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:
Jul. 03, 2018

Filed:

Dec. 23, 2011
Applicants:

Henrik Amnell, Trollhattan, SE;

Lennart Brottgardh, Trollhattan, SE;

David Russberg, Trollhattan, SE;

Patrik Svantesson, Trollhattan, SE;

Inventors:

Henrik Amnell, Trollhattan, SE;

Lennart Brottgardh, Trollhattan, SE;

David Russberg, Trollhattan, SE;

Patrik Svantesson, Trollhattan, SE;

Assignee:

GKN Aerospace Sweden AB, Trollhattan, SE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 25/16 (2006.01); F01D 25/24 (2006.01);
U.S. Cl.
CPC ...
F01D 25/162 (2013.01); F01D 25/24 (2013.01); F05D 2230/232 (2013.01); F05D 2230/60 (2013.01); Y02T 50/671 (2013.01);
Abstract

The invention concerns a gas turbine engine component () comprising an outer ring structure (), an inner ring structure () and a plurality of circumferentially spaced radial elements () for transferring loads between the inner ring structure () and the outer ring structure (), wherein the outer ring structure () comprises a circular ring member () for withstanding an internal pressure during operation of the gas turbine engine. The invention is characterized in that the outer ring structure () comprises a first set of circumferentially distributed and substantially straight reinforcement ribs () for achieving radial stiffness, wherein the reinforcement ribs () form sides in a polygonal shape and wherein each of said reinforcement ribs () extends between two adjacent radial elements (). The invention also concerns a gas turbine engine () comprising a component () of the above type.


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