Thermoformed cascades for jet engine thrust reversers

Patent metadata

Field	Value
Publication number	US-9895840-B2
Application number	US-201414278292-A
Country	US
Kind code	B2
Filing date	May 15, 2014
Priority date	May 15, 2014
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

First claim

What is claimed is:

1. A method of fabricating a cascade grid panel for a jet engine thrust reverser, the method comprising:
forming a strongback assembly from a plurality of continuous fiber-reinforced thermoplastic strongbacks that are spaced apart to form slots between adjacent strongbacks;
assembling a plurality of discontinuous fiber-reinforced thermoplastic vanes, a set of hard tool inserts, and a set of expandable soluble mandrels within the slots of the strongback assembly to form a preassembled cascade grid panel wherein forming the preassembled cascade grid panel includes:
placing the hard tool inserts into alternating ones of cavities defined by the thermoplastic vanes along the slots; and
placing expandable soluble mandrels into remaining ones of the cavities including between the alternating cavities; and

co-consolidating the preassembled cascade grid panel under heat and pressure to form the cascade grid panel, wherein the applied heat and pressure expand the expandable soluble mandrels to compress the thermoplastic vanes against the thermoplastic strongbacks and hard tool inserts during the co-consolidating.

2. The method of claim 1 , further comprising:
before said forming of the strongback assembly, fabricating the plurality of thermoplastic vanes by compression molding a thermoplastic resin reinforced with the discontinuous fibers.

3. The method of claim 1 , further comprising:
before said forming of the strongback assembly, fabricating the plurality of thermoplastic strongbacks by continuous compression molding a thermoplastic resin reinforced with continuous fibers.

4. The method of claim 1 , wherein assembling the plurality of thermoplastic vanes within the slots of the strongback assembly includes:
loading the plurality of thermoplastic vanes and plurality of the thermoplastic strongbacks into compression mold tooling, wherein co-consolidating the preassembled cascade grid panel includes:
co-consolidating the vanes and the strongbacks using the compression mold tooling to compress the thermoplastic vanes against the thermoplastic strongbacks.

5. The method of claim 4 , further comprising:
cooling the cascade grid panel after the co-consolidation;
removing the cascade grid panel from the compression mold tooling; and
dissolving the soluble mandrels.

6. The method of claim 5 , further comprising:
after removing the cascade grid panel and dissolving the soluble mandrels, trimming the cascade grid panel.

7. The method of claim 4 , wherein placing the hard tool inserts into the alternating ones of the cavities further comprises:
indexing the vanes relative to the strongbacks within the compression mold tooling.

8. The method of claim 4 , wherein loading the plurality of thermoplastic vanes and plurality of the thermoplastic strongbacks into the compression mold tooling further comprises:
resting the preassembled panel onto a tool base onto which the hard tool inserts are fixed.

9. The method of claim 8 , wherein loading the plurality of thermoplastic vanes and plurality of the thermoplastic strongbacks into the compression mold tooling further comprises:
inserting the expandable soluble mandrels into the remaining ones of the cavities to also rest on the tool base.

10. The method of claim 9 , wherein loading the plurality of thermoplastic vanes and plurality of the thermoplastic strongbacks into compression mold tooling further comprises:
placing the tool base having the fixed inserts, the preassembled panel, and the set of expandable soluble mandrels into a compression press.

11. The method of claim 10 , wherein the compression press comprises a top tool, bottom tool, and side tools which during the co-consolidating compress a top, bottom, and sides, respectively, of the preassembled panel.

12. The method of claim 4 , wherein co-consolidating the preassembled cascade grid panel to form the cascade grid panel includes:
heating each of the thermoplastic vanes and thermoplastic strongbacks of the preassembled cascade grid panel; and
compressing the thermoplastic vanes against the thermoplastic strongbacks using the compression mold tooling.

Assignees

• Boeing Co

Inventors

• Bartel Aaron William
• Morrow Robert Darel
• Scott Alan James
• Curaudeau Alexandre D
• Olaniyan Tunde Abiodun
• England Leonard Joseph
• Wilkerson Randall Dow
• Westberg Robin L

Classifications

• B29C70/342

  using isostatic pressure · CPC title

• B29C33/52

  soluble or fusible {(in particular used in injection moulding B29C45/4457)} · CPC title

• B29C70/081

  Combinations of fibres of continuous or substantial length and short fibres · CPC title

• F02K1/64

  Reversing fan flow · CPC title

• B29C33/505 Primary

  cores or mandrels, e.g. inflatable (B29C33/0016 takes precedence; for winding and joining B29C53/824; for supporting articles during joining B29C66/634; flexible cores for vulcanizing tyres B29D30/0654) · CPC title