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:
Dec. 06, 2022

Filed:

Mar. 24, 2021
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Timothy Andrew Healy, Simpsonville, SC (US);

Abhijit Prabhakar Kulkarni, Hyderabad, IN;

Scott Arthur Day, Greenville, SC (US);

John Rogers Huey, Greenville, SC (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Int. Cl.
CPC ...
G01M 15/14 (2006.01); F01D 21/12 (2006.01); F02C 7/264 (2006.01); F01D 21/14 (2006.01); F01D 21/00 (2006.01); G01M 15/05 (2006.01); G01M 15/10 (2006.01);
U.S. Cl.
CPC ...
F01D 21/12 (2013.01); F01D 21/003 (2013.01); F01D 21/14 (2013.01); F02C 7/264 (2013.01); G01M 15/05 (2013.01); G01M 15/10 (2013.01); G01M 15/14 (2013.01); F05D 2240/35 (2013.01); F05D 2260/80 (2013.01); F05D 2260/99 (2013.01); F05D 2270/303 (2013.01); F05D 2270/304 (2013.01); F05D 2270/3013 (2013.01);
Abstract

A method of detecting flame state of a combustor of a turbine engine. The method includes determining at least one of a first derivative and a second derivative of a compressor discharge pressure of a compressor of the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine exhaust gas temperature of the exhaust gases output by the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine shaft/rotor speed of the turbine engine; determining at least one of a first derivative and a second derivative of combustor dynamic pressure monitoring; and determining a flame state of a combustor of the turbine engine based on the combustor dynamic pressure monitoring, the determined derivatives of the combustion dynamics, compressor discharge pressure, gas turbine shaft/rotor speed, and gas turbine exhaust gas temperature of the exhaust gases.


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