Tear-away composite fan stator vane

• US 5,569,019 A
• Filed: 12/21/1995
• Issued: 10/29/1996
• Est. Priority Date: 12/22/1993
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Alliedsignal Inc.
• Inventors: Wilson, Bruce D., Stenard, Steven C., Katariya, Devinder N., Rich, Ronald J.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/576,023
• Time in Patent Office: 313 Days
• Field of Search: 415/200, 416/229 R, 416/229 A, 416/230
• US Class Current: 415/200
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A unitary composite stator vane for a gas turbine engine comprising an aerodynamically configured airfoil section, a foot extending substantially perpendicularly from one end of the airfoil section, and a smoothly contoured transition section interconnecting the airfoil section with the foot. The stator vane is comprised of a composite material including a plurality of compression molded, heat cured plies. The plies include a plurality of centrally located internal plies of reinforcement material of continuous yarns of para-aramid fibers. On each side of the internal plies are plies of resin impregnated graphite fiber material. The graphite fibers are protected by an external steel wire mesh ply covering the leading edges of the vanes. Substantially all of the internal para-aramid reinforcement fibers are discontinuous proximate the transition section between the airfoil section and foot.

Claims

1. In a gas turbine engine having a rotary primary fan and a stationary fan stator vane assembly disposed downstream of said fan, said assembly comprising:

an annular outer shroud having openings therein;

an annular inner hub having openings therein and disposed concentrically to and radially inwardly of said shroud to define a radial space therebetween;

a plurality of unitary stator vanes comprised of a nonmetallic composite material extending across said radial space and through said openings in said shroud and hub, each of said vanes having

a radial inner end extending through the associated one of said openings in the hub, and

an axially and circumferentially extending foot on the opposite radial outer end, said foot disposed radially outside said shroud, and

an aerodynamically configured airfoil section disposed radially across said space, and

a smoothly contoured transition section interconnecting said foot and said airfoil section,

said composite material comprising a plurality of compression molded, heat cured plies, said plies including a plurality of centrally located internal plies of reinforcement material of continuous yarns of para-aramid fibers, and a plurality of plies of resin impregnated graphite fiber material on each side of said centrally located plies of reinforcement material, substantially all of said para-aramid fibers being broken proximate said transition section between said airfoil section and said foot.

2. A gas turbine engine as set forth in claim 1, wherein said stator vanes are located upstream of and crossing in front of both an outer bypass duct and an inner core passage, each of said vanes configured and located such that under sufficient force of impact said airfoil section tears away from said foot proximate the break in said para-aramid fibers, and passes into the bypass duct.

3. A unitary composite stator vane for a gas turbine engine comprising an aerodynamically configured airfoil section, a foot extending substantially perpendicularly from one end of said airfoil section, and a smoothly contoured transition section interconnecting said foot and said airfoil section, said stator vane comprised of a composite material including a plurality of compression molded, heat cured plies, said plies including a plurality of centrally located internal plies of reinforcement material of unidirectional yarns of para-aramid fibers, a plurality of plies of resin impregnated graphite fiber material on each side of said centrally located plies of reinforcement material, and an external steel wire mesh ply on the leading edges of said vanes, substantially all of said para-aramid fibers being broken proximate said transition section between said airfoil section and said foot.

4. A composite stator vane as set forth in claim 3, wherein said plies of para-aramid fibers are disposed with the same orientation of yarns.

5. A composite stator vane as set forth in claim 4, wherein each of said plies of para-aramid fibers are non woven.

6. A composite stator vane as set forth in claim 5, wherein a first inner set of said plies of graphite fiber on each side of said centrally located plies of para-aramid fibers are oriented at a first acute angle relative to the orientation of said para-aramid fibers.

7. A composite stator vane as set forth in claim 6, wherein a second outer set of said plies of graphite fiber on each side of said first set are oriented at a second angle greater than said first set.

8. A composite stator vane as set forth in claim 7, wherein said first acute angle is approximately 20 degrees.

9. A composite stator vane as set forth in claim 8, wherein said second angle is approximately 55 degrees.

10. A composite stator vane as set forth in claim 9, there being seven plies of said centrally located reinforcement material.

11. A composite stator vane as set forth in claim 10, wherein said first inner set of said plies of graphite fiber includes at least two plies, and said second outer set of said plies of graphite fiber includes at least two plies, such that the total number adjacent plies of both said para-arimid fiber and said graphite fiber is at least fifteen.