Turbine blade with metallic attachment and method of making the same

• US 5,314,309 A
• Filed: 12/10/1991
• Issued: 05/24/1994
• Est. Priority Date: 05/25/1990
• Status: Expired due to Term

• Current Assignee: Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Sundstrand Corporation (Rtx Corporation)
• Inventors: Brown, Jeffrey A., Blakeley, Anthony, Carrington, Martin W., Horihan, Gregory E., Konicek, Timothy S., O'Callaghan, Patrick J.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): LARSON, JAMES
• Application Number:
  US07/804,391
• Time in Patent Office: 896 Days
• Field of Search: 416/230 A, 416/230 R, 416/226, 416/239, 416/241 A, 416/241 R, 416/202, 416/241 B, 29/888.025, 29/889.21, 29/889.71, 29/527.2, 264/258, 264/135
• US Class Current: 416/226
• CPC Class Codes: B29C 70/081 Combinations of fibres of continuous or substantial length and short fibres
• CPC Class Codes: B29C 70/14 oriented
• CPC Class Codes: B29C 70/46 using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
• CPC Class Codes: B29C 70/76 Moulding on edges or extremities of the preformed part
• CPC Class Codes: B29C 70/86 Incorporated in coherent impregnated reinforcing layers, e.g. by winding
• CPC Class Codes: B29C 70/885 with incorporated metallic wires, nets, films or plates as lost heating elements B29C35/0272, B29C61/0625
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: B29K 2063/00 Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
• CPC Class Codes: B29K 2105/0845 Woven fabrics
• CPC Class Codes: B29K 2105/12 of short lengths, e.g. chopped filaments, staple fibres or bristles
• CPC Class Codes: B29K 2305/02 Aluminium
• CPC Class Codes: B29K 2705/00 Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
• CPC Class Codes: B29L 2031/082 Blades, e.g. for helicopters
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49337 Composite blade

Abstract

A turbine blade (1), for example, for a ram air turbine engine, and method of making the turbine blade, wherein the turbine blade (1) includes a blade retention insert member (2) having a hub connector (3). The turbine blade (1) is fabricated by using sheet molding compound consisting essentially of discontinuous short fibers (7) initially random spaced within a polymer matrix sheet. A plurality of sheets of sheet molding compound are precut to a desired configuration or shape and placed in a heated blade mold. Heat and pressure are applied to the mold causing the sheet molding compound to flow around the blade retention insert member (2) and fill the mold cavity. The flow of the sheet molding compound causes the initially randomly oriented short fibers (7) to preferentially align in the direction of flow to rigidify the turbine blade (1). Fiber woven cloth skins (8) may integrally molded with the sheet molding compound during the compression molding process to accommodate high loads, and an aluminum chopped strand veil cloth (9) may also be integrally molded into the blade (1) or layers of conductive material may be deposited on at least portions of the surface of the turbine blade (1) during a secondary operation. At least one woven cloth material (6) may also be integrally molded into the turbine blade (1) to react to bending loads and to provide additional load transfer capabilities.

Claims

1. A turbine blade comprising an elongated, molded blade of composite material consisting essentially of short fibers positioned in an epoxy resin, and a rotor retention member having an insert at a first end of said member and a hub securing end at a second opposite end of said member, said insert being integrally molded into said composite material of said molded blade at one end of said blade with said hub securing end of said member protruding from said one end of the blade for connecting the turbine blade to a hub of a turbine rotor, wherein short fibers of said composite material are aligned in parallel to each other in a longitudinal direction of said elongated blade as a result of flow of the composite material in said direction occurring during a molding of the molded blade, so as to rigidify the elongated turbine blade.

2. A turbine blade according to claim 1, wherein the composite material is formed by integrally molding a plurality of sheets of fiber material having initially random positioned fibers in the epoxy resin.

3. A turbine blade according to claim 2, wherein the short fibers have a length of between 0.25" to 2.0".

4. A turbine blade according to claim 3, wherein the rotor retention member is fashioned of a titanium alloy.

5. A turbine blade according to claim 2, wherein the fibers consist essentially of one of carbon, graphite, glass, steel, aramide or ceramic material.

6. A turbine blade according to claim 5 wherein the rotor retention member is fashioned of a stainless steel.

7. A turbine blade according to claim 1, further comprising means the molded blade for reacting to bending loads and for providing additional load transfer capabilities.

8. A turbine blade according to claim 7, wherein said means for reacting includes at least one internal rib.

9. A turbine blade according to claim 7, wherein said means for reacting includes at least one woven cloth.

10. A turbine blade according to claim 7, further comprising at least one thin layer of conductive material on a surface of the molded blade for arresting lightning strikes.

