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:
Jun. 25, 2024

Filed:

Sep. 15, 2021
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Brandon Wayne Miller, Liberty Township, OH (US);

David Marion Ostdiek, Liberty Township, OH (US);

Darek Tomasz Zatorski, Fort Wright, KY (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 11/00 (2006.01); B64C 11/18 (2006.01); B64C 11/48 (2006.01); F01D 9/04 (2006.01); F01D 17/16 (2006.01); F02C 6/20 (2006.01); F02K 1/46 (2006.01); F02K 3/02 (2006.01); B64D 27/00 (2006.01);
U.S. Cl.
CPC ...
B64C 11/001 (2013.01); B64C 11/18 (2013.01); B64C 11/48 (2013.01); F01D 9/041 (2013.01); F01D 17/16 (2013.01); F02C 6/206 (2013.01); F02K 1/46 (2013.01); F02K 3/025 (2013.01); B64D 2027/005 (2013.01); F05B 2240/12 (2013.01); F05B 2260/96 (2013.01); F05D 2220/324 (2013.01); F05D 2220/325 (2013.01); F05D 2220/36 (2013.01); F05D 2250/30 (2013.01); F05D 2250/51 (2013.01); F05D 2250/52 (2013.01); F05D 2260/14 (2013.01);
Abstract

A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.


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