Advanced composite rotor blade

• US 5,346,367 A
• Filed: 09/02/1986
• Issued: 09/13/1994
• Est. Priority Date: 12/21/1984
• Status: Expired due to Term

• 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: Doolin, Leonard J., Olsen, Eric G., Capowich, George, Reinfelder, William C.
• Primary Examiner(s): Brown, David
• Application Number:
  US06/902,991
• Time in Patent Office: 2,933 Days
• Field of Search: 416/230 A, 416/230 R, 416/223 R, 416/229 R, 416/241 R, 416/241 A, 416/226, 156/213, 156/221, 156/245, 156/293, 264/137, 264/152, 264/258
• US Class Current: 416/230
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: B29L 2031/082 Blades, e.g. for helicopters
• CPC Class Codes: B64C 2027/4736 from composite materials
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: F05B 2240/30 Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
• CPC Class Codes: Y10T 156/103 Encasing or enveloping the configured lamina

Abstract

An advanced composite blade construction for a helicopter rotor blade using for the most part fiber reinforced plastic materials in which the major assembly of blade elements is a single step co-cure operation and in which an integral spar/skin carries centrifugal, flapwise and chordwise loads and also incorporates redundant means to carry torsional loads and a honeycomb core carries shear and aerodynamic pressures loads.

Claims

1. An advanced composite helicopter rotor blade of predetermined airfoil contour from leading edge to trailing edge including upper and lower spar/skin members, a leading edge sheath and a trailing edge stiffener, an internal I-shaped web located at a midchord position of the blade, said web having flanges in contact with the inner surfaces of said upper and lower spar/skin members, a first honeycomb core positioned on the leading edge side of said web, and a second honeycomb core positioned on the trailing edge side of said web, said spar/skin members, leading edge sheath, and web comprising the structural support of said blade for reaction of torsion and bending moments, said trailing edge stiffener, leading edge sheath and said spar/skin members combining to comprise a secondary structural support, a metallic counterweight positioned within said leading edge sheath for a portion of the blade span, said leading edge sheath being joined to said upper and lower spar/skin members by a plurality of bond planes, balance weights positioned in the honeycomb core in the outer portion of the blade and a tip closure, said spar/skin members being formed of a plurality of preselected ply groupings, and wherein said blade is manufactured substantially by a single major cure process combining and positioning said upper and lower spar/skin members, I-shaped web, first and second honeycomb cores, and trailing edge stiffener in a matched metal mold, closing the mold against the back pressure of the honeycomb core, compacting the spar/skin laminates, and curing said blade members, thus forming a major blade portion, followed by the bonding of said leading edge sheath to said major blade portion.

2. A helicopter blade according to claim 1 wherein said sheath comprises a plurality of selected ply groupings, and is formed to shape independently of the major blade portion wherein the process consists in the steps of laying up said ply groupings into a mold, inserting said metallic counterweight, and compacting and curing said assembly.

3. A helicopter blade according to claim 1 wherein the back pressure applied to the spar/skin members by the honeycomb core members is provided for by use of overthick honeycomb core wherein said spar/skin members and said core become compacted due to the closure of the matched metal mold.

4. A helicopter blade according to claim 1 wherein the spar/skin ply grouping has a spar portion consisting of plies of composite material in which there are two plies at 0°

, one ply at +30°

, and one ply at -30° and

a skin portion consisting of plies of composite material in which there is one ply at +45° and

another ply at -45°

.

5. A helicopter blade according to claim 1 wherein said spar/skin tapers in chordwise and spanwise directions.

6. A helicopter blade according to claim 1 wherein the wall of said I-shaped web contacts the adjacent edge of said honeycomb cores and the inner surfaces of the flanges of said I-shaped web are compacted against necked-down outer surfaces.