Method of manufacturing a composite blade with a reinforced leading edge

• US 5,392,514 A
• Filed: 09/20/1993
• Issued: 02/28/1995
• Est. Priority Date: 02/06/1992
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cook, James A., Nagle, David P.
• Primary Examiner(s): ROSENBAUM, IRENE CUDA
• Application Number:
  US08/123,769
• Time in Patent Office: 526 Days
• Field of Search: 29/889.6, 29/889.61, 29/889.7, 29/889.71, 264/103, 264/46.4, 264/46.7, 264/45.1, 264/279.1, 416/224, 416/230, 416/241 A, 416/241 R, 416/226
• US Class Current: 29/889.71
• 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

A method of making a shell (30) of a lightweight composite propulsor blade (10) of spar and shell construction having 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 method of manufacturing a composite propulsor blade having an axially extending load bearing spar disposed within a fiber reinforced shell defining an airfoil comprising the steps of:

forming a spar assembly that carries the load absorbed by the propulsive blade having a leading edge, a trailing edge, and a pressure side and a suction side extending therebetween;

wrapping one sheet of fabric material of substantially uniform thickness that is precut to a length exceeding the full extent of the airfoil including the pressure side and suction side defining a blanket about said spar assembly whereby said spar assembly is covered by a fabric wrap by wrapping said one sheet about said spar assembly such that said one sheet overlaps itself at the leading edge so that said fabric wrap has a first relatively uniform thickness overlapping the leading edge of said spar assembly and a second uniform thickness overlapping the remainder of said spar assembly, said first thickness being about twice the thickness as said second thickness; and

impregnating said one sheet of fabric material with a curable resin material whereby upon subsequent curing of the resin material a fiber reinforced shell having an approximately double thick leading edge portion is formed about the spar assembly.

2. A method of manufacturing a composite blade as recited in claim 1 including the step of forming the blanket from a plurality of fabric plies about said spar assembly such that the fabric blanket wraps twice about the leading edge portion of said spar assembly and wraps only once about the remainder of said spar assembly.

3. A method of manufacturing a composite propulsor blade as recited in claim 1 wherein the step of forming said spar assembly comprises:

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

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

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

4. A method of manufacturing a composite propeller blade as recited in claim 3 wherein the step of wrapping one sheet of fabric material about said spar assembly comprises wrapping the at least one sheet of fabric material about said spar assembly such that the fabric blanket wraps twice about the leading edge filler body of said spar assembly and wraps only once about the trailing edge filler body of said spar assembly.

5. A method of manufacturing a composite propeller blade as recited in claim 4 wherein the step of wrapping one sheet of fabric material about said spar assembly comprises wrapping a single blanket of fabric material made up of a plurality of fabric plies about said spar assembly such that the fabric blanket wraps twice about the leading edge filler body of said spar assembly and wraps only once about the trailing edge filler body of said spar assembly.