Turbomachine aerofoil

• US 7,025,568 B2
• Filed: 12/22/2003
• Issued: 04/11/2006
• Est. Priority Date: 01/30/2003
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Jones, Richard M
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Edgar, Richard A
• Application Number:
  US10/740,847
• Publication Number:
  US 20040151585A1
• Time in Patent Office: 841 Days
• Field of Search: 416/90.R, 416/132.A, 416/140, 416/500
• US Class Current: 416/90.00R
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/668 damping or preventing mechanical vibrations
• CPC Class Codes: Y10S 416/50 Vibration damping features
• CPC Class Codes: Y10T 29/49339 Hollow blade

Abstract

A fan blade (26) comprises a leading edge (44), a trailing edge (46), a concave wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex wall portion (52) extending from the leading edge (44) to the trailing edge (46). A flexible wall (56) is arranged within the fan blade (26) to partially define a plurality of chambers (60) with an internal surface (54) of the convex wall portion (52). The flexible wall (56) is arranged substantially parallel to the internal surface (54) of the convex wall portion (52) and a plurality of walls (64) connect the internal surface (54) of the concave wall portion (50) and the flexible wall (56). The chambers (60) contain a fluid. The chambers (60) are interconnected by apertures (62) such that in operation deflection of the flexible wall (56) by vibrations of the fan blade (36) produce a flow of fluid between the chambers (60) through apertures (62), which is restricted by the apertures (62) to damp vibrations of the fan blade (26).

Claims

1. A turbomachine aerofoil comprising a leading edge, a trailing edge, a concave wall portion extending from the leading edge to the trailing edge and a convex wall portion extending from the leading edge to the trailing edge, at least one flexible wall being arranged within the aerofoil to at least partially define a plurality of chambers, the chambers containing a fluid, the chambers being interconnected by apertures such that in operation deflection of the at least one flexible wall by vibrations of the aerofoil produces a flow of fluid between chambers through the apertures which is restricted by the apertures to damp vibrations of the aerofoil wherein the flexible wall is arranged to define a plurality of chambers with an internal surface of the concave wall portion, the flexible wall being arranged substantially parallel to the internal surface of the concave wall portion and at least one wall connecting the internal surface of the convex wall portion and the flexible wall.

2. A turbomachine aerofoil as claimed in claim 1 wherein the concave wall portion, the convex wall portion, the at least one flexible wall comprise titanium or a titanium alloy.

3. A turbomachine aerofoil as claimed in claim 1 wherein the concave wall portion and the convex wall portion form a continuous integral wall.

4. A turbomachine aerofoil as claimed in claim 1 wherein the concave wall portion, the convex wall portion and the at least one flexible wall are integral.

5. A turbomachine aerofoil as claimed in claim 4 wherein the convex wall portion, the concave wall portion and the at least one flexible wall are diffusion bonded together and have been superplastically formed.

6. A turbomachine aerofoil as claimed in claim 1 wherein the fluid comprises a gas.

7. A turbomachine aerofoil as claimed in claim 6 wherein the gas comprises argon or air.

8. A turbomachine aerofoil as claimed in claim 1 wherein there are means to control the pressure of the fluid in the chambers.

9. A turbomachine comprising a turbomachine aerofoil as claimed in claim 1.

10. A turbomachine as claimed in claim 9 wherein the turbomachine comprises means to supply fluid to the chambers of the turbomachine aerofoil to control the pressure of the fluid in the chambers.

11. A turbomachine as claimed in claim 10 wherein the turbomachine comprises a compressor to supply fluid to the chambers of the turbomachine aerofoil to control the pressure of the fluid in the chambers.

12. A turbomachine aerofoil comprising a leading edge, a trailing edge, a concave wall portion extending from the leading edge to the trailing edge and a convex wall portion extending from the leading edge to the trailing edge, at least one flexible wall being arranged within the aerofoil to at least partially define a plurality of chambers, the chambers containing a fluid, the chambers being interconnected by apertures such that in operation deflection of the at least one flexible wall by vibrations of the aerofoil produces a flow of fluid between chambers through the apertures which is restricted by the apertures to damp vibrations of the aerofoil wherein the turbomachine aerofoil is a compressor blade, a fan blade, a fan outlet guide vane or a compressor vane.

13. A turbomachine aerofoil as claimed in claim 12 wherein the flexible wall is arranged to define a plurality of chambers with an internal surface of the concave wall portion, the flexible wall being arranged substantially parallel to the internal surface of the concave wall portion and at least one wall connecting the internal surface of the convex wall portion and the flexible wall.

