Composite blade with reinforced leading edge

• US 5,439,353 A
• Filed: 06/09/1994
• Issued: 08/08/1995
• Est. Priority Date: 02/06/1992
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Cook, James A., Nagle, David P.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/257,401
• Time in Patent Office: 425 Days
• Field of Search: 416/229 R, 416/230
• US Class Current: 416/230
• CPC Class Codes: B29C 70/86 Incorporated in coherent impregnated reinforcing layers, e.g. by winding
• CPC Class Codes: B29D 99/0028 hollow blades
• CPC Class Codes: B29K 2105/0809 Fabrics
• 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: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49336 Blade making
• CPC Class Codes: Y10T 29/49337 Composite blade

Abstract

Composite Blade With Reinforced Leading Edge

The shell (30) of a lightweight composite propulsor blade (10) of spar and shell construction has a leading edge portion (39) having twice the thickness as the remainder (33, 35, 37) of the shell thereby enhancing resistance to foreign object damage and improving erosion resistance.

Claims

1. A composite propulsor blade comprising:

a spanwisely extending load bearing spar assembly having a leading edge, a trailing edge, and a pressure side and a suction side extending therebetween; and

an outer shell disposed about said spar assembly, said shell having a first relatively uniform thickness overlapping the leading edge of said spar assembly and a second relatively uniform thickness overlapping the remainder of said spar assembly, said first thickness being about twice as thick as said second thickness.

2. A composite propulsor blade as recited in claim 1 wherein said spar assembly comprises:

a spanwisely extending load bearing spar member having a leading edge and a trailing edge;

a first filler body of lightweight cellular material disposed on a leading edge of the spar member thereby defining the leading edge of said spar assembly; and

a second filler body of lightweight cellular material disposed on a trailing edge of the spar member thereby defining the trailing edge of said spar assembly.

3. A composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil,

said spar being capable of carrying the load absorbed by the propulsive blade, said spar having a leading edge, a trailing edge, and a pressure side and a suction side extending therebetween;

a single sheet of fabric material of substantially uniform thickness dimensioned to a length exceeding the full extent of the airfoil including the pressure side and suction side defining a blanket about said spar,

said leading edge, said trailing edge, said pressure side and said suction side of said spar being covered by said single sheet wrapped about said spar such that a portion of said single sheet overlaps itself at the leading edge,

said single sheet having a first portion of relatively uniform thickness overlapping the leading edge of said spar and a second portion of uniform thickness overlapping the remainder of said spar, said first thickness being about twice the thickness as said second thickness, and

said single sheet of fabric being formed from a curable resin material whereby said single layer when cured defines said fiber reinforced shell having an approximately double thick leading edge.

4. A composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil as claimed in claim 3 wherein said single sheet is formed from multiple ply fabric.

5. A composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil as claimed in claim 3 wherein said single sheet is formed from a plurality of individual plies.

6. A composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil as claimed in claim 4 wherein said single sheet is formed from a woven material of fiberglass fibers.

7. A composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil as claimed in claim 3 wherein said single sheet is formed from a material consisting essentially of graphite fibers, aramid fibers or fiberglass fibers or a combination thereof.