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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 12516635 B1

PDFFull Text
Date of Patent:
Jan. 06, 2026

Filed:

Jan. 15, 2021

Compressor stall mitigation

Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Robert Jon Mcquiston, Cincinnati, OH (US);

Stefan Joseph Cafaro, Maineville, OH (US);

Paul Robert Gemin, Cincinnati, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:

Smith Gambrell & Russell LLP

Primary Examiner:

Jason H Duger

Int. Cl.
CPC ...
F02C 9/00 (2006.01); B64D 27/02 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2024.01); B64D 27/33 (2024.01); B64D 31/06 (2024.01); F01D 15/10 (2006.01); F02C 3/04 (2006.01); F02C 6/20 (2006.01); F02C 7/00 (2006.01); F02C 7/057 (2006.01); F02C 9/28 (2006.01); F02K 3/06 (2006.01); F04D 25/04 (2006.01); F04D 25/06 (2006.01); F04D 27/00 (2006.01); F04D 27/02 (2006.01); F02K 5/00 (2006.01);
U.S. Cl.
CPC ...
F02C 9/00 (2013.01); B64D 27/10 (2013.01); B64D 31/06 (2013.01); F01D 15/10 (2013.01); F02C 3/04 (2013.01); F02C 6/20 (2013.01); F02C 7/00 (2013.01); F02C 7/057 (2013.01); F02C 9/28 (2013.01); F02K 3/06 (2013.01); F04D 25/04 (2013.01); F04D 25/06 (2013.01); F04D 27/001 (2013.01); F04D 27/02 (2013.01); F04D 27/0223 (2013.01); F04D 27/0261 (2013.01); B64D 27/026 (2024.01); B64D 27/33 (2024.01); F02K 5/00 (2013.01); F05D 2220/323 (2013.01); F05D 2270/052 (2013.01); F05D 2270/101 (2013.01); F05D 2270/301 (2013.01);
Abstract

A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising a gas turbine engine having a compressor and an electric machine coupled to the compressor, the method comprising: sensing data indicative of a pressure within the compressor of the gas turbine engine; determining conditions within the compressor are within a threshold of a stall limit for the compressor based at least in part on the sensed data indicative of the pressure within the compressor of the gas turbine engine; and modifying a torque of the compressor using the electric machine in response to determining the conditions within the compressor are within the threshold of the stall limit for the compressor to reduce a risk of compressor stall.

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