14. A turbomachine aerofoil as claimed in claim 12 wherein the flexible wall is arranged to define a plurality of chambers with an internal surface of the convex wall portion, the flexible wall being arranged substantially parallel to the internal surface of the convex wall portion and at least one wall connecting the internal surface of the concave wall portion and the flexible wall.

15. A turbomachine aerofoil as claimed in claim 12 wherein a first flexible wall is arranged to define a plurality chambers with an internal surface of the convex wall portion and a second flexible wall being arranged to define a plurality of chambers with an internal surface of the concave wall portion, the first flexible wall being arranged substantially parallel to the internal surface of the convex wall portion and the second flexible wall being arranged substantially parallel to the internal surface of the concave wall portion and at least one wall connecting the first flexible wall and the second flexible wall.

16. A turbomachine aerofoil as claimed in claim 12 wherein a first flexible wall is to arranged to define a plurality of chambers with a second flexible wall, the first and second flexible walls being substantially parallel, the first and second flexible walls connecting the internal surface of the concave wall portion and the internal surface of the convex wall portion.

17. A turbomachine aerofoil comprising a leading edge, a trailing edge, a concave wall portion extending from the leading edge to the trailing edge and a convex wall portion extending from the leading edge to the trailing edge, at least one flexible wall being arranged within the aerofoil to at least partially define a plurality of chambers, the chambers containing a fluid, the chambers being interconnected by apertures such that in operation deflection of the at least one flexible wall by vibrations of the aerofoil produces a flow of fluid between chambers through the apertures which is restricted by the apertures to damp vibrations of the aerofoil wherein the flexible wall is arranged to define a plurality of chambers with an internal surface of the convex wall portion, the flexible wall being arranged substantially parallel to the internal surface of the convex wall portion and at least one wall connecting the internal surface of the concave wall portion and the flexible wall.

18. A turbomachine aerofoil comprising a leading edge, a trailing edge, a concave wall portion extending from the leading edge to the trailing edge and a convex wall portion extending from the leading edge to the trailing edge, at least one flexible wall being arranged within the aerofoil to at least partially define a plurality of chambers, the chambers containing a fluid, the chambers being interconnected by apertures such that in operation deflection of the at least one flexible wall by vibrations of the aerofoil produces a flow of fluid between chambers through the apertures which is restricted by the apertures to damp vibrations of the aerofoil wherein a first flexible wall is arranged to define a plurality chambers with an internal surface of the convex wall portion and a second flexible wall being arranged to define a plurality of chambers with an internal surface of the concave wall portion, the first flexible wall being arranged substantially parallel to the internal surface of the convex wall portion and the second flexible wall being arranged substantially parallel to the internal surface of the concave wall portion and at least one wall connecting the first flexible wall and the second flexible wall.

19. A turbomachine aerofoil comprising a leading edge, a trailing edge, a concave wall portion extending from the leading edge to the trailing edge and a convex wall portion extending from the leading edge to the trailing edge, at least one flexible wall being arranged within the aerofoil to at least partially define a plurality of chambers, the chambers containing a fluid, the chambers being interconnected by apertures such that in operation deflection of the at least one flexible wall by vibrations of the aerofoil produces a flow of fluid between chambers through the apertures which is restricted by the apertures to damp vibrations of the aerofoil wherein a first flexible wall is to arranged to define a plurality of chambers with a second flexible wall, the first and second flexible walls being substantially parallel, the first and second flexible walls connecting the internal surface of the concave wall portion and the internal surface of the convex wall portion.

20. A method of manufacturing a turbomachine aerofoil from at least four metal workpieces comprising the steps of:

(a) forming at least four metal workpieces,

(b) applying stop off material to predetermined areas of the surfaces of at least three of the at least four metal workpieces,

(c) arranging the workpieces into a stack such that the stop off material is between the at least four metal workpieces,

(d) heating and applying pressure across the thickness of the stack to diffusion bond the at least four metal workpieces together in areas other than the predetermined area to form an integral structure,

(e) heating and internally pressurising the interior of the integral structure at the surfaces of at least two of the at least three metal workpieces to hot form at least two of the metal workpieces into an aerofoil shape to form a turbomachine aerofoil and to superplastically form at least one of the metal workpieces,

(f) heating and internally pressurising the interior of the integral structure at the surface of the other one of the at least three metal workpieces to form at least one

flexible wall to at least partially define a plurality of chambers, the chambers being interconnected by apertures, (g) supplying a fluid into the chambers.

21. A method as claimed in claim 20 comprising forming five metal workpieces.