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:
Oct. 25, 2022

Filed:

Apr. 14, 2021
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Paul R. Adams, Glastonbury, CT (US);

Shankar S. Magge, South Windsor, CT (US);

Joseph B. Staubach, Colchester, CT (US);

Wesley K. Lord, South Glastonbury, CT (US);

Frederick M. Schwarz, Glastonbury, CT (US);

Gabriel L. Suciu, Glastonbury, CT (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/36 (2006.01); F02C 3/107 (2006.01); F02C 9/18 (2006.01); F01D 11/12 (2006.01); F01D 5/06 (2006.01); F01D 25/24 (2006.01); F02C 3/04 (2006.01); F02C 7/20 (2006.01); F04D 19/02 (2006.01); F02K 3/075 (2006.01); F02K 3/06 (2006.01); F04D 29/32 (2006.01); F04D 29/54 (2006.01);
U.S. Cl.
CPC ...
F02C 7/36 (2013.01); F01D 5/06 (2013.01); F01D 11/122 (2013.01); F01D 25/24 (2013.01); F02C 3/04 (2013.01); F02C 3/107 (2013.01); F02C 7/20 (2013.01); F02C 9/18 (2013.01); F02K 3/06 (2013.01); F02K 3/075 (2013.01); F04D 19/02 (2013.01); F04D 29/324 (2013.01); F04D 29/545 (2013.01); F05B 2250/283 (2013.01); F05D 2220/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/3215 (2013.01); F05D 2240/35 (2013.01); F05D 2240/60 (2013.01); F05D 2260/40311 (2013.01);
Abstract

A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is between 0.50 and 0.55, or is greater than 0.55 and less than or equal to 0.65.


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