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. 19, 2021

Filed:

Oct. 05, 2018
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Brian D. Merry, Andover, CT (US);

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

Karl L. Hasel, Manchester, CT (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/36 (2006.01); F02K 3/00 (2006.01); F01D 25/16 (2006.01); F02K 3/04 (2006.01); F02C 7/06 (2006.01); F02C 3/04 (2006.01);
U.S. Cl.
CPC ...
F02K 3/00 (2013.01); F01D 25/162 (2013.01); F02C 3/04 (2013.01); F02C 7/06 (2013.01); F02C 7/36 (2013.01); F02K 3/04 (2013.01); Y10T 29/4932 (2015.01);
Abstract

A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.


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