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.

Date of Patent:
Nov. 07, 2023

Filed:

Aug. 24, 2022
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Jonas S. Banhos, Rocky Hill, CT (US);

Tracy A. Propheter-Hinckley, Rocky Hill, CT (US);

Michael Parkin, South Glastonbury, CT (US);

Assignee:

RTX CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B29C 70/54 (2006.01); B29C 70/56 (2006.01); B32B 37/10 (2006.01); B32B 37/18 (2006.01); B32B 38/18 (2006.01); F01D 5/28 (2006.01); F01D 25/16 (2006.01);
U.S. Cl.
CPC ...
B29C 70/541 (2013.01); B29C 70/543 (2013.01); B29C 70/56 (2013.01); B32B 37/10 (2013.01); B32B 37/18 (2013.01); B32B 38/1808 (2013.01); F01D 5/282 (2013.01); F01D 5/284 (2013.01); F01D 25/162 (2013.01); B32B 2305/72 (2013.01); B32B 2309/12 (2013.01); F05B 2230/90 (2013.01); F05C 2253/04 (2013.01); F05D 2220/323 (2013.01); F05D 2230/60 (2013.01); F05D 2260/30 (2013.01); F05D 2300/6033 (2013.01);
Abstract

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.


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