11. A turbine blade according to claim 7, further comprising at least one aluminum chopped strand veil cloth in the composite material of the molded blade to arrest lightning strikes.

12. A turbine blade according to claim 7, wherein means are arranged at least at surface portions of the molded blade for accommodating increased loads.

13. A turbine blade according to claim 12, wherein said means for accommodating includes at least one fiber woven cloth skin in the composite material of the molded blade.

14. A turbine blade according to claim 1, wherein the insert is angled relative to the longitudinal axis of the hub securing end of the rotor retention member such that the insert extends along a central line of the molded blade of composite material.

15. A turbine blade according to claim 1, wherein said rotor retention member is formed of metal.

16. A method of manufacturing an elongated, composite turbine blade, the method comprising the steps of providing a rotor retention member having an insert at a first end of the member and a hub securing end at a second opposite end of the member for connecting the turbine blade to a hub of a turbine rotor, providing a plurality of sheets of molding compound consisting essentially of short randomly positioned fibers arranged in a polymer matrix, precutting the sheets of molding compound into a desired configuration, placing said sheets and said insert of the retention member in a molding cavity of a mold and integrally molding the plurality of sheets and retention member in the mold by applying heat and pressure to form a composite blade by causing the molding compound to flow about said insert end of said retention member and to fill the mold cavity such that said short randomly positioned fibers are aligned in parallel to each other in a longitudinal direction of said elongated blade as a result of flow of the molding compound in said direction occurring during the molding so as to rigidify the composite turbine blade.

17. A method according to claim 16, wherein the step of integrally molding includes placing the plurality of sheets about the rotor retention member, heating the sheets to a predetermined temperature under an application of a predetermined pressure for a predetermined period of time to form the blade with the rotor retention member integrally molded therewith.

18. A method according to claim 17, wherein the predetermined temperature is 300°

F.

19. A method according to claim 18, wherein the predetermined pressure is 1,000 psi.

20. A method according to claim 19, wherein the predetermined period of time is twenty minutes.

21. A method according to claim 20 wherein the fibers have a length of between 0.25" to 2.00".

22. A method according to claim 21, wherein the fibers consist essentially of one of carbon, graphite, glass, steel, aramide or ceramic material.

23. A method according to claim 22, further comprising the step of pretreating the rotor retention member to enhance a bonding between the rotor retention member and the sheet molding compound.

24. A method according to claim 23, wherein the step of pretreating includes subjecting at least the insert end of the rotor retention member to an alkali etch and applying a primer coat to at least the insert end of the rotor retention member.

25. A method according to claim 24, wherein the primer is an epoxy resin, and wherein the step of pretreating further includes curing the epoxy resin for a predetermined curing time at a predetermined curing temperature.

26. A method according to claim 25, wherein the predetermined curing temperature is about 250°

F.

27. A method according to claim 25, wherein the predetermined curing time is thirty minutes.

28. A method according to claim 16, wherein the fibers consist essentially of one of carbon, graphite, glass, steel, aramide or ceramic material.

29. A method according to claim 28, further comprising the step of pretreating the rotor retention member to enhance a bonding between the rotor retention member and the sheet molding compound.

30. A method according to claim 29, wherein the step of pretreating includes subjecting at least the insert end of the rotor retention member to an alkali etch and applying a primer coat to at least the insert end of the rotor retention member.

31. A method according to claim 16, wherein the primer is an epoxy resin, and wherein the step of pretreating further includes curing the epoxy resin for a predetermined curing time at a predetermined curing temperature.

32. A method according to claim 30 further comprising the steps of providing at least one fiber woven cloth skin for accommodating high loads at least at surface portions of the blade, and integrally molding said at least one fiber woven cloth skin into the turbine blade during the step of integrally molding.

33. A method according to claim 16, further comprising the step of providing at least one woven cloth material for reacting to bending loads of the blade, and integrally molding the at least one woven cloth material into the blade during the step of integrally molding.

34. A method according to claim 16, further comprising the step of depositing at least one thin layer of conductive material on at least a portion of an outer surface of the blade for arresting lightning strikes.

35. A method according to claim 16, further comprising providing at least one aluminum chopped strand veil cloth for arresting lightning strikes, and integrally molding the at least one aluminum chopped strand veil cloth during the step of integrally molding.

36. A method according to claim 16, wherein said insert is angled relative to the longitudinal axis of the hub securing end of the rotor retention member and said insert is molded in the composite blade with the insert extending along a central line of the blade.