High stiffness airoil and method of manufacture

• US 6,190,133 B1
• Filed: 08/14/1998
• Issued: 02/20/2001
• Est. Priority Date: 08/14/1998
• Status: Expired due to Term

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Allison Engine Company, Inc., Rolls-Royce North American Technologies Incorporated
• Inventors: King, Brian Paul, Ewing, Bruce Allan, Ress, Robert Anthony Jr.
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): McAleenan, James M.
• Application Number:
  US09/134,392
• Time in Patent Office: 921 Days
• Field of Search: 416/229.R, 416/229.A, 416/230, 416/241.R, 416/242, 416/223.A, 416/241.B, 298/897, 298/897.1, 295/275
• US Class Current: 416/229.00A
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A cast metallic airfoil structure having a high stiffness core positioned therein for increasing the stiffness of the airfoil. In one embodiment, the high stiffness core is preferably formed of gamma titanium aluminde or a titanium metal matrix composite and is metallurgically bonded to the cast metallic airfoil structure. In one form the airfoil structure forms a portion of an integrally bladed rotor, and in a second form the airfoil structure has a dove tail attachment portion.

Claims

1. An apparatus comprising a single-cast metallic airfoil structure having a high stiffness metallic core positioned therein and coupled with said structure.

2. The apparatus of claim 1, wherein the airfoil structure has a tip end and an opposite attachment end with a length therebetween, and wherein said high stiffness metallic core extending almost the entire distance of said length.

3. The apparatus of claim 2, wherein the airfoil structure has a leading edge and a trailing edge with an outer surface extending from said leading edge to said trailing edge and from said tip end to said attachment end, and wherein said high stiffness metallic core extending from about said leading edge to about said trailing edge.

4. The apparatus of claim 3, wherein said metallic core is solid.

5. The apparatus of claim 3, wherein the airfoil structure defining a cast cover encapsulating said high stiffness metallic core from said leading edge to said trailing edge and from said tip end to near said attachment end.

6. The apparatus of claim 5, wherein said high stiffness metallic core has a substantially airfoil shaped portion spaced from said outer surface.

7. The apparatus of claim 5, wherein said high stiffness metallic core has an outer surface that abuts and is metallurgically bonded to said cast metallic airfoil structure.

8. The apparatus of claim 7, wherein said high stiffness metallic core is a consolidated metal matrix composite.

9. The apparatus of claim 7, wherein said high stiffness metallic core is formed of gamma titanium aluminide.

10. The apparatus of claim 1, wherein:

said airfoil structure has a first outer surface extending between a tip end and an opposite attachment end and further extending between a leading edge and a trailing edge;

said airfoil structure defining a cast cover encapsulating said high stiffness metallic core from said leading edge to said trailing edge and from said tip end to near said attachment end;

said high stiffness metallic core has a substantially airfoil shaped portion spaced from said first outer surface, and wherein said high stiffness core has a second outer surface that abuts and is metallurgically bonded to said cast metallic airfoil structure; and

wherein said high stiffness metallic core is formed of a material selected from a group consisting of consolidated metal matrix composites and gamma titanium aluminide.

11. The apparatus of claim 2, which further includes a disk, and wherein the apparatus is coupled to said disk.

12. The apparatus of claim 11, wherein said airfoil structure defining a cast cover encapsulating said high stiffness metallic core, and wherein a portion of said cast cover is coupled to an outer periphery of said disk by a diffusion bond.

13. The apparatus of claim 11, wherein said airfoil structure defining a cast cover encapsulating said high stiffness metallic core, and wherein a portion of said cast cover is coupled to an outer periphery of said disk by a braze bond.

14. The apparatus of claim 11, wherein said airfoil structure defining a cast cover encapsulating said high stiffness metallic core, and wherein a portion of said cast cover is coupled to an outer periphery of said disk by linear friction welding.

15. The apparatus of claim 11, wherein said airfoil structure defining a cast cover encapsulating said high stiffness metallic core, and wherein a portion of said cast cover is coupled to an outer periphery of said disk by forge bonding.

16. The apparatus of claim 11, wherein said airfoil structure defining a cast cover encapsulating said high stiffness metallic core, and wherein a portion of said cast cover is coupled to an outer periphery of said disk by fusion welding.

17. The apparatus of claim 11, wherein said apparatus further includes an attachment portion, and wherein said disk includes an attachment receiving portion for receiving the attachment portion therein.

