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:
Aug. 13, 2019

Filed:

Jan. 27, 2017
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Brandon ALlanson Reynolds, Cincinnati, OH (US);

Jonathan David Baldiga, Amesbury, MA (US);

Andrew Scott Bilse, Cincinnati, OH (US);

Mark Eugene Noe, West Chester, OH (US);

Brett Joseph Geiser, Cincinnati, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F23R 3/00 (2006.01); F02C 7/22 (2006.01); F01D 5/06 (2006.01); F01D 9/04 (2006.01); F01D 5/22 (2006.01); F01D 9/02 (2006.01);
U.S. Cl.
CPC ...
F23R 3/002 (2013.01); F01D 5/06 (2013.01); F01D 5/225 (2013.01); F01D 9/023 (2013.01); F01D 9/04 (2013.01); F01D 9/042 (2013.01); F02C 7/22 (2013.01); F05D 2230/30 (2013.01); F05D 2230/53 (2013.01); F05D 2240/35 (2013.01); F05D 2300/6033 (2013.01); F23R 2900/00018 (2013.01);
Abstract

Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.


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