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. 06, 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);

Michael Todd Radwanski, Newport, KY (US);

Ernesto Andres Vallejo Ruiz, Cincinnati, OH (US);

Aaron Michael Dziech, Dry Ridge, KY (US);

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

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F23R 3/00 (2006.01); F02C 3/14 (2006.01); F01D 5/06 (2006.01); F01D 9/04 (2006.01); F01D 5/22 (2006.01); F23R 3/10 (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); F02C 3/14 (2013.01); F23R 3/10 (2013.01); F05D 2220/32 (2013.01); F05D 2230/53 (2013.01); F05D 2240/35 (2013.01); F05D 2300/6033 (2013.01); F23R 2900/00018 (2013.01); Y02T 50/672 (2013.01);
Abstract

Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.


Find Patent Forward Citations

Loading…