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:
Jan. 20, 2026

Filed:

May. 26, 2023
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Paul R. Hanrahan, Sedona, AZ (US);

Michael G. Mccaffrey, Windsor, CT (US);

Assignee:

RTX Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 3/06 (2006.01); B64C 27/12 (2006.01); B64D 27/10 (2006.01); B64D 35/00 (2006.01); F02C 7/36 (2006.01); F02C 9/16 (2006.01);
U.S. Cl.
CPC ...
F02K 3/06 (2013.01); B64C 27/12 (2013.01); B64D 27/10 (2013.01); B64D 35/00 (2013.01); F02C 7/36 (2013.01); F02C 9/16 (2013.01); F05D 2220/328 (2013.01); F05D 2250/314 (2013.01); F05D 2270/02 (2013.01);
Abstract

A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.


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