BLADE OR VANE FOR A GAS TURBINE ENGINE

• US 20190101002A1
• Filed: 09/12/2018
• Published: 04/04/2019
• Est. Priority Date: 10/04/2017
• Status: Abandoned Application

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: DUFFIN, Roger S., GONZALEZ-GUTIERREZ, Gabriel
• Application Number:
  US16/128,671
• Publication Number:
  US 20190101002A1
• 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: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F04D 29/388 characterised by construction
• CPC Class Codes: F04D 29/666 by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
• CPC Class Codes: F04D 29/667 by influencing the flow pattern, e.g. suppression of turbulence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/3217 for the first stage of a compressor or a low pressure compressor
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2230/10 by removing material
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2240/305 related to the pressure side of a rotor blade
• CPC Class Codes: F05D 2240/306 related to the suction side of a rotor blade
• CPC Class Codes: F05D 2240/31 with roughened surfaces
• CPC Class Codes: F05D 2250/183 zigzag
• CPC Class Codes: F05D 2250/294 : grooved
• CPC Class Codes: F05D 2260/96 : Preventing, counteracting or reducing vibration or noise

Abstract

A blade or vane for a gas turbine engine comprising a pressure surface and a suction surface. The pressure surface or the suction surface comprises a roughness zone which is configured to provide greater flow resistance in a direction along the blade or vane than in a direction across the blade or vane.

Claims

1. A blade or vane for a gas turbine engine comprising a pressure surface and a suction surface, wherein at least one of the pressure surface and the suction surface comprises a roughness zone which is configured to provide greater flow resistance in a direction (y) along the blade or vane than in a direction (x) across the blade or vane.

2. A blade or vane for a gas turbine engine as claimed in claim 1, wherein the roughness zone is elongate and extends generally along the blade or vane.

3. A blade or vane for a gas turbine engine as claimed in claim 1, wherein the roughness zone comprises a plurality of elongate roughened areas which are spaced apart in a direction along the blade or vane and extend generally in a flow direction across the blade or vane.

4. A blade or vane for a gas turbine engine as claimed in claim 3, wherein the roughened areas are substantially continuous along their length.

5. A blade or vane for a gas turbine engine as claimed in claim 3, wherein a plurality of smooth areas are formed between the roughened areas, wherein the smooth areas generally extend in the flow direction across the blade or vane, wherein optionally the smooth areas are polished areas and the roughened areas are unpolished areas.

6. A blade or vane for a gas turbine engine as claimed in claim 3, wherein:

the roughened areas are areas which have been machined or processed to provide increased roughness compared to a remainder of the suction or pressure surface;

or

the roughened areas comprise a roughened coating or roughened element which is applied to the blade or vane.

7. A blade or vane for a gas turbine engine as claimed in claim 1, wherein the roughness zone comprises a plurality of grooves are spaced apart in a direction along the blade or vane and extend generally in a flow direction across the blade or vane, and wherein, optionally, a plurality of raised areas are formed between the grooves, wherein the raised areas generally extend in the flow direction across the blade or vane, roughened areas optionally being formed on the raised areas.

8. A blade or vane for a gas turbine engine as claimed in claim 3, wherein the roughened areas are substantially aligned with the flow streamlines across the blade or vane.

9. A blade or vane for a gas turbine engine as claimed in claim 7, wherein the grooves are substantially aligned with the flow streamlines across the blade or vane.

10. A blade or vane for a gas turbine engine as claimed in claim 3, wherein:

the roughened areas are substantially linear and are arranged in parallel;

or

the roughened areas are arcuate across the suction surface of the blade;

or

the roughened areas are substantially zig-zag shaped.

11. A blade or vane for a gas turbine engine as claimed in claim 7, wherein:

the grooves are substantially linear and are arranged in parallel;

or

the grooves are arcuate across the suction surface of the blade;

or

the grooves are substantially zig-zag shaped.

12. A blade or vane for a gas turbine engine as claimed in claim 1, wherein:

the roughness zone is formed proximate a leading edge of the blade or vane;

or the roughness zone is formed within the foremost 10% of the chord of the blade or vane;

or

the roughness zone extends from approximately 20% of the blade or vane height from a root of the blade to approximately 80% of the blade or vane height from the root of the blade or vane;

or

the roughness zone is arranged to resist or impede spanwise flow along the blade or vane in use.

13. A blade or vane for a gas turbine engine as claimed in claim 1, wherein the roughness zone is a flutter control feature.

14. A blade or vane as claimed in claim 1, wherein the roughness zone is provided on the suction surface.

15. A blade or vane as claimed in claim 1, wherein the roughness zone is provided on the pressure surface.

16. A blade for a gas turbine engine as claimed in claim 1, wherein the blade is a fan blade for a fan of a gas turbine engine.

17. A fan or bladed disk for a gas turbine engine comprising one or more blades or vanes according to claim 1.

18. A gas turbine engine comprising a fan or bladed disk according to claim 17.

19. A method of manufacturing a blade or vane for a gas turbine engine according to claim 1.

20. A method of modifying a blade or vane for a gas turbine engine comprising forming a roughness zone on a suction surface or pressure surface of the blade or vane, the roughness zone being configured to provide greater flow resistance in a direction (y) along the blade than in a direction (x) across the blade or vane.