Rotary machine with a frangible composite blade

• US 9,243,512 B1
• Filed: 01/14/2015
• Issued: 01/26/2016
• Est. Priority Date: 01/14/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Zatorski, Darek Tomasz, Breeze-Stringfellow, Andrew, Prentice, Ian Francis, Vondrell, Randy M.
• Primary Examiner(s): Verdier, Christopher
• Application Number:
  US14/596,815
• Time in Patent Office: 377 Days
• Field of Search: 415/9, 416/2, 416/229.A, 416/230, 416/241.A
• US Class Current: 1/1
• CPC Class Codes: B64C 11/26 Fabricated blades
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A rotary machine with at least one frangible composite blade that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided. The composite blade having provisions for dissipating energy, self-shredding, and predetermined release trajectory. A method for manufacturing the composite blade and assembling the blade into a rotary machine is also provided.

Claims

1. A rotary machine comprising:

a plurality of composite blades circumscribing a central longitudinal axis of the rotary machine,

the composite blades having a root, a tip, and a span therebetween,

a leading edge, a trailing edge, and a chord therebetween,

at least one of the composite blades having at least one energy dissipating member extending along the span and distributed along the chord, the at least one energy dissipating member having at least one strand, wherein the at least one energy dissipating member is at least partially covered with a release agent, wherein the at least one energy dissipating member is at least partially co-cured with the at least one of the composite blades, wherein the at least one energy dissipating member comprises at least one damage initiator, wherein the at least one strand is coupled to the at least one damage initiator, wherein the at least one damage initiator comprises at least one pouch, wherein the at least one damage initiator comprises at least one plunger adapted to conform to the at least one pouch, wherein the at least one plunger is coupled to the at least one strand, the at least one pouch being at least partially filled with filler.

2. The rotary machine of claim 1, wherein the least one energy dissipating, member is adapted to shred the at least one of the composite blades having at least one energy dissipating member after a portion of the at least one of the composite blades having at least one energy dissipating member is released.

3. The rotary machine of claim 1, wherein the at least one energy dissipating member is adapted to align the trajectory of a released portion of the at least one of the composite blades having at least one energy dissipating member.

4. The rotary machine of claim 1, wherein the at least one energy dissipating member is adapted to dissipate the energy of a released portion of the at least one of the composite blades having at least one energy dissipating member.

5. The rotary machine of claim 1, further comprising a rotor, wherein the at least one energy dissipating member is adapted to assemble with the rotor.