Composite blade construction for a propeller or rotor blade

• US 4,966,527 A
• Filed: 08/03/1989
• Issued: 10/30/1990
• Est. Priority Date: 08/03/1988
• Status: Expired due to Fees

• Current Assignee: Herbert Merz
• Original Assignee: MTU Motoren- und Turbinen-Union Muenchen GmbH
• Inventors: Merz, Herbert
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Nguyen, Hoang
• Application Number:
  US07/389,333
• Time in Patent Office: 453 Days
• Field of Search: 416/229 R, 416/229 A, 416/230, 416/244 A, 416/239, 416/217, 416/234, 416/248, 416/241 A, 416/204 R, 416/204 A, 416/214 R, 416/220 R, 416/220 A , 416/223 R, 416/223 A, 416/224
• US Class Current: 416/241.00R
• CPC Class Codes: B29C 70/202 arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] B29C70/207 takes precedence
• CPC Class Codes: B29C 70/30 Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
• CPC Class Codes: B29C 70/865 completely encapsulated
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: B63H 1/26 Blades
• CPC Class Codes: B64C 11/26 Fabricated blades
• CPC Class Codes: F01D 5/30 Fixing blades to rotors; Blade roots ; Blade spacers
• CPC Class Codes: F01D 5/3053 by means of pins
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A composite propeller blade construction has fiber strands extending predominantly in a radial direction and looping around mounting hardware connecting a blade root to a rotor hub. The mounting hardware includes at least one bolt secured to the rotor hub or a shackle member secured to the hub by a mounting bolt and holding a tying bolt so that fiber strand loops forming the blade body loop around the shackle member and around free ends of the tying bolt. The radially extending fiber strands take up centrifugal forces and are enclosed by a jacket, the radially inner end of which is formed as mounting flanges screwed to a respective rim of the hub. The arrangement of the fiber loops is especially suitable for a fiber composite lightweight construction wherein the fibers form redundant load take-up paths and provide an advantageous centrifugal force and moment introduction into the structure.

Claims

1. A composite blade construction, comprising a blade root for connection to a rotor hub defining a rotational axis, mounting means for securing said blade root to said rotor hub, a blade body integrally secured to said blade root, said blade body and said blade root comprising fiber composite material including elongated fiber strands extending substantially radially relative to said rotational axis and forming fiber loops around said mounting means, said fiber strands merging with their radially outer ends into said blade body, jacket means covering said blade body, said jacket means comprising mounting flanges formed at a radially inner end of said jacket means near said blade root, said mounting flanges extending substantially perpendicularly to a radial blade plane, means for securing said mounting flanges to a respective rim of said rotor hub, and wherein said mounting means comprise a shackle member having a radially inner end reaching into a radial opening of said rotor hub, said radially inner shackle end having a through-bore extending substantially in parallel to said rotational axis, a mounting bolt extending through said through-bore, said mounting bolt having ends protruding from said first bore into respective bores of said rotor hub for securing said radially inner shackle end to said rotor hub, and tie means having tie ends projecting from a radially outer shackle end for holding a respective group of fiber loops.

2. The composite blade construction of claim 1, wherein said fiber strands form a central fiber strand group looping around said radially inner shackle end, and two lateral fiber strand sections looping around said tie bolt ends of said tie bolt.

3. The composite blade construction of claim 1, wherein said radially outer end of said shackle member has a further through-bore, said tie means comprising a tie bolt extending through said further through-bore in parallel to a chord through said blade body or in the direction of said chord.

4. The composite blade construction of claim 1, wherein said radially outer end of said shackle member comprises a central saddle and two arms extending substantially axially away from said central saddle in opposite directions, said tie means including tie bolts in said two shackle arms, said tie bolts holding respective fiber loops.

5. The composite blade construction of claim 4, wherein said two shackle arms comprise bore means, said tie bolts extending through said bore means and substantially tangentially to a circle having its center in said rotational axis and defining a plane extending radially and perpendicularly to said rotational axis, whereby said tie bolts (8, 9, ) extend substantially perpendicularly of a chord through said blade body.

6. The composite blade construction of claim 1, wherein said mounting means for securing said blade root to said rotor hub further comprise eccentric means for adjusting said mounting bolt in its position relative to said rotor hub.

7. The composite blade construction of claim 6, wherein said eccentric means comprise an externally threaded bushing with an eccentric hole in which said mounting bolt is received, said bushing being adjustably mounted in said rotor hub.

8. The composite blade construction of claim 6, wherein said eccentric means are part of said mounting bolt.

9. The composite blade construction of claim 1, further comprising vibration damping means (16) operatively arranged between said mounting flanges of said jacket jacked means and said rim of said rotor hub, said vibration damping means having a central dished section surrounded by a ring section, said central dished section having a contour for at least partially enclosing said mounting means which secure the blade root to the rotor hub.

10. The composite blade construction of claim 1, wherein said fiber strands comprise a plurality of fiber strand groups arranged in fan-type patterns which at least partially overlap one another.

11. The composite blade construction of claim 1, wherein said blade body comprises a blade core (4) of shear resistant, lightweight construction, said blade core having a radially inner end resting on said mounting means securing said blade root to said rotor hub.

12. The composite blade construction of claim 1, wherein said jacket means including said mounting flanges are made of fiber reinforced synthetic material.

13. The composite blade construction of claim 12, wherein said fiber reinforced synthetic material of said jacket means comprise fiber types having a high modulus of elasticity within the range of about 235 to about 440 GPa, and wherein said elongated fiber strands of said fiber composite material comprise fiber types having a modulus of elasticity within the range of about 65 GPa to about 440 GPa.

14. The composite blade construction of claim 13, wherein said elongated fiber strands comprise a plurality of layers of fiber strands, wherein fiber types of said strands are so selected that the modulus of elasticity in the longitudinal fiber direction increases from an inwardly located fiber strand layer to an outwardly located fiber strand layer.

15. The composite blade construction of claim 1, wherein said mounting flanges of said jacket means have a curved portion merging into said jacket means, whereby said mounting flanges form a bending spring.

16. The composite blade construction of claim 15, wherein said mounting flanges of said jacket means comprise a plurality of fiber layers, said fiber layers having at least one intermediate fiber layer with a relatively low modulus of elasticity within the range of about 60 to 180 GPa.

17. The composite blade construction of claim 15, wherein said jacket means (12) including said mounting flanges (13) are made substantially of carbon fiber reinforced composite material comprising carbon fibers embedded in a resin matrix, and wherein said jacket means include an erosion protective outer coating made of a polyurethane laquer or a polyurethane elastomer film.

18. The composite blade construction of claim 1, wherein said elongated fiber strands form layers of glass fibers, of p,p'"'"'-aramide fibers, and of carbon fibers respectively embedded in a matrix material.

19. The composite blade construction of claim 1, wherein said fiber strands are arranged in fiber strand loops, said blade construction further comprising lateral retaining elements (18) for holding said fiber strand loops against lateral displacement.

20. The composite blade construction of claim 1, wherein said tie means comprise a tie bolt forming an integral part of said mounting shackle member, said tie bolt having bolt ends projecting out of said shackle member at opposite sides thereof.

21. The composite blade construction of claim 4, wherein said tie bolts and said shackle member form an integral component.