Composite blade with partial length spar

• US 5,269,658 A
• Filed: 12/24/1990
• Issued: 12/14/1993
• Est. Priority Date: 12/24/1990
• 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: Carlson, Charles E. K., Violette, John A.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Mattingly, Todd
• Application Number:
  US07/633,566
• Time in Patent Office: 1,086 Days
• Field of Search: 416/223 R, 416/224, 416/226, 416/229 A, 416/229 R, 416/230, 416/232, 416/500, 29/889.6, 29/889.7, 29/889.71, 29/889.72
• US Class Current: 416/229.00R
• CPC Class Codes: B64C 11/26 Fabricated blades
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F04D 29/668 damping or preventing mechanical vibrations
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 416/50 Vibration damping features
• CPC Class Codes: Y10T 29/49337 Composite blade

Abstract

A composite axial flow rotary machine blade (50) and method of blade construction is disclosed. A partial-length, spanwisely-disposed hollow spar (20) partially captures a shaped foam core (30) which extends from within the spar'"'"'s cavity (26) along a substantial length of the blade (50) in a spanwise fashion. A resin-impregnated high strength, high modulus cloth (34) and graphite (32) composition overlays the spar-core assembly (36) and forms the casing (50) with airfoil regions (52, 54) of the propeller blade (10). This construction results in a rotor blade (50) with enhanced natural frequencies thereby providing for an enhanced operational speed range.

Claims

1. A rotor blade extending a given spanlength from a flange for mounting the blade to a hub spanwisely to a blade tip and having an airfoil section having a leading edge, a trailing edge and a relatively flat pressure surface extending therebetween on one side of the blade and a relatively flat suction surface extending therebetween on the opposite of the blade, the blade comprising:

a spanwisely extending spar having a proximate end that provides the flange for attaching the spar to the hub and a distal end defining a hollow cavity therein and having a flared open end opening to the spar cavity disposed therein, said spar extending for a length ranging from 10% to 50% of the blade spanlength;

a spanwisely extending core of lightweight foam filler extending from a proximate end disposed within the spar cavity through the opening and beyond the flared open end of the distal end of the spar a predetermined spanwise distance to a distal end of the blade tip;

a first laminate wrap formed of a plurality of cloth layers disposed about the spar and the core, the first laminate wrap having a plurality of layers of high strength fibers interspersed among the plurality of cloth layers so as to spanwisely extend along the pressure and suction surfaces of the blade, thereby forming a preliminary composite assembly;

additional foam filler shaped to mate with the preliminary composite assembly to form portions of the blade'"'"'s leading and trailing airfoil edges; and

a second laminate wrap formed of a plurality of cloth layers disposed about the preliminary composite assembly and proximately located shaped foam filler.

2. The blade as recited in claim 1, wherein the cloth layers consist essentially of woven high strength fibers.

3. The blade as recited in claim 1, wherein the high strength fibers are graphite fibers.

4. The blade as recited in claim 1, wherein the spar is of metallic composition.

5. The blade as recited in claim 1, wherein the core consists essentially of low density foam.

6. The blade as recited in claim 1, wherein the spar is at least one-quarter the length of the airfoil span of the blade.