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:
Feb. 04, 2025

Filed:

Dec. 30, 2022
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Steven W. Burd, Cheshire, CT (US);

Christopher A. Eckett, Simsbury, CT (US);

Assignee:

RTX Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/32 (2006.01); F02C 3/073 (2006.01); F02C 3/10 (2006.01); F02C 3/113 (2006.01); F02C 3/14 (2006.01); F02C 6/18 (2006.01); F02C 6/20 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01);
U.S. Cl.
CPC ...
F02C 7/32 (2013.01); F02C 3/073 (2013.01); F02C 3/113 (2013.01); F02C 3/14 (2013.01); F02C 6/18 (2013.01); F05D 2220/323 (2013.01); F05D 2220/50 (2013.01);
Abstract

An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.


Find Patent Forward Citations

Loading…