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The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 10364700 B1

PDFFull Text
Date of Patent:
Jul. 30, 2019

Filed:

Jun. 28, 2016

Method for forming a composite part of a gas turbine engine

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Bryan W. Olver, Nobleton, CA;

Stephen Caulfeild, Rockwook, CA;

Assignee:

PRATT & WHITNEY CANADA CORP., Longueuil, CA;

Attorney:

Norton Rose Fulbright Canada LLP

Primary Examiner:

Eldon T Brockman

Int. Cl.
CPC ...
F01D 25/24 (2006.01); F01D 25/00 (2006.01); B29B 13/02 (2006.01); B29C 35/02 (2006.01); B29C 65/48 (2006.01); F01D 17/10 (2006.01); F01D 25/12 (2006.01); F01D 25/18 (2006.01); B29C 65/00 (2006.01); B29C 65/02 (2006.01); F02C 7/14 (2006.01); F02C 7/24 (2006.01); B29K 63/00 (2006.01); B29K 71/00 (2006.01); B29K 105/06 (2006.01); B29K 307/04 (2006.01); B29K 309/08 (2006.01); B29L 31/00 (2006.01); B29C 65/50 (2006.01);
U.S. Cl.
CPC ...
F01D 25/005 (2013.01); B29B 13/02 (2013.01); B29C 35/02 (2013.01); B29C 65/02 (2013.01); B29C 65/48 (2013.01); B29C 66/1122 (2013.01); B29C 66/532 (2013.01); B29C 66/71 (2013.01); B29C 66/7392 (2013.01); B29C 66/7394 (2013.01); B29C 66/73751 (2013.01); B29C 66/73753 (2013.01); B29C 66/73755 (2013.01); B29C 66/73941 (2013.01); F01D 17/105 (2013.01); F01D 25/12 (2013.01); F01D 25/18 (2013.01); F01D 25/24 (2013.01); F02C 7/14 (2013.01); F02C 7/24 (2013.01); B29C 65/5057 (2013.01); B29C 66/7212 (2013.01); B29C 2035/0283 (2013.01); B29K 2063/00 (2013.01); B29K 2071/00 (2013.01); B29K 2105/06 (2013.01); B29K 2307/04 (2013.01); B29K 2309/08 (2013.01); B29L 2031/7504 (2013.01); F05D 2220/32 (2013.01); F05D 2260/213 (2013.01); F05D 2300/2102 (2013.01); F05D 2300/224 (2013.01); F05D 2300/603 (2013.01); F05D 2300/614 (2013.01);
Abstract

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

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