Noise Reducing Gas Turbine Engine Airfoil

• US 20200132087A1
• Filed: 10/25/2018
• Published: 04/30/2020
• Est. Priority Date: 10/25/2018
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kumar, Arun, Jain, Nitesh, Kray, Nicholas Joseph, Moniz, Thomas Ory, Breeze-Stringfellow, Andrew
• Granted Patent: US 10,788,053 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/667 by influencing the flow pattern, e.g. suppression of turbulence
• CPC Class Codes: F04D 29/684 by fluid injection
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2240/24 for turbines
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

Claims

1. A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge, the airfoil comprising:

a pressure side;

a suction side; and

a trailing edge sheath, defining an outer surface, coupled to the trailing edge of the airfoil and extending at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath, wherein the trailing edge sheath defines a fluid passageway extending along at least a portion of the span, and wherein the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

2. The airfoil of claim 1, wherein the at least one aperture is configured to supply pressurized air from the fluid passageway to the outer surface to reduce wakes, velocity deficits, or both.

3. The airfoil of claim 1, further comprising:

a fluid inlet at the root fluidly coupled to the fluid passageway.

4. The airfoil of claim 1, wherein the trailing edge sheath extends between the root and the tip along the span.

5. The airfoil of claim 1, wherein each aperture of the at least one aperture is positioned between a point along the span 50% of the span from the root and the tip.

6. The airfoil of claim 1, wherein each aperture of the at least one aperture is positioned on the pressure or suction side, and wherein each aperture of the at least one aperture is positioned between 10% and 20% of the chord from the trailing edge at a point along the span of each aperture.

7. The airfoil of claim 1, wherein the at least one aperture comprises at least one slot.

8. The airfoil of claim 1, wherein the at least one aperture comprises a plurality of blow holes distributed along the span.

9. The airfoil of claim 8, wherein the plurality of blow holes define at least one gap between adjacent blow holes, and wherein each gap of the at least one gap defines the same length.

10. The airfoil of claim 8, wherein the plurality of blow holes define at least one gap between adjacent blow holes, at least one gap proximate to the root defining a first length, and at least one gap proximate to the tip defining a second length different than the first length, and wherein the first length is longer than the second length.

11. The airfoil of claim 8, wherein each blow hole of the plurality of blow holes defines a width on the outer surface and a length through the trailing edge sheath, and wherein at least one blow hole defines a ratio of the length over the width between 0.9 and 1.1.

12. The airfoil of claim 8, wherein each blow hole of the plurality of blow holes defines a centerline and an exterior line on the outer surface tangent to a point nearest the leading edge and a point nearest the trailing edge of each blow hole on the outer surface, and wherein at least one of the blow holes defines a centerline having an aperture angle between the centerline and the exterior line of at least fifteen degrees but less than or equal to thirty degrees.

13. The airfoil of claim 1, wherein the airfoil is a fan blade of a gas turbine engine.

14. A gas turbine engine defining a central axis, the gas turbine engine comprising:

an engine shaft extending along the central axis;

a compressor attached to the engine shaft and extending radially about the central axis;

a combustor positioned downstream of the compressor to receive a compressed fluid therefrom;

a turbine mounted on the engine shaft downstream of the combustor to provide a rotational force to the compressor; and

a plurality of airfoils operably connected to the engine shaft, each of the plurality of airfoils defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge, the plurality of airfoils including at least one noise reducing airfoil comprising;

a pressure side;

a suction side; and

a trailing edge sheath, defining an outer surface, coupled to the trailing edge of the airfoil and extending at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath, wherein the trailing edge sheath defines a fluid passageway extending along at least a portion of the span, and wherein the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

15. The gas turbine engine of claim 14, further comprising a fan section including the plurality of airfoils configured as fan blades.

16. The gas turbine engine of claim 14, wherein each airfoil of the plurality of airfoils is a noise reducing airfoil.

17. The gas turbine engine of claim 16, wherein each aperture of the at least one aperture is positioned between a point along the span 50% of the span from the root and the tip.

18. The gas turbine engine of claim 14, wherein the plurality of airfoils comprises a first plurality of airfoils and a second plurality of airfoils arranged to alternate around the engine shaft, wherein each airfoil of the first plurality of airfoils is a noise reducing airfoil.

19. The gas turbine engine of claim 18, wherein the at least one aperture comprises a plurality of blow holes distributed along the span, the plurality of blow holes defining at least one gap between adjacent blow holes, and wherein at least one gap proximate to the root defines a first length, and at least one gap proximate to the tip defines a second length different than the first length, and wherein the first length is longer than the second length.

20. The gas turbine engine of claim 14, wherein the compressor is fluidly coupled to a fluid inlet at the root of each noise reducing airfoil such that the compressor is fluidly coupled to the fluid passageway.