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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.

Patent No.:

US 11073157 B1

PDFFull Text
Date of Patent:
Jul. 27, 2021

Filed:

Jul. 18, 2019

Efficient, low pressure ratio propulsor for gas turbine engines

Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Edward J. Gallagher, West Hartford, CT (US);

Byron R. Monzon, Cromwell, CT (US);

Shari L. Bugaj, Haddam, CT (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:

Carlson, Gaskey & Olds, P.C.

Primary Examiner:

Justin D Seabe

Int. Cl.
CPC ...
F02C 7/36 (2006.01); F04D 29/02 (2006.01); F02K 3/06 (2006.01); F01D 5/28 (2006.01); F01D 5/14 (2006.01); F02K 1/06 (2006.01); F01D 15/12 (2006.01); F04D 29/053 (2006.01); F04D 29/32 (2006.01); F04D 29/38 (2006.01); F04D 29/52 (2006.01); F04D 29/56 (2006.01); F02C 3/06 (2006.01);
U.S. Cl.
CPC ...
F04D 29/023 (2013.01); F01D 5/147 (2013.01); F01D 5/282 (2013.01); F01D 15/12 (2013.01); F02C 3/06 (2013.01); F02C 7/36 (2013.01); F02K 1/06 (2013.01); F02K 3/06 (2013.01); F04D 29/053 (2013.01); F04D 29/325 (2013.01); F04D 29/388 (2013.01); F04D 29/526 (2013.01); F04D 29/563 (2013.01); F05D 2220/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/327 (2013.01); F05D 2220/36 (2013.01); F05D 2260/4031 (2013.01); F05D 2300/603 (2013.01); Y02T 50/60 (2013.01);
Abstract

A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

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