18. An airfoil, comprising:

a high stiffness metallic core member; and

a cast metallic monolithic structure having said high stiffness core member positioned within and fixedly coupled thereto, wherein the high stiffness metallic core member has a modulus of elasticity greater than the modulus of elasticity of the cast metallic monolithic structure and wherein the airfoil has a modulus of elasticity greater than the modulus of elasticity of said cast metallic monolithic structure.

19. The airfoil of claim 18, wherein said high stiffness metallic core has a room temperature modulus of elasticity on the order of 24×

10⁶ pounds per square inch, and wherein the cast metallic structure has a room temperature modulus of elasticity on the order of 17×

10⁶ pounds per square inch.

20. The airfoil of claim 19, wherein said cast metallic monolithic structure is formed of a titanium alloy, and wherein said high stiffness core member is formed of gamma titanium aluminide.

21. The airfoil of claim 20, wherein said high stiffness metallic core member is solid.

22. The airfoil of claim 21, wherein said high stiffness metallic core member has a portion with a first substantially airfoil shape.

23. The airfoil of claim 22, wherein said cast metallic monolithic structure is metallurgically bonded to an outer surface of said high stiffness metallic core member.

24. The airfoil of claim 23, wherein said cast metallic monolithic structure has a portion with a second substantially airfoil shape, and wherein said high stiffness metallic core member occupies a substantial portion within the volume defined by said portion with a second substantially airfoil shape.

25. The airfoil of claim 24, wherein the airfoil defines a gas turbine engine blade.

26. The airfoil of claim 24, wherein the airfoil defines a gas turbine engine vane.

27. The airfoil of claim 18, wherein said high stiffness metallic core has a room temperature longitudinal modulus of elasticity on the order of 32×

10⁶ pounds per square inch, and wherein the cast metallic monolithic structure has a room temperature modulus of elasticity on the order of 17×

10⁶ pounds per square inch.

28. The airfoil of claim 27, wherein said cast metallic monolithic structure is formed of a titanium alloy, and wherein said high stiffness metallic core member is formed of a titanium metal matrix composite.

29. The airfoil of claim 28, wherein said core member is solid and has a portion with a first substantially airfoil shape, and wherein said cast metallic monolithic structure is metallurgically bonded to an outer surface of said high stiffness metallic core member.

30. The airfoil of claim 29, wherein said cast metallic monolithic structure has a portion with a second substantially airfoil shape, and wherein said high stiffness metallic core member occupying a substantial portion within the volume defined by said portion with a second substantially airfoil shape.

31. The airfoil of claim 30, wherein said titanium metal matrix composite includes a plurality of silicon carbide fibers, and wherein said high stiffness metallic core has a fiber loading of forty percent by volume.

32. An apparatus, comprising:

a stiffening core formed of a material selected from a group consisting of metal matrix composites and gamma titanium aluminide; and

a cast metallic structure having an outer surface defining an airfoil, said cast metallic structure formed around and connected to said stiffening core, wherein said cast structure substantially encloses said first stiffening core.

33. The apparatus of claim 32, wherein said metal matrix composite defines a titanium metal matrix composite.

34. The apparatus of claim 32, wherein said cast structure is a single cast structure.

35. The apparatus of claim 34, wherein said cast metallic structure is metallurgically bonded to said stiffening core.

36. The apparatus of claim 35, wherein the stiffening core has a density less than the density of said cast metallic structure so that the apparatus has a density less than the density of said cast metallic structure.

37. A method for fabricating an airfoil, comprising:

providing a high stiffness member and a casting mold having a cavity adapted for forming an airfoil shaped structure therein;

positioning the high stiffness member within the cavity;

casting a metal structure around the high stiffness member after said positioning; and

forming a metallurgical bond between the metal structure and the high stiffness member after said casting.

38. The method of claim 37, wherein said forming includes hot isostatic pressing to densify the airfoil.

39. The method of claim 38, which further comprises forming the high stiffness member into a substantially airfoil shape prior to said positioning.

40. The method of claim 39, wherein said providing of the high stiffness member is accomplished by one of permanent mold casting or die casting.

41. The method of claim 39, wherein said providing of the high stiffness member is accomplished by powder metallurgy manufacturing techniques.

42. The method of claim 39, wherein said providing of the high stiffness member is accomplished by titanium metal matrix manufacturing techniques.