dimple extending between greater than 50% and less than 100% of the stream-wise length.

7. The airfoil of claim 5 , wherein a portion of the non-perforated section from the maximum depth to the dimple trailing edge defines a curved cross section when viewed in the span-wise direction.

8. The airfoil of claim 1 , wherein the at least one lateral edge converges from the dimple leading edge and to the dimple trailing edge.

9. The airfoil of claim 1 , wherein the dimple leading edge includes a rounded edge and the at least one lateral edge extends from the rounded edge.

10. A gas turbine engine comprising:
a first airfoil including:
a pressure side, a suction side, a leading edge, a trailing edge, a root, and a tip, wherein the leading edge and the trailing edge define a stream-wise direction, wherein the root and the tip define a span-wise direction, and wherein a throat is defined by a minimum distance between the suction side of the first airfoil and a trailing edge of a second airfoil adjacent the suction side of the first airfoil, the throat defining a span-wise direction throat line on the suction side; and
a set of dimples on the suction side, each of the dimples of the set of dimples having a non-perforated section, wherein the set of dimples have a first density in an area between the span-wise direction throat line and the trailing edge, wherein the set of dimples have a second density in an area between the span-wise direction throat line and the leading edge, wherein the first density is greater than the second density.

11. The gas turbine engine of claim 10 , wherein the set of dimples are arranged in rows in the stream-wise direction, and at least one row is staggered with respect to the other rows.

12. The gas turbine engine of claim 10 , wherein the non-perforated section increases in depth in the stream-wise direction, each dimple of the set of dimples extends in a stream-wise length between a dimple leading edge and a dimple trailing edge, and the depth first increases from the dimple leading edge to a maximum depth and then the depth decreases from the maximum depth to the dimple trailing edge.

13. The gas turbine engine of claim 12 , wherein a steam-wise location of the maximum depth of the dimple is provided in an area of the dimple extending between greater than 50% and less than 100% of the stream-wise length.

14. The gas turbine engine of claim 12 , wherein a portion of the non-perforated section from the maximum depth to the dimple trailing edge defines a curved cross section when viewed in the span-wise direction.

15. The gas turbine engine of claim 12 , wherein the depth constantly increases from the dimple leading edge to the maximum depth.

16. The gas turbine engine of claim 12 , wherein the depth constantly decreases from the maximum depth to the dimple trailing edge.

17. The gas turbine engine of claim 10 , the first airfoil is provided within at least a portion of at least one of a compressor section, a turbine section, a fan section, an exhaust section or a bypass duct of the gas turbine engine.

18. The gas turbine engine of claim 10 , wherein the suction side defines a convex portion of the airfoil and the pressure side defines a concave portion of the airfoil.

19. The gas turbine engine of claim 10 , wherein the set of dimples are arranged in rows in the stream-wise direction and in columns in the span-wise direction, with the set of dimples having a greater number of at least one of rows or columns along the suction side from the throat to the trailing edge than from the leading edge to the throat.

Assignees

• Ge Avio Srl
• Gen Electric

Inventors

• Patil Pratish
• Goyal Amit
• Manoharan Mahendran
• Bertini Francesco
• Loganathan Jaikumar

Classifications

• F01D5/145 Primary

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

• F05D2240/31

  with roughened surfaces · CPC title

• F01D5/141 Primary

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

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2250/11

  triangular · CPC title