Rance B Fox from 115 North Rd, Torrington, CT 06791, age 75, Phone: (860) 485-1697

Braided Complex Composite Parts And Methods Of Forming Same

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US Patent:

55760791, Nov 19, 1996

Filed:

Aug 16, 1994

Appl. No.:

8/291284

Inventors:

Thomas P. Forman - Greenwich CT
Rance B. Fox - Milford CT
George E. Sabak - Monroe CT
Timothy A. Sands - Muncy Valley PA
Paul A. Vallier - Kensington CT

Assignee:

Dow-United Technologies Composite Products, Inc. - Wallingford CT

International Classification:

B32B 108

US Classification:

428 341

Abstract:

A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Braided Complex Composite Parts And Methods Of Forming Same

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US Patent:

53993950, Mar 21, 1995

Filed:

Nov 15, 1993

Appl. No.:

8/152508

Inventors:

Thomas P. Forman - Greenwich CT
Rance B. Fox - Milford CT
George E. Sabak - Monroe CT
Timothy A. Sands - Muncy Valley PA
Paul A. Vallier - Kensington CT

Assignee:

Dow-United Technologies Composite Products Inc. - Wallingford CT

International Classification:

B32B 108

US Classification:

428 341

Abstract:

A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Process Of Making Braided Composite Part

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US Patent:

56246188, Apr 29, 1997

Filed:

Jun 7, 1995

Appl. No.:

8/486321

Inventors:

Thomas P. Forman - Greenwich CT
Rance B. Fox - Milford CT
George E. Sabak - Monroe CT
Timothy A. Sands - Muncy Valley PA
Paul A. Vallier - Kensington CT

Assignee:

Dow-United Technologies Composite Products, Inc. - Wallingford CT

International Classification:

B29C 7030
B32B 512
B32B 3100

US Classification:

264103

Abstract:

A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Three Dimensional Stabilization Of Dry Composite Fabric

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US Patent:

48670855, Sep 19, 1989

Filed:

Sep 2, 1988

Appl. No.:

7/239824

Inventors:

Michael W. Brace - Huntington CT
Rance B. Fox - Milford CT
Marilyn Michel - Seymour CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

D05B 2100
D05B 9700

US Classification:

1122621

Abstract:

A method for fabricating and stabilizing three dimensional composite fabric preforms. The method comprises disposing a plurality of fabric plies between upper and lower templates that have substantially the desired preform shape and openings in at least two planes. The fabric plies are joined through the template openings and the templates are removed from the preform. These stabilized preforms maintain tighter tolerances.